tut axial rotor stat or

822019 Tut Axial Rotor Stat Or

httpslidepdfcomreaderfulltut-axial-rotor-stat-or 130CFX-5 Tutorials Page 257

Master Contents Master Index Help On Help

CFX-5 Tutorials

Tutorial 12

Flow in an AxialRotorStator

Sample files used in this tutorial can be copied to your working

directory from ltCFXROOTgtexamples SeeWorking Directory (p 2)

and Sample Files (p 3) for more information

Sample files referenced by this tutorial include

bull Axialpre

bull AxialInipre

bull AxialIni_001res

bull statordef bull rotorgrd


httpslidepdfcomreaderfulltut-axial-rotor-stat-or 230

Flow in an Axial RotorStatormdashIntroduction

Page 258 CFX-5 Tutorials


12A Introduction

12A1 Features explored in this tutorial

Introduction This tutorial addresses the following features of CFX-5

Component Feature Details

CFX-Pre User Mode Turbo Wizard

Simulation Type Steady State

Transient

Fluid Type Ideal Gas

Domain Type Multiple Domain

Rotating Frame of

Reference

Turbulence Model k-Epsilon

Heat Transfer Total EnergyBoundary Conditions Inlet (Subsonic)

Outlet (Subsonic)

Wall No-Slip

Wall Adiabatic

Domain Interfaces Frozen Rotor

Periodic

Transient Rotor Stator

Timestep Physical Timescale

Transient Example

Transient Results File

CFX-Solver Manager Restart

Parallel Processing




CFX-5 Tutorials Page 259


You learn about

bull using the Turbo Wizard in CFX-Pre to quickly specify a turbomachineryapplication

bull multiple Frames of Reference and Generalised Grid Interface

bull using a Frozen Rotor interface between the rotor and stator domains

bull modifying an existing simulation

bull setting up a transient calculation

bull using a Transient Rotor-Stator interface condition to replace a Frozen

Rotor interface

bull creating a transient animation showing domain movement in CFX-Post

12A2 Before beginning this tutorial

Introduction It is necessary that you have a working directory and that

sample files have been copied to that directory This procedure is detailed

in Introduction to the CFX-5 Tutorials on page 1

Unless you review the introductory materials and perform required steps

including setting up a working directory and copying related sample files

the rest of this tutorial may not work correctly It is recommended that you

perform the tasks in Tutorial 1 Tutorial 2 and Tutorial 3 before working with

other tutorials as these three tutorials detail specific procedures that are

simplified in subsequent tutorials

CFX-Post Plots Animation

Isosurface

Surface Group

Turbo Post

Other Changing the Colour

Range

Chart Creation

Instancing Transformation

MPEG Generation

Quantitative Calculation

Timestep Selection

Transient Animation







12A3 Overview of the problem to solve

The following tutorial demonstrates the versatility of GGI and MFR in

CFX-Pre by combining two dissimilar meshes The first mesh to be imported

(the rotor) was created in CFX-TurboGrid This is combined with a second

Definition File mesh (the stator)

The geometry to be modelled consists of a single stator blade passage andtwo rotor blade passages The rotor rotates about the Z axis while the stator

is stationary Periodic boundaries are used to allow only a small section of

the full geometry to be modelled

Figure 1

At the change in reference frame between the rotor and stator twodifferent interface models are considered First a solution is obtained using

a frozen rotor model After viewing the results from this simulation the

CFX-Pre simulation is modified to use a transient rotor-stator interface

model The frozen rotor solution is used as an initial guess for the transient

rotor-stator simulation

Hub

Rotor Blade

Outflow

Shroud

Stator Blade

Inflow






The full geometry contains 60 stator blades and 113 rotor blades To help

you visualise how the modelled geometry fits into the full geometryFigure

1 on page 260 the image shows approximately half of the full geometry

The Inflow and Outflow labels show the location of the modelled section in

Figure 2 on page 261

Figure 2 The modelled geometry contains two rotor blades and one stator blade

This is an approximation to the full geometry since the ratio of rotor blades

to stator blades is close to but not exactly 21 In the stator blade passage a

6deg section is being modelled (360deg 60 blades) while in the rotor blade

passage a 6372deg section is being modelled (2360deg 113 blades) This

produces a pitch ratio at the interface between the stator and rotor of 0942

where the pitch ratio is the area of side 1 divided by the area of side 2 As the

flow crosses the interface it is scaled to allow this type of geometry to be

modelled This results in an approximation of the inflow to the rotorpassage Furthermore the flow across the interface will not appear

