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Experimental flow coefficients of a full-coverage film-cooled-vane chamberAmbient- and elevated-temperature flow tests were performed on a four-times-actual-size model of an impingement- and film-cooled segment of a core engine turbine vane. Tests were conducted with the impingement and film cooling plates combined to form a chamber and also with each of the individual separated plates. For the combined tests, the proximity of the film cooling plate affected the flow of coolant through the impingement plate, but not conversely. Impingement flow is presented in terms of a discharge coefficient, and the film cooling flow discharging into still air with no main stream gas flow is presented in terms of a total pressure-loss coefficient. The effects of main stream gas flow on discharge from the film cooling holes are evaluated as a function of coolant to main-stream gas momentum flux ratio. A smoothing technique is developed that identifies and helps reduce flow measurement data scatter.
Document ID
19770025209
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Meitner, P. L. (Army Air Mobility Research and Development Lab. Cleveland, Ohio, United States)
Hippensteele, S. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TP-1036
E-9146
Accession Number
77N32153
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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