center for turbomachinery and propulsion research · center for turbomachinery and propulsion...

Center for Turbomachinery

and Propulsion Research

Providing Research and Educational Programs in Turbomachinery and

Propulsion Science and Engineering

Table of ContentsTable of ContentsTable of ContentsTable of Contents Table of ContentsTable of ContentsTable of ContentsTable of Contents

CENTER FOR TURBOMACHCENTER FOR TURBOMACHCENTER FOR TURBOMACHCENTER FOR TURBOMACHINERY AND INERY AND INERY AND INERY AND PROPULSION RESEARCH PROPULSION RESEARCH PROPULSION RESEARCH PROPULSION RESEARCH

1. Introduction 1

2. Recent and On-Going Projects

• Acoustics and Active Control 2

• Combustion and Active Control 3 - 4

• Aerodynamics and Heat Transfer 5 - 11

• Rocket Propulsion 12 - 13

• Instrumentation and Sensor Development 14 - 16

• Rotor Dynamics and Magnetic Bearings 17 - 18

3. Participating Faculty Members 19 - 25

4. Facilities 26

5. Sponsors 27

1

Introduction

The program of turbomachinery and propulsion research at Vir-

ginia Tech has provided research and educational service to indus-

try and government agencies for more than thirty years. Beginning

with the development of high-response instrumentation for on-

rotor pressure measurements in 1971, the program has expanded

dramatically. Research is conducted on a wide variety of turbo-

machinery fluid

mechanics topics including:

• Development of computational techniques for calculation of

turbomachinery flows

• Research on sensors for flow and heat transfer measurements

• Measurement and prediction of rotor dynamics

• Blade vibration and seal performance

• Large-scale aero and thermal measurements

• Ramjet and rocket combustion

• Optimization techniques for turbomachinery applications

The Center is organized to support and enhance the research ef-

forts of faculty and to provide increased research and educational

services. The faculty members pursue a comprehensive program

of relevant, fundamental research in the turbomachinery, gas tur-

bine, and propulsion fields. In addition to individually sponsored

programs, the Center acts as a focal point for cooperative re-

search efforts between faculty and affiliate sponsors. The Center

promotes effective communica-tion between the two, and seeks to

encourage relevant activities. It works to support quality educa-

tion of graduate students in the turbomachinery and propulsion

areas.

Control of Inlet Noise from Turbofan Engines Using Herschel-

Qenke Waveguide Resonator,

Ricardo A. Burdisso

An innovative implementation of the Herschel-Quincke waveguides

(or tubes) concept for the reduction of tonal and broadband noise

from a turbofan engine is experimentally investigated. The

Herschel-Quincke tube con-

cept, applied to turbofan en-

gines, consists of installing

circumferential arrays of tubes

around the inlet of the turbo-

fan engine. The experimental

work is carried out on a Pratt

and Whitney JT15D turbofan

jet engine. Single and multi-

ple circumferential arrays of

Herschel-Quincke tubes are

mounted around the inlet of the engine, and their effects on the

radiated noise are measured and oompared to the hard-walled

inlet case. The results on the JT15D

turbofan engine show reductions exceeding 8 dB in the blade pas-

sage frequency tone sound power levels. Experimental results also

show that the Herschel-Quincke technique is also very effective at

reducing the turbofan inlet broadband noise with sound power

reduction of up to 3 dB in the 0-3200 Hz frequency range.

JTI5D turbofan for engine experiments

Acoustic and Active Control

2

Acoustic Characterization and Modeling of Gas Turbine Acoustic Characterization and Modeling of Gas Turbine Acoustic Characterization and Modeling of Gas Turbine Acoustic Characterization and Modeling of Gas Turbine FlowtrainsFlowtrainsFlowtrainsFlowtrains, R.L. West, Uri VandsburgerR.L. West, Uri VandsburgerR.L. West, Uri VandsburgerR.L. West, Uri Vandsburger Methodologies have been developed for characterization of the

acoustic field in flow trains and combustors. These have been applied to lab development and industrial model combustors. In parallel acoustic modeling of the flow trains was undertaken using FEA. The ABAQUS package was utilized since it can handle complex boundary conditions. This code can and will be coupled with a CFD solver like FLUENT.

Characterization of ThermoCharacterization of ThermoCharacterization of ThermoCharacterization of Thermo----Acoustic Instabilities in LeanAcoustic Instabilities in LeanAcoustic Instabilities in LeanAcoustic Instabilities in Lean----Premixed Combustion Uri Vandsburger, Premixed Combustion Uri Vandsburger, Premixed Combustion Uri Vandsburger, Premixed Combustion Uri Vandsburger, R.L. WestR.L. WestR.L. WestR.L. West The dynamics, thermo acoustic instabilities, of Lean Premixed Combustion systems are studied experimentally. The diagnos-tic techniques include microphones, hot wire anemometers, chemiluminescence, laser absorption. The data acquired, in the form of FRF are combined with the acoustic characteriza-tion to obtain the closed loop behavior, and to test models de-veloped.

Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-stabilities prediction, stabilities prediction, stabilities prediction, stabilities prediction, Uri Vandsburger, R.L. WestUri Vandsburger, R.L. WestUri Vandsburger, R.L. WestUri Vandsburger, R.L. West The effort aims at providing models for design engineers to pre-dict the stability of their, LP, combustion system, with the usage of full reacting CFD.

Combustion chamber

for thermoacoustic

characterization

Combustion and Active Control

3

Development of active fuel nozzles for Active Combustion Development of active fuel nozzles for Active Combustion Development of active fuel nozzles for Active Combustion Development of active fuel nozzles for Active Combustion Control of Lean Direct Injections (LDI) Combustors, Control of Lean Direct Injections (LDI) Combustors, Control of Lean Direct Injections (LDI) Combustors, Control of Lean Direct Injections (LDI) Combustors, Uri Uri Uri Uri VandsburgerVandsburgerVandsburgerVandsburger The project aims at the development of active spray nozzles for ACC (Active Combustion Control) systems for LDI combustors. Nozzle requirements are 40% mass fluctuations, and a band-width of 1KHz. Joint project with PSU who will provide the spray transfer function

Conversion of PT6Conversion of PT6Conversion of PT6Conversion of PT6----20 turboprop engine from JetA to LP 20 turboprop engine from JetA to LP 20 turboprop engine from JetA to LP 20 turboprop engine from JetA to LP hydrogenhydrogenhydrogenhydrogen----air operation, air operation, air operation, air operation, Walter O’Brien, Uri VandsburgerWalter O’Brien, Uri VandsburgerWalter O’Brien, Uri VandsburgerWalter O’Brien, Uri Vandsburger Hydrogen Enriched Combustion of Low BTU Fuels, Uri Vandsburger Studies of various renewable, non-fossil, fuels combustion are con-ducted. The fuels are being burned in the lean-premixed (LP) mode to minimize pollutants formation. The study focuses on generated a data base for properties like flame speed, and flammability limits. This information is need to design stable burners/combustors.

Studies of Liquid Sprays in Cross Flow, Studies of Liquid Sprays in Cross Flow, Studies of Liquid Sprays in Cross Flow, Studies of Liquid Sprays in Cross Flow, Uri VansburgerUri VansburgerUri VansburgerUri Vansburger Atomization and spray evolution of a liquid jet in cross flow are meas-ured. The jets of water and Jet A are injected into a cross flow of air at 900˚F and 150m/sec. The memento ratio is varied between 12 and 36. Effect of geometric variations are examined too. The spray characteristics are measured with a PDA system. Attempts to use a DPVV system however the signal was too noisy.

Particulate deposition on turbine blades leading edge, Particulate deposition on turbine blades leading edge, Particulate deposition on turbine blades leading edge, Particulate deposition on turbine blades leading edge, Uri Uri Uri Uri Vandsburger, Danesh Tafti, and Wing NgVandsburger, Danesh Tafti, and Wing NgVandsburger, Danesh Tafti, and Wing NgVandsburger, Danesh Tafti, and Wing Ng The project addresses the interaction of particulate laden flows and gas turbine components. The particulate stem from pro-duction of synthesis gas from coal using various devices, e.g., a fluidized bed. The specific aspect of the project is interaction between the particles and film cooling holes in the frontal area of blades and varies. The project involves CFD models develop-ment and their verification. The latter involves complex experi-ments involving Teflon particles in a hot air flow, 700F and 150m/S.


4

5

Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-

lar Combustors lar Combustors lar Combustors lar Combustors , Srinath V. Ekkad and Danesh Tafti Srinath V. Ekkad and Danesh Tafti Srinath V. Ekkad and Danesh Tafti Srinath V. Ekkad and Danesh Tafti

Research will focus on the interaction between the hot swirling gases and the liner wall within a gas tur-bine combustor. Improved understanding of the heat transfer process from the gases to the combustor liner is critical with the re-duction of direct film cool-ing of the liner. Thus more accurate local quantification of the heat transfer rates will allow more effective cooling on the backside of the combustor liner. Modern DLE combustors are characterized by highly swirling and expanding flows that make convective heat load on the gas side very difficult to predict or estimate. Present methodology is based on peak heat load (quantified based on the peak combustion temperature) rather than local near wall conditions. This conservative approach re-quires very high cooling rates on the wall, thus requiring compli-cated cooling designs and high coolant flow rates. Annular combustors are significantly different in design than can com-bustors as there is no boundary in the transverse direction for flow expansion for these types of combustors.


