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The effects of Reynolds number, rotor incidence angle and surface roughness on the heat transfer distribution in a large-scale turbine rotor passageA combined experimental and computational program was conducted to examine the heat transfer distribution in a turbine rotor passage geometrically similar to the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP). Heat transfer was measured and computed for both the full span suction and pressure surfaces of the rotor airfoil as well as for the hub endwall surface. The objective of the program was to provide a benchmark-quality database for the assessment of rotor heat transfer computational techniques. The experimental portion of the study was conducted in a large scale, ambient temperature, rotating turbine model. The computational portion consisted of the application of a well-posed parabolized Navier-Stokes analysis of the calculation of the three-dimensional viscous flow through ducts simulating a gas turbine package. The results of this assessment indicate that the procedure has the potential to predict the aerodynamics and the heat transfer in a gas turbine passage and can be used to develop detailed three dimensional turbulence models for the prediction of skin friction and heat transfer in complex three dimensional flow passages.
Document ID
19920002079
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Blair, M. F. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.26:184260
NASA-CR-184260
UTRC/R91-970057-3
Accession Number
92N11297
Funding Number(s)
CONTRACT_GRANT: NAS8-38870
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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