Axial compressor performance with heat extraction via blade passage surfaces (compressor cooling) is compared to its adiabatic counterpart, using computational experiments and mean line modeling. For a multistage compressor with an adiabatic design point, results at fixed corrected rotor speed indicate that, if available, compressor cooling would (i) raise the overall pressure ratio (at a given corrected flow), (ii) raise the maximum mass flow capability, (iii) raise the efficiency, defined as the ratio of isentropic work for a given pressure ratio to actual shaft work, and (iv) provide rear stage choking relief at low corrected speed. In addition, it is found that, if available, cooling in the front stages is better than in the rear stages. This is primarily a thermodynamic effect that results from the fact that, for a given gas, the compression work required to achieve a given pressure ratio decreases as the gas becomes colder. Heat transfer considerations indicate that the engineering challenges lie in achieving high enough heat transfer rates to provide a significant impact to the compressor’s performance.

1.
Hewitt
,
F. A.
and
Johnson
,
M. C.
, 1991, “
Propulsion System Performance and Integration for High Mach Air Breathing Flight
,”
High Speed Flight Propulsion Systems
,
S. N. B.
Murthy
and
E. T.
Curran
, eds., Vol. 137,
AIAA
.
2.
Powell
,
T.
and
Glickstein
,
M.
, 1988, “
Precooled Turbojet Engine Cycle For High Mach Number Applications
,”
AIAA/SAE/ASME/ASEE 24th Joint Propulsion Conference
.
3.
Rudakov
,
A.
, and
Balepin
,
V.
, 1991, “
Propulsion Systems With Air Precooling For Aerospaceplane
,” SAE Paper 911182.
4.
Sreenath
,
A.
, 1961, “
Studies of Turbojet Engines for Hypersonic Propulsion
,” Technical Report,
McGill University
, Department of Mechanical Engineering.
5.
Isomura
,
K.
, and
Omi
,
J.
, 2001, “
A Comparative Study of an ATREX Engine and a Turbo Jet Engine
,”
AIAA/ASME/SAE/ASEE 37th Joint Propulsion Conference
.
6.
Johnson
,
J.
, 1995, “
Variable Cycle Engine Developments
,”
Developments in High-Speed-Vehicle Propulsion Systems
.
7.
Shapiro
,
A.
, 1953,
The Dynamics and Thermodynamics of Compressible Fluid Flow
.
Ronald Press
,
New York
.
8.
Greitzer
,
E.
,
Tan
,
C.
, and
Graf
,
M.
, 2004,
Internal Flow Concepts and Applications
,
Cambridge University Press
,
Cambridge, UK
.
9.
Schlichting
,
A.
, 1987,
Boundary Layer Theory
,
McGraw-Hill
,
New York
.
10.
Cumpsty
,
N.
, 1989,
Compressor Aerodynamics
,
Longman
,
Cambridge, UK
.
11.
Shah
,
P. N.
, 2006, “
Novel Turbomachinery Concepts for Highly Integrated Airframe/Propulsion Systems
,” Ph.D. thesis, MIT, October.
12.
Reid
,
L.
, and
Moore
,
R.
, 1978,
Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82
, Technical Paper 1338,
NASA
, Cleveland, OH.
13.
Gong
,
Y.
,
Sirakov
,
B.
,
Epstein
,
A.
, and
Tan
,
C.
, 2004, “
Aerothermodynanics of Micro-Turbomachinery
,” ASME GT2004-53877.
14.
Kerrebrock
,
J. L.
, 1992,
Aircraft Engines and Gas Turbines
,
2nd ed.
MIT Press
,
Cambridge, MA
.
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