6

Backside Cooling of Gas Turbine Combustor Liners, Backside Cooling of Gas Turbine Combustor Liners, Backside Cooling of Gas Turbine Combustor Liners, Backside Cooling of Gas Turbine Combustor Liners, Sri-Sri-Sri-Sri-nath V. Ekkadnath V. Ekkadnath V. Ekkadnath V. Ekkad This study, with Solar Turbines, Inc. based in San Diego, focuses on

improved combustion liner cooling. The modern lean premixed low

NOx combustor injectors produce a highly swirling and expanding

flow, so the convective heat load estimate in the gas side becomes a

daunting task. The combustors are so designed to reduce the NOx

emissions but the design produces increased heat load that ad-

versely affects the life of the components.

The life and performance of the combustor

depends on adequate cooling to the liner

walls. In older design, the cooling technique

utilized combustion dilution air and film cool-

ing of various types to achieve reasonable

liner temperatures. In low NOx combustors,

film cooling is not an option. So, there is a

need to design advanced cooling techniques,

which are a combination of traditional tech-

niques as in rib turbulators, impingement,

pin fins, and TBC coatings. In the present

study, we focus on various combined tech-

niques to achieve high cooling efficiency that

will help in reducing liner temperatures, re-

sulting in cooled liners without using film

cooling and thus reducing NOx emissions.


Advanced Film Cooling Hole Geometry Study, Advanced Film Cooling Hole Geometry Study, Advanced Film Cooling Hole Geometry Study, Advanced Film Cooling Hole Geometry Study, Srinath V. Srinath V. Srinath V. Srinath V.

EkkadEkkadEkkadEkkad

Film cooling is used extensively in gas turbine hot

gas path components to protect the surfaces from

being exposed to high temperature combustion

gases. Typically, bleed air from the compressor is

routed under the hot gas path and injected through

the surface from discrete holes to form a protective

film of cooler air, hence called film cooling. As

turbine inlet temperatures rise, the amount of avail-

able coolant is limited and cooling efficiency has

become an critical issue. In an attempt to enhance

cooling efficiency, new cooling hole designs have been investigated.

Three different cooling designs are proposed: Trenched holes where the

cylindrical holes are embedded in 2-dimensional trenches to simulate slot

exits; Cratered holes where the cylindrical holes are embedded in 3-

dimensional craters to reduce upward momentum; and lastly the anti-

vortex geometry where the main holes also feed two smaller side holes to

generate anti-vortices that reduces jet lift-off and improve cooling effec-

tiveness. All the above designs have been tested on a flat plate in a low

speed wind tunnel. Geometrical variations such as trench width and

depth, crater depth and crater-to-hole exit location, anti-vortex pair hole

size and location have been investigated.

Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors, Wing Wing Wing Wing

F. NgF. NgF. NgF. Ng

The perturbation effects of “as manufactured” gas turbine compres-sor blades can have a detrimental effect on engine performance. Statistical techniques, such as Principal Component Analysis, are used to determine the most common manufacturing perturbations and the descriptive parameters that define these perturbations. Nu-merical and experimental studies are then employed to quantify the effects of manufacturing perturbations, where experimental and

numerical data is obtained via 2-D cascades.

Aerodynamics and Heat Trans-

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Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,

Wing F. Ng

A two dimensional, transonic, linear cascade tunnel is used for compres-

sor aerodynamic research. Freestream turbulence intensity can vary

from 0.5% to 5% by the addition of a turbulence grid upstream. Loss

measurements have been taken for a variety of compressor stator blades.

In addition, the use of flow control to reduce losses is also investigated.


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Heat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine Blades,

Wing F. Ng A two dimensional transonic turbine cascade is used to study the heat

transfer to turbine blades and vanes. Time-resolved surface heat transfer

measurements are made by heating the inlet air and using thin film heat

flux gauges to measure corresponding changes in surface temperature.

The thin film heat flux gauges allow for high frequency response and

high spatial resolution measurements (we can measure heat flux at ap-

proximately 30 locations depending on blade size). Additionally, velocity

and pressure measurements are made up and downstream of the cascade,

as well as on the surface of the blades. The effects of film cooling,

freestream turbulence and exit Mach number on the transfer of heat to the

blades and vanes are studied. A turbulence generator, which can vary the

turbulence intensity up to 15%, is used to simulate engine combustor exit

conditions.

8

Active Flow Control for HighActive Flow Control for HighActive Flow Control for HighActive Flow Control for High----Cycle Fatigue Reduction,Cycle Fatigue Reduction,Cycle Fatigue Reduction,Cycle Fatigue Reduction,

Wing F. Ng and Ricardo A. Burdisso

The high-cycle-fatigue (HCF) of com-

pressor components is due to blade

vibration and the accumulated dam-

age of the fatigue stress cycle. One

major source of such fatigue stress

cycles is the forced response of the

blade from unsteady aerodynamic exci-

tation. In particular, the unsteady ef-

fect on the rotor blade loading due to

the movement of the rotor through disturbances from the stationary

wake of an upstream stator or inlet guide vane (IGV) has been shown

to have a major effect on the HCF of compressor blades and the first

stage fan rotor.

Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet, Wing F. Ng and Wing F. Ng and Wing F. Ng and Wing F. Ng and

Ricardo A. Burdisso Ricardo A. Burdisso Ricardo A. Burdisso Ricardo A. Burdisso

An innovative method to reduce inlet distortion and improve the

performance of propulsion systems in unmanned air vehicles is

investigated. These vehicles (as well as other tactical aircraft) use

serpentine inlets to improve the stealth characteristics of the aircraft.

Unfortunately, these serpentine ducts cause flow separation and in-

crease the distortion at the engine reducing its stability and perform-

ance. In this research program, fluidic actuators will be used for

active flow control to prevent flow separation in serpentine gas tur-

bine inlet ducts. These fluidic actuators operated by bleeding high-

pressure air from the engine, will provide boundary layer suction and

blowing near the separation-prone areas in the inlet. Non-intrusive

microphones mounted on the internal surface of the inlet to detect

separated flow will be used to provide error signals for the controller.


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Blade surface flow visualiza-

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Operating on hydrocarbons, a

plasma torch produces a

bright, luminous combustion

plume in a M=2.4 crossflow

10

AxialAxialAxialAxial----Compressor Response to NonCompressor Response to NonCompressor Response to NonCompressor Response to Non----Uniform Flow,Uniform Flow,Uniform Flow,Uniform Flow,

Walter F. O’Brien

An experimentally-derived technique for predicting the behavior of

axial- flow compressors operating with circumferential non-uniform

inlet flow is currently under development. The technique relies on cap-

turing unsteady blade- row flow phenomena with frequency

domain transfer functions. The stage-to-stage transfer of flow distor-

tion and the resulting first stage rotor blade forced response is included.

Ignition, Flameholding and Combustion Enhancement Ignition, Flameholding and Combustion Enhancement Ignition, Flameholding and Combustion Enhancement Ignition, Flameholding and Combustion Enhancement

System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,

Walter F. O’BrienWalter F. O’BrienWalter F. O’BrienWalter F. O’Brien

Initiating and sustaining combustion in supersonic flows is a challeng-

ing problem. A new system based on the Aeroramp® fuel injector de-

sign combined with a plasma torch is under research. Several fuels and

torch feedstocks including liquids and gasses are being investigated.

Tests in an unheated wind tunnel at a Mach number of 2.4 are promis-

ing.

Computational Simulations of Internal Turbine Blade Computational Simulations of Internal Turbine Blade Computational Simulations of Internal Turbine Blade Computational Simulations of Internal Turbine Blade

Cooling, Cooling, Cooling, Cooling, Danesh TaftiDanesh TaftiDanesh TaftiDanesh Tafti

The internal cooling of turbine blades

is a critical problem for the gas turbine

industry. Prediction of these flows

have been complicated by the pres-

ence of turbulence generators for heat

transfer augmentation, rotational Cori-

olis, and buoyancy forces. Reynolds

number ranges from moderate O(104)

to very high O(105) depending on the

application. Rotation numbers can be

of O(1), and centrifugal buoyancy

driven Rayleigh numbers of O(108).

The turbulent flow is highly anisotropic

and all attempts at predicting the flow and heat transfer have fo-

cused on the solution of steady Reynolds Averaged Navier-Stokes

(RANS) and energy equations. The focus of the current research is to

apply alternative time-dependent solution techniques based on large-

eddy and detached-eddy simulations (LES and DES, respectively).

Currently LES is being performed in ribbed channels with the code

GenIDLEST (Generalized Direct and Large Eddy Simulations of Turbu-

lence) at Re=20,000.

Periodic section of a ribbed channel


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12

A General Theory for the Effect of Large Scale

Freestream Turbulence on Surface Heat Transfer, Tom

Diller and Pavlos Vlachos

The objective of

this research is to examine

the effects of freestream

turbulence on boundary

layer heat transfer using

state-of-the-art TRDPIV

(Time Resolved Digital

Particle Image Veloci-

metry) and by developing

and employing a new class

of thin film heat flux sen-

sors called the HFA (Heat

Flux Array). TRDPIV is

used to spatiotemporally

resolve the dynamics of the

flow, while the HFA is used

to directly measure heat

flux signals on the surface as well as surface temperature. We were able

to resolve coherent structures as they interacted with the boundary layers,

and directly correlate these motions with heat flux. Coherent structure

identification and tracking algorithms were developed and implemented

to further understand the fundamental mechanism of heat transfer aug-

mentation by freestream turbulence. Our results so far support the notion

that vortices near the plate interact or exchange heat with the plate for a

characteristic time t~d2/G where d is the mean distance of the vortex core

form the surface and G is the mean circulation of the vortex. Correlations

of measured heat flux with coherent structures validate this hypothesis.