continuous due to the scaling applied

The periodic boundary conditions will introduce an additional

approximation since they cannot be periodic when a pitch change occurs

Inflow

Outflow

Axis of Rotation






You should always try to obtain a pitch ratio as close to 1 as possible in your

model to minimise approximations but this must be weighed against

computational resources A full machine analysis can be performed

(modelling all rotor and stator blades) which will always eliminate any pitch

change but will require significant computational time For this rotorstator

geometry a 14 machine section (28 rotor blades 15 stator blades) would

produce a pitch change of 1009 but this would require a model about 15times larger than in this tutorial example

If you have already completed the frozen rotor part of this tutorial you can

continue from Setting up the Transient Rotor-Stator Calculation (p 276)

Note that a converged results file from the frozen rotor section is required

as an initial guess You can use your own solution or use the results file

provided in the examples directory Further details are given inObtaining a

Solution to the Transient Rotor-Stator Model (p 280) You must make sure

that the boundary names used in the initial results file exactly match those

used in the transient rotor-stator case



Flow in an Axial RotorStatormdashDefining the Frozen-Rotor Simulation in CFX-Pre



12B Defining the Frozen-Rotor Simulation in

CFX-Pre

This section describes the step-by-step definition of the flow physics in

CFX-Pre If you wish you can use the session file AxialInipre to

complete this section for you and continue fromObtaining a Solution to theFrozen Rotor Simulation (p 269) See one of the first four tutorials for

instructions on how to do this

12B1 Creating a New Simulation

This tutorial will use the Turbo Wizard in CFX-Pre This pre-processing mode

is designed to simplify the setup of turbomachinery simulations

1 Start CFX-Pre

2 Select File gt New Simulation

New Simulation File appears

3 Click the Turbo icon in the area at right to highlight it

4 Browse the folders as necessary then enter the file nameAxialIni

5 Click Save

The Turbo Wizard will appear in the User Mode workspace which is

part of the general CFX-Pre workspace

12B2 Component Definition

The first step is to define the rotational axis machine type and simulation

state The names of the turbo regions for the domains will also be set

When the Turbo Wizard appears

1 Set Rotational Axis to Z

2 Leave Simulation Type set to Steady State

3 Expand the Turbo Regions frame This shows the regions that CFX-Pre attempts to automatically assign to

appropriate boundary conditions To do this it needs to know the region

names to expect in the mesh files The upper case Turbo Regions that are

selected (eg HUB) correspond to the region names in the CFX-TASCflow

ldquogrdrdquo file CFX-TASCflow turbomachinery meshes use these names

consistently The lower case Turbo Regions correspond to the region names

in the CFX-5 Definition file CFX-5 turbomachinery meshes may have






different region names than these In this case just leave the Turbo Regions

frame with its default settings you will be able to assign regions to

boundary conditions later

4 Click Next gt

12B3 Importing the Meshes

Tip While we provide a mesh to use with this tutorial you may want to

develop your own in the future Instructions on how to create this meshin CFX-Mesh are available from the CFX Community Site Please seeMesh Generation on page 3 for details

The first step is to import the two different mesh files One mesh file

contains the rotor mesh in a CFX-TASCflow ldquogrdrdquo file while the other mesh

file contains the stator in a CFX-5 Definition file

1 Copy the filesrotorgrd andstatordef located in the examples

directory (ltCFXROOTgtexamples) to your working directory

2 On the Stage Definition form click New

3 Set Name to S2 then click OK

4 Set Component Type to Stationary

5 Click to the right of Select Mesh

An Import Mesh form will appear beneath the Turbo Wizard

6 On the Import Mesh forma Set Mesh Format to CFX-5 DefRes file

b Set File to statordef

c Click OK to import the mesh

7 In the Select Mesh drop-down list ensure that Default is selected


9 Set Name to R1 then click OK

10 Set Component Type to Rotating11 Set Speed to 5236 [radian s^-1]







13 On the Import Mesh form

a Set Mesh Format to CFX-TASCflow v2

b Set File to rotorgrd


You will receive a warning message when importing this mesh The

message will tell you the information that has been ignored duringimport See CFX-TASCflow v2 on page 91 in the document CFX-Pre

