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Advanced radial inflow turbine rotor program: Design and dynamic testingThe advancement of small, cooled, radial inflow turbine technology in the area of operation at higher turbine inlet temperature is discussed. The first step was accomplished by designing, fabricating, and subjecting to limited mechanical testing an advanced gas generator rotating assembly comprising a radial inflow turbine and two-stage centrifugal compressor. The radial inflow turbine and second-stage compressor were designed as an integrally machined monorotor with turbine cooling taking place basically by conduction to the compressor. Design turbine inlet rotor gas temperature, rotational speed, and overall gas generator compressor pressure ratio were 1422 K (2560 R), 71,222 rpm, and 10/1 respectively. Mechanical testing on a fabricated rotating assembly and bearing system covered 1,000 cold start/stop cycles and three spins to 120 percent design speed (85,466 rpm).
Document ID
19770009119
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Rodgers, C.
(Solar San Diego, CA, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-135080
SOLAR-ER-2519
Accession Number
77N16062
Funding Number(s)
CONTRACT_GRANT: NAS3-18524
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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