Therefore this simplistic phenomenological model is capturing the asso-

ciated physical processes. Additional, more complex models and correla-

tions are currently being examined with promising results.


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Example of TRDPIV images where flow velocity magnitude is contoured and vectors are added to bring out the structure of the

stagnating flow field.

Porous flow Modeling and Parallel Implementation of Porous flow Modeling and Parallel Implementation of Porous flow Modeling and Parallel Implementation of Porous flow Modeling and Parallel Implementation of

Aircast, Aircast, Aircast, Aircast, Danesh Tafti

The project involves the enhancement of ARCAST, which predicts the

thermal response of charring materials used in nozzle liners. It involves

the enhanced modeling of the pyrolyzed gas flow in the liner together

with efficient parallelization strategies to increase physical as well as

computational fidelity.

Rocket Propulsion

13

14

Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,

Joseph A. Schetz

A direct-measuring skin friction gage was developed for the high-

speed, high-temperature environment of the turbulent boundary layer in

a supersonic combustor. The design is that of a non-nulling

cantilevered beam, the head of which is flush with the model wall and

surrounded by a small (0.0127 cm) gap. Finite element software along

with simple beam theory were used to analyze the response of the

beam to an applied shear load. Semiconductor (piezo-resistive) strain

gages were used to detect this strain at the base of the beam. Cooling

water was routed both inside the beam and around the external housing

in order to control the temperature of the strain gages. The gage was

statically calibrated using a direct force method and verified by testing

in a well-documented Mach 2.4 cold-flow. Results of the cold-flow

tests were repeatable and within 15% of the value of Cf estimated from

simple theory. The gage was then installed and tested in a rocket-

based-combined-cycle engine model operating in the scramjet mode.

Instrumentation and Sensor

Development

VT Skin Friction Gage Qualified for Hypersonic Flight Test

on X-43

15

Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,

Anbo Wang

The Center for Photonics Technology

(CPT) in the Department of Electrical

and Computer Engineering at Virginia

Tech is a recognized leader in the

area of photonic sensors for harsh

environments. The Center currently

maintains 8,000 square feet of labo-

ratory and office space specifically to

support research and development

programs in the areas of photonic

sensor instrumentation for physical,

chemical, medical and biological measurements. Their research

covers all major aspects concerning sensors, ranging from novel sens-

ing mechanisms, sensor materials, nanofilms, optoelectronic signal

processing to instrumentation systems. Some of the major sensors

they have investigated or developed include: pressure sensors for

static and dynamic measurements up to 20,000psi; temperature sen-

sors from up to 1700oC; strain sensors for high temperatures up to

1500oC; acoustic sensors for frequencies from 0.01Hz to 1MHz; self-

calibrating flow sensors; magnetic field sensors from 1-40,000nT;

laser spectroscopy for cancer diagnosis; chemical gas measurement

at high temperatures up to 800oC; biological agent detection; simulta-

neous measurement of multi-quantities by a single fiber; sensor

multiplexing.

Single-crystal sapphire fiber fiber-based

strain sensor capable of operation above

1000oC


Development

16

Heat Flux SensorsHeat Flux SensorsHeat Flux SensorsHeat Flux Sensors, T. E. Diller

Several new heat flux sensors are being built and tested in sup-

port of gas turbine research. These include insert type gages and thin

surface mounted gages, both single point and sensor arrays. The High

Temperature Heat Flux Sensor (HTHFS) is capable of long term opera-

tion at temperatures and heat flux levels in excess of 1000°C and 10 W/

cm2 respectively. The current sensor configuration utilizes type-K ther-

mocouple materials in a durable welded thermopile arrangement. The

steady-state thermoelectric sensitivity of the design is predicted using a

one-dimensional thermal resistance model and the Seebeck coefficient of

the thermocouple materials. Average experimental values of the sensitiv-

ity are about 1 mV/W/cm2 with no apparent effect of thermal cycling.

Calibration facilities include methods for testing sensors in pre-

dominantly convective, radiative, or conductive heat transfer modes. A

high-temperature calibration facility is currently being designed for im-

plementation in the near future. Based on experimental results previously

obtained, a model has been developed and tested that shows the effect of

convection relative to

radiation on the re-

sponse of heat flux

gages. The effect of

convection can be quite

significant over some

ranges.


Development

Original version of the VT/EPFL heat flux gage

17

A MagneticallyA MagneticallyA MagneticallyA Magnetically----Levitated Levitated Levitated Levitated Rocket Thrust Measurement Rocket Thrust Measurement Rocket Thrust Measurement Rocket Thrust Measurement

Test Rig,Test Rig,Test Rig,Test Rig, Mary E. F. Kasarda

A Magnetically-Levitated Rocket Thrust Measurement System (TMS)

is a novel approach allowing for increased flexibility to meet changing

test requirements for rockets and gas turbines, while providing high-

accuracy thrust measurements. This project develops such a system

by utilizing Active Magnetic Bearings (AMBs) to simultaneously sup-

port the test article and measure the generated thrust and side loads.

