Sub-idle is a very challenging operating region as the performance of a gas turbine engine changes significantly compared with design conditions. In addition, the regulations for new and existing engines are becoming stricter and the prediction of engine relight capability is essential. In order to predict the performance of an engine, detailed component maps are required. The data obtained from rig tests are insufficient at low speeds, creating the need for generation of maps within the sub-idle regime. The first step toward this direction is the use of an extrapolation process. This is a purely mathematical process and the results are not usually of sufficient accuracy. In addition, this method does not provide any insight on the physical phenomena governing the operation of the compressor at low speeds. The accuracy of the resulting compressor map can be increased with a better low speed region definition; this can be achieved via the thorough study of a locked rotor compressor, enabling the derivation of the zero rotational speed line and allowing an interpolation process for the generation of the low speed part of the characteristic. In this work, an enhanced sub-idle compressor map generation technique is proposed. The suggested methodology enables the generation of characteristics at far off-design conditions with enhanced physical background. Alternative parameters for map representation are also introduced. Provided that the all the blade rows of the compressor are of known geometry, a numerical analysis is used for the calculation of the characteristic of the half stage and a stage stacking method is employed to create the entire compressor characteristic. This way, the sub-idle region of the map can be calculated through interpolation, which provides a more accurate and predictive technique. Application of the method for compressor map generation showed that the proposed interpolation approach is robust and capable of enhancing any performance simulation tool used for the prediction of transient altitude relight or ground-starting maneuvers.

1.
Anderson
,
B. A.
,
Messih
,
D.
, and
Plybon
,
R. C.
, 1997, “
Engine-Out Performance Characteristics
,”
ISABE—International Symposium on Air Breathing Engines
.
2.
Pakanati
,
S.
,
Sampath
,
R.
,
Irani
,
R.
,
Plybon
,
R. C.
, and
Anderson
,
B. A.
, 2006, “
High Fidelity Engine Performance Models for Windmill Relight Predictions
,”
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
, Sacramento, CA.
3.
Kurzke
,
J.
, 1996, “
How to Get Component Maps for Aircraft Gas Turbine Performance Simulations
,”
International Gas Turbine and Aeroengine Congress and Exhibition
, Birmingham, UK.
4.
Walsh
,
P. P.
, and
Fletcher
,
P.
, 2004,
Gas Turbine Performance
,
2nd ed.
,
Oxford Blackwell Science
.
5.
Jones
,
G.
,
Pilidis
,
P.
, and
Curnock
,
B.
, 2001, “
Compressor Characteristics in Gas Turbine Performance Modelling
,”
ASME Turbo Expo
, New Orleans, LA.
6.
Kurzke
,
J.
, and
Riegler
,
C.
, 2000, “
A New Compressor Map Scaling Procedure for Preliminary Conceptional Design of Gas Turbines
,”
ASME Turbo Expo
, Munich, Germany.
7.
Cravero
,
C.
, and
Macelloni
,
P.
, 2009, “
A New Model for the Prediction of Compressor Performance Maps
,”
ISABE—International Symposium on Air Breathing Engines
.
8.
Morita
,
M.
,
Sasaki
,
M.
, and
Torisaki
,
T.
, 1989, “
Restart Characteristics of Turbofan Engines
,”
ISABE—International Symposium on Air Breathing Engines
.
9.
Agrawal
,
R. K.
, and
Yunis
,
M.
, 1982, “
A Generalized Mathematical Model to Estimate Gas Turbine Starting Characteristics
,”
ASME J. Eng. Gas Turbines Power
0742-4795,
104
, pp.
194
201
.
10.
Sexton
,
W.
, 2001, “
A Method to Control Turbofan Engine Starting by Varying Compressor Surge Valve Bleed
,” MS thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA.
11.
Gaudet
,
S. R.
, and
Gauthier
,
J. E. D.
, 2007, “
A Simple Sub-Idle Component Map Extrapolation Method
,”
ASME Turbo Expo
, Montreal, Canada.
12.
Adam
,
O.
, and
Leonard
,
O.
, 2005, “
A Quasi-One Dimensional Model for Axial Compressors
,”
Proceedings of the 17th ISABE
.
13.
Kang
,
I. S.
,
Choi
,
M. S.
,
Lim
,
J. S.
, and
Hong
,
Y. Y.
, 1997, “
Analysis of Windmilling Characteristics for a Twin-Spool Turbofan Engine
,”
ASME
Paper No. 97-AA-113.
14.
Converse
,
G. L.
, and
Giffen
,
R. G.
, 1984, “
Representation of Compressor Fans and Turbines
,” Report No. NASA-CR-174645.
15.
De-You
,
Y.
, and
Zhong-Fan
,
M.
, 1983, “
A Dynamic Model of a Turbojet in Starting at High Altitude
,”
The Sixth International Symposium on Air Breathing Engines
, AIAA Paper No. 83-7045.
16.
Jones
,
G.
,
Pilidis
,
P.
, and
Curnock
,
B.
, 2002, “
Extrapolation of Compressor Characteristics to the Low-Speed Region For Sub-Idle Performance Modelling
,”
ASME Turbo Expo
, Amsterdam, The Netherlands.
17.
Riegler
,
C.
,
Bauer
,
M.
, and
Kurzke
,
J.
, 2000, “
Some Aspects of Modeling Compressor Behavior in Gas Turbine Performance Calculations
,”
ASME Turbo Expo
, Munich, Germany.
18.
McKenzie
,
A. B.
, 1997,
Axial Flow Fans and Compressors: Aerodynamic Design and Performance
,
Ashgate
,
Aldershot
.
19.
Howell
,
A. R.
, 1945, “
Fluid Dynamics of Axial Compressors
,”
Proceedings of IMechE
, p.
153
.
20.
Zachos
,
P. K.
,
Pengue
,
F.
,
Pachidis
,
V.
, and
Pilidis
,
P.
, 2009, “
Flowfield Investigation of a Compressor Cascade at High Incidence—Part 2: Numerical Analysis
,”
ASME Turbo Expo
, Orlando, FL.
21.
Zachos
,
P. K.
,
Pachidis
,
V.
,
Charnley
,
B.
, and
Pilidis
,
P.
, 2009, “
Flowfield Investigation of a Compressor Cascade at High Incidence—Part 1: Pneumatic Probe Measurements
,”
ASME Turbo Expo
, Orlando, FL.
22.
Dixon
,
S. L.
, 2005,
Fluid Mechanics and Thermodynamics of Turbomachinery
,
5th ed.
,
Pergamon
,
New York
.
23.
Song
,
T. W.
,
Kim
,
T. S.
,
Kim
,
J. H.
, and
Ro
,
S. T.
, 2001, “
Performance Prediction of Axial Flow Compressors Using Stage Characteristics and Simultaneous Calculation of Inter-Stage Parameters
,”
Proceedings of the IMechE
, Vol.
215
, Pt. A, pp.
89
98
.
24.
Howell
,
A. R.
, and
Calvert
,
W. J.
, 1978, “
A New Stage Stacking Technique for Axial-Flow Compressor Performance Prediction
,”
ASME J. Eng. Gas Turbines Power
0742-4795,
100
, pp.
698
703
.
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