for further details on this and importing CFX-TASCflow meshes

14 Click OK on the warning message to continue

15 Set Select Mesh to Assembly 3D

16 Click Next gt to continue

12B4 Creating the Interfaces

Here you will set up appropriate periodic interfaces on the rotor and stator

These are required since you are only modelling a small section of the true

geometry An interface is also required to connect the two meshes together

across the frame change See Domain Interfaces on page 299 in the

document CFX-Pre for more details

CFX-Pre will try to create appropriate interfaces using the Turbo Region

names shown earlier In this case CFX-Pre has displayed the definition of

three interfaces The following steps will verify that the interface definitions

are correct

Rotor PeriodicInterface

The first interface is named R1 to R1 Periodic

1 Click the interface to display the Interface definition

2 As expected a periodic interface has been created for the rotor domain

and the regions selected for the interface are correct

3 These are the correct settings for the periodic interface so no further

action is required

Stator PeriodicInterface

1 Click the S2 to S2 Periodic interface

2 The Interface Definition shows a periodic interface for the stator

domain showing the correct regions

3 No further action is required for this interface






Frozen RotorDomainInterface

1 Click the R1 to S2 Stage interface

2 The correct regions INFLOW and out have been selected for this

interface

3 The intention is to use a Frozen Rotor interface in this tutorial so change

Type to Frozen Rotor

Note If inappropriate interface conditions were created automatically youcan highlight and delete them using the delete icon

4 Click Next gt

12B5 General Physics

The General Physics form will now be displayed

1 In the Fluid drop-down list select Air Ideal Gas

2 Under Model Data

a Set Reference Pressure to 025 [bar]

Note the change in units from Pa to bar

b Leave Heat Transfer set to Total Energy

c Leave Turbulence set to k-Epsilon (scalable wall function)

3 Under Solver Parameters

a Leave Advection Scheme set to High Resolution

b Set Convergence Control to Physical Timescale and PhysicalTimescale to 0002 [s]

This timescale is approximately equal to 1 ω which is often

appropriate for rotating machinery applications


12B6 Boundary Definition

CFX-Pre will now try to create appropriate boundary conditions using the

Turbo Region names shown earlier The Boundary Definition form willappear showing a list of boundary conditions These were automatically

created and can be viewed edited and deleted in the same way as the

interface connections that were set up earlier

Setting theStator InletBoundaryCondition

1 Click Inlet

Location and Boundary Type are both correct so there is no need to

change these settings






2 Under Flow Specification set Option to Stationary Frame Total

Pressure and Relative Pressure to 0 [Pa]

3 Leave Flow Direction set to Normal to Boundary

4 Set Total Temperature to 340 [K]

To set therotor outletboundarycondition

1 Click OutletLocation and Boundary Type are both correct so there is no need to


2 Under Flow Specification set Option to Mass Flow Rate and Mass

Flow Rate to 006 [kg s^-1]

Checking theRotor BladeBoundaryCondition

Click Blade a wall boundary specified on the BLADE region Note that all of

the details are correct for this boundary condition

Wall boundary conditions are created relative to the local domain reference

frame by default so this boundary is stationary relative to the rotatingdomain (ie rotating relative to the stationary domain)

Checking theRotor HubBoundaryCondition

Click Hubawallboundaryonthe HUB region Note that all of the details are

correct for this boundary condition

Checking theRotor ShroudBoundary

Condition

Click Shroud a wall boundary on the SHROUD region Note that all of the

details are correct for this boundary condition

Checking theRemainingBoundaries

1 Click on the boundaries Blade 2 Hub 2 and Shroud 2 Wall boundaries

will be shown on the regions blade hub and shroud respectively and

need no editing

Note If inappropriate boundary conditions are created by CFX-Pre or aremissing you can delete and add them as appropriate







