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Numerical evaluation of single central jet for turbine disk coolingThe cooling arrangement of the Space Shuttle Main Engine High Pressure Oxidizer Turbopump (HPOTP) incorporates two jet rings, each of which produces 19 high-velocity coolant jets. At some operating conditions, the frequency of excitation associated with the 19 jets coincides with the natural frequency of the turbine blades, contributing to fatigue cracking of blade shanks. In this paper, an alternate turbine disk cooling arrangement, applicable to disk faces of zero hub radius, is evaluated, which consists of a single coolant jet impinging at the center of the turbine disk. Results of the CFD analysis show that replacing the jet ring with a single central coolant jet in the HPOTP leads to an acceptable thermal environment at the disk rim. Based on the predictions of flow and temperature fields for operating conditions, the single central jet cooling system was recommended for implementation into the development program of the Technology Test Bed Engine at NASA Marshall Space Flight Center.
Document ID
19930070635
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Subbaraman, M. R.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Hadid, A. H.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Mcconnaughey, P. K.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: Rotating machinery - Transport phenomena; Proceedings of the 3rd International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC-3), Honolulu, HI, Apr. 1-4, 1990 (A93-54
Publisher: Hemisphere Publishing Corp.
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
93A54632
Distribution Limits
Public
Copyright
Other

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