By selectively utilizing multiple AMBs in parallel, test articles with a

wider range of performance can be tested in the same fixture, elimi-

nating the need for multiple test stands in some scenarios, resulting

in a reduction of hardware and facility expenditures. A laboratory

scale prototype TMS system sponsored by NASA Stennis and Imlach

Consulting Engineering was recently delivered to NASA Stennis after

initial testing at Virginia Tech.

Magnetic Dampers for Improved Rotor Stability, Magnetic Dampers for Improved Rotor Stability, Magnetic Dampers for Improved Rotor Stability, Magnetic Dampers for Improved Rotor Stability,

Mary E. F. Kasarda

The main body of this work involved examin-

ing the effect of a magnetic damper on reduc-

ing subsynchronous and supersynchronous

vibrations on a small high-speed test rotor.

Tests were run on two different rotor configu-

rations with the damper located at various

locations along the rotor and with various

settings of stiffness and damping.

(continued on next page)

Investigation of active magnetic

bearings for reduction of gear

noise

Rotor Dynamics and

Magnetic Bearings

Results showed as much as a 98% reduction in subsynchronous vibra-

tions and in some cases showed an increase in synchronous vibrations.

The tests demonstrated the potential for a magnetic damper to improve

rotor stability and that a thorough rotor dynamic investigation is neces-

sary to fully examine the effect of the magnetic damper on overall sys-

tem dynamics.

CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,

R. Gordon Kirk

A major research effort is CFD analysis for fluid film bearings and seals.

CFX-TASCflow with CFX-Build and CFX-TurboGrid have been used

to simulate fluid-film bearing and seal geometries.

Some desired geometries for bearing simulation

have been successfully conducted including the

cylindrical hydrodynamic bearing, the hydrostatic

bearing and the hybrid bearing with laminar or

turbulent flow conditions. A user’s program will

be developed and connected to the software

through a new interface. This will permit auto-

matic perturbation analysis for computation of bearing and seal dy-

namic stiffness and damping characteristics. Bearing, seal and viscous

damper evaluation of internal flows and leakage rates are compared to

current analysis and design methods.

Evaluating CFD results of

bearing analyses

Rotor Dynamics and

Magnetic Bearings

18

William T. BaumannWilliam T. BaumannWilliam T. BaumannWilliam T. Baumann

Education: B.S.E.E., Lehigh University, 1978,

M.S.E.E., M.I.T., 1980 , Ph.D., Johns Hopkins

University, 1985

Research Interests: Active Combustion Control and

Modeling of Combustion Systems: Theoretical and

experimental investigation of the control of ther-

moacoustic instabilities in gas turbines and aero engines. Development of

modular models that describe combustion instabilities such as ther-

moacoustic limit cycles and lean blow out. Active Noise and Vibration

Control: Design of feedback-based hearing protection systems and struc-

tural vibration control systems. Approaches include adaptive control and

direct optimization.

Ricardo A. BurdissoRicardo A. BurdissoRicardo A. BurdissoRicardo A. Burdisso

Dr. Burdisso received his engineering degree from the

National University of Cordoba, Argentina in 1981. He

obtained his Ph.D. at Virginia Tech in 1986 with

research in stochastic analysis of systems under

multiple correlated seismic input. He joined the

Mechanical Engineering Department at Virginia Tech in

1989 as a Research Scientist working in the area of ac-

tive control of structurally radiated sound. In the Fall of

1992, Dr. Burdisso accepted the assistant professor position in the same

department.

Research Interests: Passive and active control of structural vibrations

and their sound radiation, development of adaptive control algorithms

Participating Faculty Members

19

William J. DevenportWilliam J. DevenportWilliam J. DevenportWilliam J. Devenport

Dr. Devenport received his B. Sc. degree in Engineering

Science from the University of Exeter, England, and his

Ph.D. in experimental and computational fluid dynamics

from the University of Cambridge, England. He came to

Virginia Tech in 1985 as a research associate and then

joined the faculty of the Department of Aerospace and

Engineering in 1989.

Research Interests: Experimental studies of turbulence structure of tip

vortices, tip-vortex blade interactions and tip-leakage vortex wakes Thomas E. DillerThomas E. DillerThomas E. DillerThomas E. Diller Dr. Diller received degrees in Mechanical Engineering from Carnegie-

Mellon University (B.S., 1972) and the Massachusetts Institute of Technol-

ogy (M.S., 1974; Sc.D., 1977). Prior to joining the Mechanical Engineer-

ing faculty in 1979, he spent three years at the Polaroid Cor-

poration doing research in the process engineering area.

