Heat flux measurement in SSME turbine blade tester
- Liebert, Curt H.
- Nov 1, 1990.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available. and Free-to-read Unrestricted online access
- 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.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19910001892., Accession ID: 91N11205., E-5719., NAS 1.15:103274., NASA-TM-103274., and Annual Conference on Health Monitoring for Space Propulsion Systems; 14-15 Nov. 1990; Cincinnati, OH; United States.
- No Copyright.
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