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Experimental modeling of jet-ring turbine disk coolingThe experimental facility and some early results are described from a current research program modeling turbine disk cooling with multiple impinging jets, such as employed on the Space Shuttle Main Engine oxygen turbopump. The study is designed to obtain detailed local convection heat transfer rates on specially constructed turbine disk models that employ either multiple cooling jet impingement near the disk outer radius from a jet ring, or alternatively, single entrance coolant supply into the center of the disk cavity. Jet impingement is an effective scheme for cooling of turbine disks at or near the blade attachment region, but the heat transfer mechanisms and merits relative to other schemes are not well understood. The present study employs two specially constructed full scale plastic model disks, contoured and plane, together with the corresponding stators. Local heat transfer rates are determined by a computer vision system from the response of thin liquid crystal coatings applied to the disk test faces. The present results indicate that multiple jet impingement directed at the blade attachment region results in higher cooling rates in that region than does the same flow supplied to the disk center, but this conclusion must be regarded as tentative.
Document ID
19910034620
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Metzger, D. E.
(Arizona State Univ. Tempe, AZ, United States)
Kim, Y. W.
(Arizona State University Tempe, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-0343
Accession Number
91A19243
Distribution Limits
Public
Copyright
Other

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