Cold-air performance of a 15. 41-cm-tip-diameter axial-flow power turbine with variable-area stator designed for a 75-kW automotive gas-turbine engine

Technical Report · Mon Feb 01 04:00:00 EST 1982

OSTI ID:5267443

McLallin, K L; Kofskey, M G; Wong, R Y

Experimentally determined performance data are presented for the power turbine stage of the Department of Energy upgraded automotive gas turbine engine. The power turbine is a single-stage, axial-flow design with pivotable vanes to vary stator area for engine control and braking. The stage performance evaluation was performed with dry air at nominal stator inlet conditions of 320/sup 0/K and 0.409 atmosphere. At these conditions a Reynolds number equal to that at actual engine conditions was obtaind at the equivalent design values of speed and pressure ratio. The results are presented for stator throat areas of 79.3, 100.0, 117.7, and 135.6 percent of design in terms of mass flow rate, torque, speed, power, and efficiency. Stator performance is presented in terms of mass flow rate and stator exit torque, which was measured with a stationary paddlewheel rotor. Interstage duct performance and exit diffuser performance are presented in terms of wall static pressures. The results of radial surveys of flow angle, total temperature, and total pressure are presented at the stator inlet and the rotor exit.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• DOE Contract Number: AI01-77CS51040
• OSTI ID: 5267443
• Report Number(s): DOE/NASA/51040-30; NASA-TM-82644; ON: DE82012558
• Country of Publication: United States
• Language: English

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33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
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AIR FLOW
AUTOMOBILES
DATA
DESIGN
EFFICIENCY
ENGINES
EXPERIMENTAL DATA
FLOW RATE
FLUID FLOW
FLUID MECHANICS
GAS FLOW
GAS TURBINE ENGINES
GAS TURBINES
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NUMERICAL DATA
OPERATION
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TURBINES
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VEHICLES