NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Turbine airfoil gas side heat transferWork is currently underway to develop and characterize an analytical approach, based on boundary layer theory, for predicting the effects of leading edge (showerhead) film cooling on downstream gas side heat transfer rates. Parallel to this work, experiments are being conducted to build a relevant data base for present and future methods verification.
Document ID
19870001786
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Turner, E. R. (General Motors Corp. Detroit, MI, United States)
Date Acquired
August 13, 2013
Publication Date
October 1, 1984
Publication Information
Publication: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
87N11219
Funding Number(s)
CONTRACT_GRANT: NAS3-23695
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19870001747Collected WorksTurbine Engine Hot Section Technology, 1984
No Preview Available