NDLI: Heat flux measurement in ssme turbine blade tester

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Heat flux measurement in ssme turbine blade tester

Content Provider	NASA Technical Reports Server (NTRS)
Author	Liebert, Curt H.
Copyright Year	1990
Description	Surface heat flux values were measured in the turbine blade thermal cycling tester located at NASA-Marshall. This is the first time heat flux has been measured in a space shuttle main engine turbopump environment. Plots of transient and quasi-steady state heat flux data over a range of about 0 to 15 MW/sq m are presented. Data were obtained with a miniature heat flux gage device developed at NASA-Lewis. The results from these tests are being incorporated into turbine design models. Also, these gages are being considered for airfoil surface heat flux measurement on turbine vanes mounted in SSME turbopump test bed engine nozzles at Marshall. Heat flux effects that might be observed on degraded vanes are discussed.
File Size	9733478
Page Count	19
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910001892
Archival Resource Key	ark:/13960/t6644ng5r
Language	English
Publisher Date	1990-11-01
Access Restriction	Open
Subject Keyword	Flux Quantization Turbine Blades Engine Design Thermal Cycling Tests Airfoils Quasi-steady States Engine Tests Heat Measurement High Temperature Environments Heat Flux Gas Mixtures High Pressure Turbine Pumps Space Shuttle Main Engine Vanes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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