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Analytical investigation of chord size and cooling methods on turbine blade cooling requirements. Book 1: Sections 1 through 8 and appendixes A through IA study was conducted to determine the effect of chord size on air cooled turbine blades. In the preliminary design phase, eight turbine blade cooling configurations in 0.75-in., 1.0-in., and 1.5-in. chord sizes were analyzed to determine the maximum turbine inlet temperature capabilities. A pin fin convection cooled configuration and a film-impingement cooled configuration were selected for a final design analysis in which the maximum turbine inlet temperature was determined as a function of the cooling air inlet temperature and the turbine inlet total pressure for each of the three chord sizes. The cooling air flow requirements were also determined for a varying cooling air inlet temperature with a constant turbine inlet temperature. It was determined that allowable turbine inlet temperature increases with increasing chord for the convection cooled and transpiration cooled designs, however, the film-convection cooled designs did not have a significant change in turbine inlet temperature with chord.
Document ID
19730009082
Document Type
Contractor Report (CR)
Authors
Faulkner, F. E. (AiResearch Mfg. Co. Torrance, CA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1971
Subject Category
PROPULSION SYSTEMS
Report/Patent Number
NASA-CR-120882-BK-1
AIRESEARCH-71-7487-BK-1
Funding Number(s)
CONTRACT_GRANT: NAS3-13205
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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