Research Interests: Development and use of new instru-

mentation for measuring heat transfer, particularly in high

temperature unsteady flows


20

Srinath V. EkkadSrinath V. EkkadSrinath V. EkkadSrinath V. Ekkad

Dr. Ekkad joined Virginia Tech in August 2007. He

spent 9 years at LSU and 2 years at Rolls-Royce, Indi-

anapolis before that. Dr. Ekkad is an expert in the area

of gas turbine heat transfer and cooling. He has devel-

oped experimental techniques for heat transfer meas-

urement for film cooling and has written a book on

gas turbine heat transfer and cooling technology. He

received his Ph.D. in 1995 from Texas A&M University.

Research Interests: Research Interests: Research Interests: Research Interests: Gas turbine cooling and heat transfer, film cool-

ing, design of high temperature components, combustor design, ex-

perimental heat transfer, micro-channel flow and heat transfer, nan-

ofluids

Steve KampeSteve KampeSteve KampeSteve Kampe

Dr. Kampe received a B.S. in 1981, an M.S. in 1983, and a

Ph.D. in 1987 from Michigan Technological University.

He is currently an associate professor in the Materials Sci-

ence and Engineering department at Virgina Tech.

Research interests: Mechanical behavior, composite mate-

rials, intermetallics, titanium alloys, and alloy development

and processing


21

Mary E. F. KasardaMary E. F. KasardaMary E. F. KasardaMary E. F. Kasarda

Dr. Kasarda joined Virginia Tech as an assistant

professor in January of 1997. She has six years of

professional engineering experience and is a former em-

ployee of Ingersoll-Rand, Rotor Bearing Dynamics, Inc.,

and Du Pont. Her background is in various aspects of tur-

bomachinery engineering including rotor dynamics and

the repair and overhaul of rotating equipment. She com-

pleted her Ph.D. in 1996 at the University of Virginia.

Research Interests: Effects of base motion on performance of

magnetic bearing systems, investigation of magnetic bearings for meas-

urement of forces in a rocket thrust measurement system and the charac-

terization of power losses in magnetic bearings

R. Gordon KirkR. Gordon KirkR. Gordon KirkR. Gordon Kirk

Dr. Kirk studied at the University of Virginia where he received a B.S.

degree in 1967, an M.S. in 1969, and a Ph.D. in 1972.

His industrial experience includes three years with Pratt &

Whitney Aircraft in East Hartford, Conn., and ten years

with the Ingersoll-Rand Turbo Machinery Division in

Phillipsburg, NJ. He joined the Mechanical Engineering

Department at Virginia Tech in 1985.

Research Interests: Liquid and gas seal influence on rotor

response and stability, dynamics stability of active magnetic bearings,

active control of rotor response, thermal instability of rotors, and balanc-

ing of rotating machinery


22

Wing F. NgWing F. NgWing F. NgWing F. Ng

Dr. Ng is the Chris Kraft Professor of Engineering at

Virginia Tech. He received his B.Sc. (M.E.) degree

from Northeastern University, and his S.M. and Ph.D.

from the Massachusetts Institute of Technology. Before

beginning his S.M. work, he worked for the Aircraft

Engine Group of the General Electric Company.

Research Interests: Flow control for aeropropulsion, calculations of

turbo-machinery flowfields, experimental studies of turbomachinery cas-

cades, and aeroacoustics

Walter F. O’BrienWalter F. O’BrienWalter F. O’BrienWalter F. O’Brien

Dr. O’Brien received degrees from Virginia Polytechnic Institute & State

University and Purdue University. He has conducted

research and development projects in several propul-

sion-related areas including gas generators and rockets,

gas turbines, and SCRAMJETS.

Research Interests: Modeling the transfer of non-

uniform flow in transonic compressors, the use of gas

turbine engine performance models for improving gas turbine manufac-

turing and maintenance practices, ignition and flame holding in super-

sonic flame combustion


23

Danesh K. TaftiDanesh K. TaftiDanesh K. TaftiDanesh K. Tafti

Dr. Danesh K. Tafti obtained his Ph.D. from Penn State University in

1989. He served as a visiting professor at West Virginia Institute of

Technology from 1988-1989, a post doctoral research associate from

1989-1991 and then as a research scientist at the national Center for Su-

percomputing Applications at the University of Illinois,

Urbana Champaign from 1991-2001. Currently he is an

Associate Professor in the Department of Mechanical Engi-

neering at Virginia Tech, where he directs the High Per-

formance Computational Fluid-Thermal Science and Engi-

neering Lab.

