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Heat transfer results and operational characteristics of the NASA Lewis Research Center hot section cascade test facilityThe NASA Lewis Research Center gas turbine hot section test facility has been developed to provide a real-engine environment with well known boundary conditions for the aerothermal performance evaluation/verification of computer design codes. The initial aerothermal research data obtained are presented and the operational characteristics of the facility are discussed. This facility is capable of testing at temperatures and pressures up to 1600 K and 18 atm which corresponds to a vane exit Reynolds number range of 0.5 x 1 million to 2.5 x 1 million based on vane chord. The component cooling air temperature can be independently modulated between 330 and 700 K providing gas-to-coolant temperature ratios similar to current engine application. Research instrumentation of the test components provide conventional pressure and temperature measurements as well as metal temperatures measured by IR-photography. The primary data acquisition mode is steady state through a 704 channel multiplexer/digitizer. The test facility was configured as an annular cascade of full coverage film cooled vanes for the initial series of research tests.
Document ID
19860037315
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gladden, H. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Yeh, F. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Fronek, D. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
March 1, 1985
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 85-GT-82
Accession Number
86A22053
Distribution Limits
Public
Copyright
Other

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