precise modeling of desing point performance for a uav
TRANSCRIPT
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C A P T A I N R O M A N S H A P I R O , I A F ( R E T . )
8 T H I S R A E L I S Y M P O S I U M O N J E T E N G I N E S A N D G A S T U R B I N E S
F A C U L T Y O F A E R O S P A C E E N G I N E E R I N G , T E C H N I O N , H A I F A , 1 9 / 1 1 / 2 0 0 9
Precise modeling of design point performance for a UAV turboprop engine,
under constraints of GasTurb software
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Outline1
Motivation
Methodology steps
First constraint: template selection
Second constraint: cooling system representation
Design point modeling
Simulation results
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Motivation
Compose an off-design simulation using GasTurb software.
GasTurb uses a design point model as a reference point for off-design simulation.
Accurate off-design simulation requires a precise model for reference point.
2
Off-Design Simulation
DP Reference Model
Test Bench Measurements
Evaluate the benefits of adding a heat exchanger to an existing PT6A-67A engine.
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Methodology steps3
Select an appropriate engine template.
Perform fine tuning so that the simulation results match the actual engine’s performance in design point.
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Template selection within GasTurb4
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???
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intercooled recuperated turboshaft with booster driven by HP spool
First constraint: template selection5
turboshaft with booster driven by HP spool
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Second constraint: cooling system representation
PT6A-67A
Cooling air enters HP turbine rotor.
Splits to 2 paths: 1st stage of PT rotor and the guide vanes.
Splits to 2 paths: 2nd
stage of PT rotor and the guide vanes.
6
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Second constraint: cooling system representation
GasTurb
Single value for the temperature of the cooling air.
Has 4 fixed points for entering of the cooling air: 1) HPT GV 2)HPT Rotor 3) PT GV 4) PT Rotor
7
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Design point modeling8
Steady state DECK software was used to generate
input data (forced variables)
comparison data (control variables)
GasTurb was operated in the Test Analysis mode.
Iterations mode of GasTurb was used to estimate
Various losses
Coefficients
Components efficiencies
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Design point modeling9
Calculated Values
Output Shaft [kWatt] 894.8026 Fuel Flow [kg/sec] 0.085983
Net Trust [Nt] 803.4379 PSFC [kg/(kW*h)] 0.3459
Output Torgue [Nt-m] 5026.309 Gas Gen. Speed [RPM] 36204.7
A8 [m²] 0.060645 Engine Airflow [kg/sec] 4.667466
Pressures Temperatures
Comp. Inlet P1 [kPa] 101.3253 Comp. Inlet T1 [K] 288.15
Interstage P2.5 [kPa] 418.8151 Interstage T2.5 [K] 464.48
Comp. Delivery P3 [kPa] 943.2441 Comp. Delivery T3 [K] 610.38
Exhaust P7 [kPa] 108.5579 EGT T7 [K] 823.03
P2.5 Bleed (Interstage) [kPa] 368.5592 ITT [K] 993.61
P3 Bleed (Comp. Del.) [kPa] 943.2441
Pressure Ratios
P2.5 / P1 4.13337
P3 / P1 9.30909 Forced variable
P7 / Pamb 1.0714 Control variable
P2.5 Bleed/ P1 3.63736
P3 Bleed/ P1 9.30909
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Simulation results10
Deck GasTurb Error
Output Shaft Power
[kW] 894.8026 894.84 -0.0042%
Net Thrust [Nt] 803.4379 803.437 0.0001%
PSFC [kg/(kW*h)] 0.3459 0.3459 0.0000%
Wf [kg/sec] 0.085983 0.085983 0.0006%
A8 [m²] 0.060645 0.060645 0.0002%
R8 [m] 0.138939 0.138938 0.0001%
Wa [kg/sec] 4.667 4.667 0.0000%
NG [RPM] 36204.7 36204 0.0019%
P02 [Kpa] 101.325 101.325 0.0000%
P025 [kPa] 418.82 418.81 0.0012%
P03 [kPa] 943.24 943.24 0.0000%
P08 [kPa] 108.56 108.552 0.0074%
T02 [K] 288.15 288.15 0.0000%
T025 [K] 464.48 464.48 0.0000%
T03 [K] 610.38 610.38 0.0000%
T045 [K] 993.61 993.61 0.0000%
T08 [K] 823.03 823.03 0.0000%
P03/P02 9.30909 9.30906 0.0003%
P08/Pamb 1.0714 1.07132 0.0075%
Component Isentr. Eff. P/P
LP Compressor 0.8243 4.218
HP Compressor 0.8033 2.252
Combustor 0.995 0.97
HP Turbine 0.8824 3.435
Power Turbine 0.8827 2.357
LP Spool Mech. 0.9779 -
HP Spool Mech. 0.9650 -
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Model transformation11
intercooled recuperated turboshaft with booster driven by HP spool
turboshaft with booster driven by HP spool
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Model transformation12
02/04/2009 GasTurb 11
-.2 0 .2 .4 .6 .8 1 1.2
Entropy [kJ/(kg K)]
-200
0
200
400
600
800
1000
1200
1400
En
tha
lpy [k
J/k
g]
200 kPa
400 kPa
600 kPa
800 kPa
Pso (ambient) = 101 kPa1 2
24 25
3
441
43
44 45
49
5 8
s8
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Summary13
A need in precise DP model with an option for the HE.
Lack of adequate engine template in GasTurb software.
Usage of combination of two semi-adequate templates
Incompatibility between the software's and the actual PT6 turbine cooling mechanism.
Proper adjustment of air cooling capacity
Model adjustment with high accuracy.
Transfer of adjusted model to the compatible template with HE option.