12B7 File Definition Options

The last form offers the following three options

bull Enter General Mode

bull Start Solver Write the Solver (def) File enter General Mode and start

the CFX-Solver

bull Start Solver and Quit Write the Solver (def) File start the CFX-Solverand quit CFX-Pre

1 Select Start Solver and Quit then click Finish

2 Answer Yes when asked if you want to save the CFX file



Flow in an Axial RotorStatormdashObtaining a Solution to the Frozen Rotor Simulation



12C Obtaining a Solution to the Frozen Rotor

Simulation

Compared to previous tutorials the mesh for this tutorial contains many

more nodes (although it is still too coarse to perform a high quality CFD

simulation) This results in a corresponding increase in solution time for theproblem We recommend solving this problem in parallel It is

recommended that your machine has a minimum of 256MB of memory to

run this tutorial

Note If you do not have a license to run CFX-5 in parallel you can run inserial by clicking the Start Run button when CFX-Solver Manager has

opened up Solution time in serial is approximately 45 minutes on a 1GHzprocessor

Instructions are provided below to run this tutorial in parallel More detailedinformation about setting up CFX-5 to run in parallel is provided in Flow

Arounda Blunt Body on page 123 and in Setting Up and Running a Parallel

Run on page 45 in the document CFX- Solver Manager

You can solve this example using either Local Parallel or Distributed Parallel

as guidance is provided for both

Solving UsingLocal Parallel

To run in Local Parallel the machine you are on must have more than one

processor

1 On the Define Run form set Run Mode to PVM Local Parallel (this isthe recommended method for most applications see Run Mode on

page 12 in the document CFX- Solver Manager for details on the other

options)

2 By default 2 partitions are assigned Click Add Partition to add

more partitions

3 Click Start Run

During convergence data is written to an out file for each equation in

each fluid domain separately

When the Solver has finished

4 Click Post-Process Results

5 When Start CFX-Post appears turn on Shut down Solver Manager

then click OK






Solving UsingDistributedParallel

1 On the Define Run form set Run Mode to PVM Distributed Parallel

1 partition should already be assigned to the host that you are logged

into

2 Click Select Host to specify a new parallel host

3 In Select Parallel Hosts select another Host Name (this should be a

machine that you can log into using the same user name)

4 Click Add then Close

The names of the two selected machines should be listed in the Host

Name column of the Define Run form

5 Click Start Run

Notice that the pitch ratio is written near the start of the OUT file for a

parallel run

+--------------------------------------------------------------------+

| Total Number of Nodes Elements and Faces |+--------------------------------------------------------------------+Domain Interface Name Auto Interface 3

Non-overlap area fraction on side 1 = 00Non-overlap area fraction on side 2 = 01Area based pitch ratio (6372 leg 6000 leg) = 1062






then click OK



Flow in an Axial RotorStatormdashViewing the Results



12D Viewing the Results

The Turbo-Post feature will be demonstrated in the following sections This

feature is designed to greatly reduce the effort taken to post-process

turbomachinery simulations A number of turbo-specific features are also

available see CFX-Post Turbo Menu on page 171 in the document

CFX-Post for more details

Initialising Turbo-Post

To initialise Turbo-Post the properties of each componentmustbe entered

This includes entering information about the inlet outlet hub shroud

blade and periodic regions

1 Select Turbo gt Turbo Mode from the main menu

The Turbo tab is automatically selected and shows the two components in

domains R1 and S2 In the next step both of these components will be

initialised1 Double-click Component 2

2 Under Definition set

a Hub to Hub

b Shroud to Shroud

c Blade to Blade

d Inlet to R1 to S2 Stage Side R1 Part 1

This is the rotor side of the frozen rotor interface so it is the inlet to

the rotor domain

e Outlet to Outlet

f R1 to R1 Periodic Side R1 Part 1

g R1 to R1 Periodic Side R1 Part 2

3 Click the Instancing tab then under Rotation you will see that the

Angle From is set to Instances in 360 the of Passages is set to 113

and the PassagesComponent is set to 2 These settings are correct for

this component4 Click Apply

5 Double-click Component 1







a Hub to Hub 2

b Shroud to Shroud 2

c Blade to Blade 2

d Inlet to Inlet

e Outlet to R1 to S2 Stage Side S2 Part 2 This is the stator side of the Frozen Rotor interface so it is the outlet

