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The design of an air-cooled metallic high temperature radial turbineRecent trends in small advanced gas turbine engines call for higher turbine inlet temperatures. Advances in radial turbine technology have opened the way for a cooled metallic radial turbine capable of withstanding turbine inlet temperatures of 2500 F while meeting the challenge of high efficiency in this small flow size range. In response to this need, a small air-cooled radial turbine has been designed utilizing internal blade coolant passages. The coolant flow passage design is uniquely tailored to simultaneously meet rotor cooling needs and rotor fabrication constraints. The rotor flow-path design seeks to realize improved aerodynamic blade loading characteristics and high efficiency while satisfying rotor life requirements. An up-scaled version of the final engine rotor is currently under fabrication and, after instrumentation, will be tested in the warm turbine test facility at the NASA Lewis Research Center.
Document ID
19880057784
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Snyder, Philip H.
(General Motors Corp. Allison Gas Turbine Div., Indianapolis, IN, United States)
Roelke, Richard J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 88-2872
Accession Number
88A45011
Distribution Limits
Public
Copyright
Other

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