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Computation of the temperature distribution in cooled radial inflow turbine guide vanesA two-dimensional finite-difference numerical technique is presented to determine the temperature distribution of an internally-cooled blade of radial turbine guide vanes. A simple convection cooling is assumed inside the guide vane. Such an arrangement results in relatively small cooling effectiveness at the leading edge and at the trailing edge. Heat transfer augmentation in these critical areas may be achieved by using impingement jets and film cooling. A computer program is written in Fortran IV for IBM 370/165 computer.
Document ID
19770045742
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tabakoff, W.
(Cincinnati Univ. OH, United States)
Hosny, W.
(Cincinnati Univ. OH, United States)
Hamed, A.
(Cincinnati, University Cincinnati, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
March 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ASME PAPER 77-GT-83
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Philadelphia, PA
Start Date: March 27, 1977
End Date: March 31, 1977
Sponsors: American Society of Mechanical Engineers
Accession Number
77A28594
Funding Number(s)
CONTRACT_GRANT: NAS2-7850
Distribution Limits
Public
Copyright
Other

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