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The effect of unsteadiness on the time-mean thermal loads in a turbine stageTwo steady numerical analysis methods and one unsteady method are used to study the viscous three-dimensional flow in the middle stage of the Pratt & Whitney alternate design Space Shuttle Main Engine fuel turbine. The principal characteristic of this flow is that the secondary flows generated in the rotor blade reconfigure a radial inlet total temperature distortion into one with a pitchwise exit hot streak distortion. Secondary flows in the following vane redistribute the radial variation while unsteadiness causes a segregation of hot and cold flow from the hot streak within the vane. Such redistribution and segregation can lead to unexpected thermal loads and reduced durability. The physical phenomena and the ability of a steady analysis to capture them are investigated by performing a numerical experiment whereby the results of the two steady analysis methods are compared to the time-mean of the unsteady simulation. The flow physics related to the segregation and mixing of total temperature are discussed.
Document ID
19950062055
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kirtley, K. R.
(Sverdrup Technology, Inc. Brookpark, OH, United States)
Celestina, M. L.
(Sverdrup Technology, Inc. Brookpark, OH, United States)
Adamczyk, J. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
ISSN: 0148-7191
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
SAE PAPER 931375
Meeting Information
Meeting: SAE, Aerospace Atlantic Conference & Exposition
Location: Dayton, OH
Country: United States
Start Date: April 20, 1993
End Date: April 23, 1993
Accession Number
95A93654
Funding Number(s)
CONTRACT_GRANT: NAS3-25266
Distribution Limits
Public
Copyright
Other

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