from the stator domain

f Periodic 1 to S2 to S2 Periodic Side S2 Part 1

g Periodic 2 to S2 to S2 Periodic Side S2 Part 2

7 Click the Instancing tab where you will see that Angle From is set to

Instances in 360 of Passages is 60 and PassagesComponent is 1

These are all correct for this component

8 Click Apply

Colouring aSurface of Constant Span

1 Open the Turbo Plotter by selecting Turbo gt Turbo Plotter from the

main menu

2 Click the Run Initial Setup button (located at the bottom right of the

Turbo Plotter form)

bull Three objects are created in separate viewports when the Initial

Setup option is chosen Turbo 3D view 2D Blade-to-Blade view and

2D Meridional view

bull In this case the meridional turbo surface will obscure part of the

plots you will be creating in the next steps

3 In the Object Selector turn off the visibility for theTurbo Plotter Merid

Surface






One of the default objects created when you ran the initial setup is a

blade-to-blade turbo surface drawn at a spanwise location of 05 (halfway

between the hub and shroud) For an explanation of turbo locations please

see Turbo Measurements on page 187 in the document CFX-Post Here

you will colour the surface with pressure

1 In the Object Selector right-click the Turbo Plotter B2B Surface and

select Edit

2 Click the Colour tab and set

a Mode to Variable

b Variable to Pressure

c Range to Global

3 Click Apply

Viewing 3

domainpassages

Next you will create an instancing transformation to plot three blade

passages for the stator and six blade passages for the rotor

The instancing properties of each domain have already been entered

during Initialisation In the next steps you will create a surface group plot

(see Surface Group on page 94 in the document CFX-Post) to colour the

blade and hub surfaces with the same variable The number of instances of

for each domain will then be changed

1 Use the Object Selector to make all objects invisible

2 Select Create gt Object gt Surface Group from the main menu

3 Accept the default name and click OK

4 Set Locations to Hub Hub 2 Blade and Blade 2(use the icon to

open the Locations Selector)

5 On the Colour panel set Mode to Variable and Variable to Pressure

6 Click Apply

7 In the Turbo Plotter make sure Plot is set to Turbo 3D View

8 Under Instancing set of Copies for the R1 domain to 3

9 Click Apply






10 Carry out the same step for the S2 domain

Creating aBlade LoadingChart

In this section you will create a plot of pressure around the stator blade at a

given spanwise location For more details on this functionality please see

Turbo Plotter Turbo Chart on page 192 in the document CFX-Post

1 In the Turbo Plotter set

a Plot to Turbo Chart

b Type to Blade Loading

c Domain to S2

d Span to 05e X Variable to Z

f Y Variable to Pressure






2 Click Apply

A turbo line is automatically created in the viewer to show where

pressure values have been sampled

The profile of the pressure curve is typical in turbomachinery applications

This completes the frozen-rotor part of the tutorial The next section

describes how to use the solution to set up a transient rotor-stator

calculation



Flow in an Axial RotorStatormdashSetting up the Transient Rotor-Stator Calculation



12E Setting up the Transient Rotor-Stator

Calculation


CFX-Pre The existing frozen-rotor simulation is modified to define the

transient rotor-stator simulation If you wish you can use the session fileAxialpre to complete this section for you and continue fromObtaining

a Solution to the Transient Rotor-Stator Model (p 280) See one of the first

four tutorials for instructions on how to do this

Note The session file creates a newsimulation namedAxialcfx and willnot modify the existing database It also copies the required initial values

files from the examples directory to the current working directory

12E1 Opening the Existing Simulation

This step involves opening the original simulation and saving it to a

different location

1 Start CFX-Pre and select File gt Open Simulation

2 Select the original simulation fileAxialIni_001res

bull You will need to change the import filter to showdef and

res files

bull If you have not completed the first part of the tutorial this file can

be copied from the examples directory

3 Select File gt Save Simulation As

4 Enter Axial and click OK

The simulation will open in General Mode The Turbo-Pre Wizard can be

used to quickly create turbomachinery cases but General Mode is always

used when re-opening a simulation






12E2 Modifying the Simulation Type

You need to modify the domain to define a transient simulation You are

going to run for a time interval such that the rotor blades pass through 1

pitch (6372o) using 10 timesteps This is generally too few timesteps to

obtain high quality results but is sufficient for tutorial purposes The

timestep size is calculated as followsRotational Speed = 5236 radsRotor Pitch Modelled = 2(2π113) = 01112 radTime to pass through 1 pitch = 011125236 = 2124e-4 s

