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Algorithm for calculating turbine cooling flow and the resulting decrease in turbine efficiencyAn algorithm is presented for calculating both the quantity of compressor bleed flow required to cool the turbine and the decrease in turbine efficiency caused by the injection of cooling air into the gas stream. The algorithm, which is intended for an axial flow, air routine in a properly written thermodynamic cycle code. Ten different cooling configurations are available for each row of cooled airfoils in the turbine. Results from the algorithm are substantiated by comparison with flows predicted by major engine manufacturers for given bulk metal temperatures and given cooling configurations. A list of definitions for the terms in the subroutine is presented.
Document ID
19800011581
Document Type
Technical Memorandum (TM)
Authors
Gauntner, J. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1980
Subject Category
Computer Programming And Software
Report/Patent Number
NASA-TM-81453
E-384
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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