Research Interests: Large-scale unsteady simulations of complex turbu-

lent flow and heat transfer using Direct Numerical Simulations (DNS),

Large-Eddy Simulations (LES), and hybrid methods (RANS-LES), paral-

lel computing and programming paradigms. Current projects are in com-

pact heat exchangers, turbomachinery, microfluidics for integrated micro

-total-analysis systems, and the development of computational tools for

high performance computing

Joseph A. SchetzJoseph A. SchetzJoseph A. SchetzJoseph A. Schetz

Dr. Schetz received his bachelor’s degree in 1958 from

Webb Institute of Naval Architecture and went on to pursue

three graduate degrees at Princeton University. He obtained

his M.S. in 1960, his M.A. in 1961, and his doctorate the

following year. While writing his dissertation for Prince-

ton, Dr. Schetz joined the General Applied Science Labora-

tory. In 1964, he joined the faculty of the University of

Maryland as an associate professor of Aerospace Engineering, and five

years, later, he joined Virginia Tech in the Department of Aerospace and

Ocean Engineering.

Research Interests: Turbulent flow injection and mixing problems, from

supersonic cases to thermal pollution in rivers


24

25

Uri VandsburgerUri VandsburgerUri VandsburgerUri Vandsburger

Dr. Vandsburger received his B.Sc. in Mechanical Engi-

neering from the Technion (IIT). His postgraduate

work was performed at Princeton University where he

earned a M.A. and Ph.D. in Mechanical and Aerospace

Engineering. Before returning to graduate school, he

worked in Israel as a mechanical design engineer in the

area of airborne structures, and in West Germany as a

thermal systems design engineer. He worked as a re-

search associate for five years at SU-HTGL.

Research Interests: Flow and combustion control for the purpose of

missing and combustion enhancement, fundamental studies on pollutant

formation, synthesis of nanosize powders, CO formation and transport in

building fires

Pavlos VlachosPavlos VlachosPavlos VlachosPavlos Vlachos

Dr. Vlachos received his BS in Mechanical Engineer-

ing from the National Technical University of Athens

(1995) and his MS (1998) and PhD (2000) in Engineer-

ing Mechanics from Virginia Tech. On August 2003

he joined the Department of Mechanical Engineering at

Virginia Tech as assistant professor and he was pro-

moted to associate with tenure in 2007. Dr Vlachos is

the recipient of the 2007 ASME Fluids Engineering

Moody award and a 2007 College of Engineering Fac-

ulty Fellow. In the same year, he delivered the keynote paper in the

ASME Fluids Measurement and Instrumentation Forum. He was

awarded the 2005 Dean’s Award of Excellence for Outstanding Assis-

tant Professor and the 11th Annual T.F. Ogilvie Lectureship Award for

Young Investigator in Ocean Engineering and Fluid Mechanics by the

MIT Department of Mechanical Engineering. In 2006 he became a re-

cipient of the NSF CAREER award . Research Interests: Research Interests: Research Interests: Research Interests: Experimental fluid mechanics addressing a variety

of flows such as biofluid/cardiovascular mechanics, multi-phase flows

classical aerothermodynamics, sensors and instrumentation


26

Facilities

• Compressor Cascade with Moving Wall

• JT15D Research Gas Turbine

• F109 Turbofan Engine

• Supersonic/Transonic Wind Tunnel

• Laminar and Turbulent

Combustors

• Anechoic Chamber

• Two Linked Reverberation Chambers

• Schlieren and Shadowgraph

• Laser Doppler Anemometers

• Chemiluminecense Analyzers (CLA)

• Heat Flux Sensors

• Infared Thermolgrapy

• Liquid Crystal Thermography

• Hot-Wire Anemometry

• Fast-Response Pressure and Heat Flux Gages

• High-Speed Fluid-Film Bearing Test Rig

28

Sponsors

30

Virginia Tech’s College of Engineering Virginia Tech’s College of Engineering Virginia Tech’s College of Engineering Virginia Tech’s College of Engineering

Virginia Tech is home to the

Commonwealth's leading Col-

lege of Engineering, known in

Virginia and throughout the

nation for its excellent pro-

grams in engineering educa-

tion, research, and public

service. Overall, the college

ranked 24th in the 2002 U.S.

News and World Report graduate survey of engineering schools.

Tech’s College of Engineering, specifically the Mechanical Engi-

neering Department, is one of the few institutions with a strong back-

ground in propulsion and turbomachinery research.

For more information about Virginia Tech’s Center for Turbomachinery and Propulsion Research, feel free to contact: Dr. Srinath Ekkad Mechanical Engineering 101 Randolph Hall Mail Code 0238 Blacksburg VA 24061

Center for Turbomachinery and Center for Turbomachinery and Center for Turbomachinery and Center for Turbomachinery and Propulsion Research Propulsion Research Propulsion Research Propulsion Research

© 2004– Center for Turbomachinery and Propulsion Research - Virginia Tech- All Rights Reserved.

Phone: 540-231-7192 Fax: 540-231-9100 E-mail: [email protected]

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