Since 10 timesteps are going to be used over this interval then each

timestep should be 2124e-5s

1 Select Create gt Flow Objects gt Simulation Type from the main menu

2 On the Basic Settings panel set Option to Transient

3 Under Time Duration

a Set Option to Total Time and Total Time to 2124e-4 [s]

This gives 10 timesteps of 2124e-5 s

b Set Timesteps to 2124e-5 and leave the units set to [s]

This timestep will be used until the total time is reached

4 Under Initial Time set Option to Automatic with Value and Time to

0 [s]

5 Click OK

Note A transient rotor-stator calculation often runs through more than onepitch In these cases it may be useful to look at variable data averaged overthe time interval required to complete 1 pitch You can then compare datafor each pitch rotation to see if a ldquosteady staterdquo has been achieved or if theflow is still developing See Using Statistics with Transient Rotor-StatorCases on page 335 in the document CFX-Pre for details on how to get

time averaged variable data

12E3 Modifying the Domain Interface

1 In the Physics Workspace double click R1 to S2 Stage

2 Under FrameChange set Option to Transient RotorStatorthenclick

OK






12E4 Setting Initial Values

When defining a simulation using the Turbo Wizard initial values are not set

since the default is Automatic for all variables When the Simulation Type

waschanged to Transient CFX-Pre signalled a Physics Validation error since

initial values are required for all transient runs The initial values must either

be specified or provided by selecting an Initial Values File in the CFX-SolverManager when defining the run In this tutorial the solution from the Frozen

Rotor simulation will be used as the Initial Values File

Ignoring the Physics Validation warning andlater specifying an initial values

file in the CFX-Solver would still allow the problem to run (because the

CFX-Solverwould still attempt to run the simulation with Automaticvalues)

but in this tutorial the values will be explicitly set to Automatic to remove

the Physics Validation warning

1 Click Global Initialisation

2 Change all of the options that are currently set to Automatic with

Value to Automatic

3 Turn on Turbulence Eddy Dissipation and set Option to Automatic

4 Click OK

12E5 Modifying the Solver Control

1 Click Solver Control

2 Set Max Iter Per Timestep to 3

We do not generally recommend using a large number of iterations per

timestep see Transient Timestep Control on page 352 in the

document CFX-5 Solver Modelling for details

3 Click OK to set the solver parameters

12E6 Creating Transient Results Files

1 Click Output Control

2 Click the Transient Results tab

3 Click Add new item and then click OK to accept the default name

for the object

4 Leave Option set to Minimal






5 Set Output Variable List to Pressure Velocity and Velocity in Stn

Frame (use the ltCtrlgt key to select more than one variable)

Note Velocity is always defined in the local reference frame so it will givethe rotating frame velocity in the rotor component

6 Turn on Time Interval and set Time Interval to 2124e-5 [s]

7 Click OK

12E7 Writing the Solver (def) File

1 Click Create Definition File

2 Set File name to Axialdef

3 Leave Operation set to Start Solver Manager with def file

4 Turn on Report Summary of Interface Connections

5 Click OK

The Information window shows that the fluid-fluid interface is GGI and

the two periodic interfaces are one-to-one

6 Click OK in the information window

7 Select File gt Quit

8 Click Yes when asked if you want to save the CFX file



Flow in an Axial RotorStatormdashObtaining a Solution to the Transient Rotor-Stator Model



12F Obtaining a Solution to the Transient

Rotor-Stator Model

When the CFX-Solver Manager has started you will need to specify an Initial

Values File before starting the CFX-Solver Set Initial Values File to

AxialIni_001res (the Frozen Rotor solution)

