The effects of heat transfer between the compressor structure and the primary gas path flow on compressor stability are investigated during hot engine re-acceleration transients. A mean line analysis of an advanced, high-pressure ratio compressor is extended to include the effects of heat transfer on both stage matching and blade row flow angle deviation. A lumped capacitance model is used to compute the heat transfer of the compressor blades, hub, and casing to the primary gas path. The inputs to the compressor model with heat transfer are based on a combination of full engine data, compressor test rig measurements, and detailed heat transfer computations. Nonadiabatic transient calculations show a 8.0 point reduction in stall margin from the adiabatic case, with heat transfer predominantly altering the transient stall line. 3.4 points of the total stall margin reduction are attributed to the effect of heat transfer on blade row deviation, with the remainder attributed to stage rematching. Heat transfer increases loading in the front stages and destabilizes the front block. Sensitivity studies show a strong dependence of stall margin to heat transfer magnitude and flow angle deviation at low speed, due to the effects of compressibility. Computations for the same transient using current cycle models with bulk heat transfer effects only capture 1.2 points of the 8.0 point stall margin reduction. Based on this new capability, opportunities exist early in the design process to address potential stability issues due to transient heat transfer.

References

References
1.
Schulte
,
H.
,
Schmidt
,
K.
,
Weckend
,
A.
, and
Staudacher
,
S.
,
2008
, “
Multi-Stage Compressor Model for Transient Performance Simulations
,”
ASME
Paper No. GT2008-51159.
2.
Schölce
,
M.
,
Merkler
,
R.
,
Schulte
,
H.
, and
Schmidt
,
K.
,
2005
, “
Simulation of Clearance Changes and Mechanical Stresses in Transient Gas Turbine Operation by a Matrix Method
,”
AIAA
Paper No. 2005-4022.
3.
Maccallum
,
N.
, and
Grant
,
A.
,
1978
, “
The Effect of Boundary Layer Changes Due to Transient Heat Transfer on the Performance of an Axial-Flow Air Compressor
,” Society of Automotive Engineers, New York, Technical Report No. 770284.
4.
Crawford
,
R.
, and
Burwell
,
A.
,
1985
, “
Quantitative Evaluation of Transient Heat Transfer on Axial Flow Compressor Stability
,”
AIAA
Paper No. 1985-1352.
5.
Lou
,
F.
,
Fabian
,
J.
, and
Key
,
N.
,
2017
, “
Stall Inception in a High-Speed Centrifugal Compressor During Speed Transients
,”
ASME J. Turbomach.
,
139
(
12
), p.
121004
.
6.
Kiss
,
A.
,
2015
, “
Two Investigations of Compressor Stability: Spike Stall Inception and Transient Heat Transfer Effects
,”
Master's thesis
, Massachusetts Institute of Technology, Cambridge, MA.https://dspace.mit.edu/handle/1721.1/101445
7.
Jones
,
S.
,
2014
, “
Development of an Object-Oriented Turbomachinery Analysis Code Within the NPSS Framework
,” National Aeronautics and Space Administration, Hanover, MD, Technical Report No.
TM-2014-216621
.https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140011370.pdf
8.
Jones
,
S.
,
2015
, “
Design of an Object-Oriented Turbomachinery Analysis Code: Initial Results
,”
International Symposium on Air-Breathing Engines
, Phoenix, AZ, Oct. 25–30, Report No.
ISABE-2015-20015
.https://ntrs.nasa.gov/search.jsp?R=20160001350
9.
Shah
,
P.
,
2007
, “
Novel Turbomachinery Concepts for Highly Integrated Airframe/Propulsion Systems
,”
Ph.D. thesis
, Massachusetts Institute of Technology, Cambridge, MA.https://dspace.mit.edu/handle/1721.1/38929
10.
Farthing
,
P.
,
Long
,
C.
,
Owen
,
J.
, and
Pincombe
,
J.
,
1992
, “
Rotating Cavity With Axial Throughflow of Cooling Air: Heat Transfer
,”
ASME J. Turbomach.
,
114
(
1
), pp.
229
236
.
11.
Camp
,
T.
, and
Day
,
I.
,
1998
, “
A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor
,”
ASME J. Turbomach.
,
120
(
3
), pp.
393
401
.
12.
Pullan
,
G.
,
Young
,
A.
,
Day
,
I.
,
Greitzer
,
E.
, and
Spakovszky
,
Z.
,
2014
, “
Origins and Structure of Spike-Type Rotating Stall
,”
ASME J. Turbomach.
,
137
(
5
), p.
051007
.
13.
Lieblein
,
S.
,
1959
, “
Loss and Stall Analysis of Compressor Cascades
,”
J. Basic Eng.
,
81
, pp.
387
400
.
14.
Frechette
,
L.
,
1997
, “
Implications of Stability Modeling for High-Speed Axial Compressor Design
,”
Master's thesis
, Massachusetts Institute of Technology, Cambridge, MA.https://dspace.mit.edu/handle/1721.1/10721
15.
Longley
,
J.
, and
Hynes
,
T.
,
1990
, “
Stability of Flow Through Multistage Axial Compressors
,”
ASME J. Turbomach.
,
112
(
1
), pp.
126
132
.
16.
Cumpsty
,
N. A.
,
2004
,
Compressor Aerodynamics
,
Krieger Publishing Company
,
Malabar, FL
.
You do not currently have access to this content.