Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine. I. Volute-manifold and stator performance

Technical Report · Fri May 01 04:00:00 EDT 1981

OSTI ID:6168674

Roelke, R J; Haas, J E

The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine of the Upgraded Gas-Turbine Engine was experimentally determined with cold air. The investigation was made to determine: the losses within the manifold; the flow conditions entering and leaving the stator; and the stator blading performance. The aerodynamic evaluation of the manifold and stator will subsequently be-used for evaluating the turbine rotor performance from overall stage data. The experimental conditions and measuring methods are described. The loss in total pressure in the inlet manifold ranged from 0.4 to 0.5%; however, the design swirl was not achieved near the endwalls. The underturning of the flow near the endwalls resulted in positive stator incidence as high as 19/sup 0/ at one circumferential position. Measurements also indicated a thick hub boundary layer at the stator inlet. The aftermixed stator efficiency between 20 and 90% span was generally equal to the design value of 0.965 but fell off appreciably at the endwalls. The overall aftermixed efficiency calculated for that part of the span surveyed (7 to 95%) was 0.959. An extrapolation of the survey measurements to the endwalls was made in an attempt to include the endwall losses. The overall aftermixed efficiency calculated from the extrapolated data was 0.936. An analysis of the factors contributing to the overall loss in kinetic energy (1-efficiency) showed the following elements: profile, trailing-edge drag, and mixing, 0.035; incidence, 0.006; endwall boundary layer, 0.010; and secondary flow, 0.014. Comparison of the subject stator showed that the small stators had comparable kinetic energy losses which were 50 to 100% more than the larger stators.

• Research Organization: National Aeronautics and Space Administration, Cocoa Beach, FL (USA). John F. Kennedy Space Center; AVRADCOM Research and Technology Labs., Cleveland, OH (USA)
• OSTI ID: 6168674
• Report Number(s): DOE/NASA/1011-34; NASA-TM-82682; ON: DE81028520
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AERODYNAMICS
AUTOMOBILES
COMPRESSORS
DATA
EFFICIENCY
ENGINES
EXPERIMENTAL DATA
FLUID MECHANICS
GAS TURBINE ENGINES
GAS TURBINES
HEAT ENGINES
INFORMATION
INTERNAL COMBUSTION ENGINES
LOSSES
MACHINERY
MECHANICS
NUMERICAL DATA
PERFORMANCE TESTING
TESTING
TURBINES
TURBOMACHINERY
VEHICLES