12F1 Serial Solution

If you do not have a license or do not want to run CFX-5 in parallel you can

runin serial by clicking the StartRun button Solution time in serial is similar

to the first part of this tutorial

12F2 Parallel Solution


in the same way as in the first part of this tutorial See Obtaining a Solution

to the Frozen Rotor Simulation (p 269) if you need further guidance

12F3 Monitoring the Run

During the solution look for the additional information that is provided for

transient rotor-stator runs Each time the rotor is rotated to its next position

the number of degrees of rotation and the fraction of a pitch moved is

given You should see that after 10 timesteps the rotor has been movedthrough 1 pitch

You will notice a jump in the residuals (to the order of 10E-2) for every

timestep This is to be expected for a transient simulation under these

conditions which in the interest of time has a large timestep You will also

notice that the problem does not converge to the convergence criteria in a

single timestep and for accurate results reaching the convergence criteria

is very important Convergence is achieved by adjusting the length of the

timestep to an appropriate valueTransient Timestep Control on page 352

in the document CFX-5 Solver Modelling




then click OK






12G Viewing the Results

To examine the transient interaction between the rotor and stator you are

going to create a blade-to-blade animation of pressure A turbo surface will

be used as the basis for this plot


To initialise Turbo-post the properties of each domain must be entered This includes entering information about the inlet outlet hub shroud

blade and periodic regions The instancing properties are set on the

Instancing tab menu

1 Select Turbo gt Turbo Mode from the main menu bar



initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet





and the PassagesComponent issetto2 These settings are correct for

this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply

9 As for the initial axial case the meridionalturbo surface will obscure part

of the plots you will be creating in the next steps In the Object Selector

uncheck the visibility for the Turbo Plotter Merid Surface

Creating a Turbo SurfaceMidwayBetween the

Hub andShroud

1 Click View Toward -X (by using the viewer icon drop-down menu)

and zoom in so that the geometry fills the Viewer

2 Make all existing plots invisible

3 Select Turbo gt Turbo Surface from the main menu bar

4 On the Geometry panel set

a Domains to All Domains

b Method to Constant Span

Constant span specifies a fractional distance from the hub (0) to the

shroud (1) In this case a plot is created at 05 (halfway between hub

and shroud) See Turbo Measurements on page 187 in the

document CFX-Post for more detailsc Value to 05






5 On the Colour panel set

a Mode to Variable


c Range to User Specified

d Min to -12000 [Pa]

e Max to -8000 [Pa]6 Click Apply to create the turbo surface

Setting upInstancing Transformations

Next you will use instancing transformations to view a larger section of the

model The properties for each domain have already been entered during

the initialisation phase so only the number of instances needs to be set

1 In the Turbo Plotter make sure that Plot is set to Turbo 3D View

2 In the Instancing section of the form set of Copies for both domains

to 6 (For each domain click Apply after you set of Copies)

Creating a TransientAnimation

Start by loading the first timestep

1 Click Show Timestep Selector

2 Select Time Value 0

3 Click Apply to load the timestep

The rotor blades move to their starting position This is exactly 1 pitch

from the previous position so the blades will not appear to move

4 Turn off visibility for the Wireframe object






5 Position the geometry as shown below ready for the animation During

the animation the rotor blades will move to the right Make sure you

have at least two rotor blades out of view to the left side of the Viewer

They will come into view during the animation

6 Click Show Animation Editor

7 In Animation Editor click New

8 Use the Timestep Selector to load Time Value 00002124

9 In the Animation Editor click New to create KeyframeNo2

10 Highlight KeyframeNo1 then set of Frames to 9

11 Click Options and set Timestep to TimeValue Interpolation

Playing theAnimation

The animation now contains a total of 11 frames (9 intermediate frames plus

the two Keyframes) one for each of the available time values

1 On the Animation Editor form turn on Save Animation Movie

2 Click Browse nexttothe MPEG File box and then set File name to

an appropriate file name (ending inmpg)

