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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 engineAn experimental evaluation of the aerodynamic performance of the axial flow, variable area stator power turbine stage for the Department of Energy upgraded automotive gas turbine engine was conducted in cold air. The interstage transition duct, the variable area stator, the rotor, and the exit diffuser were included in the evaluation of the turbine stage. The measured total blading efficiency was 0.096 less than the design value of 0.85. Large radial gradients in flow conditions were found at the exit of the interstage duct that adversely affected power turbine performance. Although power turbine efficiency was less than design, the turbine operating line corresponding to the steady state road load power curve was within 0.02 of the maximum available stage efficiency at any given speed.
Document ID
19820013319
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mclallin, K. L. (NASA Lewis Research Center Cleveland, OH, United States)
Kofskey, M. G. (NASA Lewis Research Center Cleveland, OH, United States)
Wong, R. Y. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-899
NAS 1.15:82644
DOE/NASA/51040-30
NASA-TM-82644
Accession Number
82N21193
Funding Number(s)
PROJECT: RTOP 778-32-01
CONTRACT_GRANT: DE-AI01-77CS-51040
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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