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Heat-transfer and surface-pressure measurements for the SSME fuel-side turbopump turbineDetailed heat flux and surface pressure distribution on the first-stage vane and blade of the Space Shuttle Main Engine fuel side turbopump turbine are examined. The specific turbine being utilized for the study is a combination of actual engine hardware and reproduced hardware consistent with that being used at NASA-Marshall for the initial measurements in their newly constructed blow-down turbine test facility. The facility is of the short duration shock tunnel variety, which permits use of thin film thermometers which are used to measure the surface temperature histories at prescribed locations on the turbine component parts. Heat flux values are then inferred from the temperature histories using standard data reduction procedures. The measurement program is described in detail.
Document ID
19910015022
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dunn, Michael G. (Calspan-Buffalo Univ. Research Center NY, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1989
Publication Information
Publication: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems
Subject Category
Mechanical Engineering
Accession Number
91N24335
Funding Number(s)
CONTRACT_GRANT: NAG3-581
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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