3 If Frame 1 is not loaded (shown in the top right corner of the Animation

Editor) click To Beginning to load itWait for CFX-Post to finish loading the objects for this frame before

proceeding

4 Click Play Forward

bull It takes a while for the animation to complete

bull To view the MPEG file you will need to use a media player that

supports the MPEG format






You will be able to see from the animation and from the plots created

previously that the flow is not continuous across the interface

This is because a pitch change occurs The relatively coarse mesh and the

small number of timesteps used in the transient simulation also contribute

to this The movie was created with a narrow pressure range compared to

the global range which exaggerates the differences across the interface

FurtherPostprocessing

You can use the Turbo Calculator to produce a report on the performance

of the turbine

1 Select Turbo gt Turbo Calculator from the main menu bar

2 Set Macro to Gas Turbine Performance

3 Set Ref Radius to 04575 and leave other settings at their default

values

4 Click Calculate

5 Click View Report

The values calculated are defined inPredefined Macros on page 158 in the

document CFX-Post

Next TutorialPrevious Tutorial








58 CFX-5 Tutorials


12A Introduction

12A1 Features explored in this tutorial

Introduction This tutorial addresses the following features of CFX-5


CFX-Pre User Mode Turbo Wizard

Simulation Type Steady State

Transient

Fluid Type Ideal Gas

Domain Type Multiple Domain

Rotating Frame of

Reference

Turbulence Model k-Epsilon

Heat Transfer Total EnergyBoundary Conditions Inlet (Subsonic)

Outlet (Subsonic)

Wall No-Slip

Wall Adiabatic

Domain Interfaces Frozen Rotor

Periodic

Transient Rotor Stator

Timestep Physical Timescale

Transient Example

Transient Results File

CFX-Solver Manager Restart

Parallel Processing






You learn about







Rotor interface













Isosurface

Surface Group

Turbo Post


Range

Chart Creation


MPEG Generation


Timestep Selection

Transient Animation















Figure 1






Hub

Rotor Blade

Outflow

Shroud

Stator Blade

Inflow























Inflow

Outflow

Axis of Rotation



























CFX-Pre








1 Start CFX-Pre





5 Click Save
























4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post











You learn about







Rotor interface













Isosurface

Surface Group

Turbo Post


Range

Chart Creation


MPEG Generation


Timestep Selection

Transient Animation















Figure 1






Hub

Rotor Blade

Outflow

Shroud

Stator Blade

Inflow























Inflow

Outflow

Axis of Rotation



























CFX-Pre








1 Start CFX-Pre





5 Click Save
























4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post



















Figure 1






Hub

Rotor Blade

Outflow

Shroud

Stator Blade

Inflow























Inflow

Outflow

Axis of Rotation



























CFX-Pre








1 Start CFX-Pre





5 Click Save
























4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post




























Inflow

Outflow

Axis of Rotation



























CFX-Pre








1 Start CFX-Pre





5 Click Save
























4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post
































CFX-Pre








1 Start CFX-Pre





5 Click Save
























4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post














4 Click Next gt














































are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post






























are correct







action is required














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post














interface




4 Click Next gt




2 Under Model Data

















1 Click Inlet


























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post





























Condition






need no editing












the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post















the CFX-Solver










Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












Simulation





run this tutorial










processor



options)


more partitions

3 Click Start Run






then click OK









into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post














into







5 Click Start Run


parallel run

+--------------------------------------------------------------------+








then click OK





















a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post


























a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet














a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply



main menu


Turbo Plotter form)



2D Meridional view




Surface












select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post

















select Edit


a Mode to Variable


c Range to Global

3 Click Apply

Viewing 3

domainpassages














6 Click Apply



9 Click Apply














c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post



















c Domain to S2








2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post











2 Click Apply






calculation







Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












Calculation










different location




res files





























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post



























0 [s]

5 Click OK






OK




















Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post

























Value to Automatic


4 Click OK












for the object











7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post















7 Click OK






5 Click OK












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












Rotor-Stator Model




























then click OK













Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post


















Instancing tab menu




initialised



a Hub to Hub

b Shroud to Shroud

c Blade to Blade



the rotor domain

e Outlet to Outlet






this component

4 Click Apply








a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












a Hub to Hub 2


c Blade to Blade 2

d Inlet to Inlet








8 Click Apply





Hub andShroud


















a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post












a Mode to Variable











































proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post









4 CFX-5 Tutorials




















proceeding


















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post



















of the turbine




values

4 Click Calculate

5 Click View Report


document CFX-Post






tut axial rotor stat or

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