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Prediction of the aerodynamic environment and heat transfer for rotor-stator configurationsA numerical study of the aerodynamic and thermal environment associated with axial turbine stages is presented. Computations were performed using a modification of the unsteady viscous code, ROTORI, and an improved version of the steady inviscid cascade system, MERIDL-TSONIC, coupled with boundary layer codes, BLAYER and STAN5. Two different turbine stages were analyzed: the first stage of the United Technologies Research Center Large Scale Rotating Rig (LSRR) and the first stage of the Space Shuttle Main Engine (SSME) high pressure fuel turbopump turbine. The time-averaged airfoil midspan pressure and heat transfer profiles were predicted for numerous thermal boundary conditions including adiabatic wall, prescribed surface temperature, and prescribed heat flux. Computed solutions are compared with each other and with experimental data in the case of the LSRR calculations. Modified ROTORI predictions of unsteady pressure envelopes and instantaneous contour plots are also presented. Relative merits of the two computational approaches are discussed.
Document ID
19900036752
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Griffin, L. W.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Mcconnaughey, H. V.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 89-GT-89
Accession Number
90A23807
Funding Number(s)
CONTRACT_GRANT: NAS8-36284
Distribution Limits
Public
Copyright
Other

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