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3-d thermal analysis using finite difference technique with finite element model for improved design of components of rocket engine turbomachines for space shuttle main engine ssmeThree-dimensional finite element models were generated and transferred into three-dimensional finite difference models to perform transient thermal analyses for the SSME high pressure fuel turbopump's first stage nozzles and rotor blades. STANCOOL was chosen to calculate the heat transfer characteristics (HTCs) around the airfoils, and endwall effects were included at the intersections of the airfoils and platforms for the steady-state boundary conditions. Free and forced convection due to rotation effects were also considered in hollow cores. Transient HTCs were calculated by taking ratios of the steady-state values based on the flow rates and fluid properties calculated at each time slice. Results are presented for both transient plots and three-dimensional color contour isotherm plots; they were also converted into universal files to be used for FEM stress analyses.
Document ID
19880060807
Document Type
Conference Paper
Authors
Sohn, Kiho D.
(Rockwell International Corp. Canoga Park, CA, United States)
Ip, Shek-Se P.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 88-2993
Funding Number(s)
CONTRACT_GRANT: NAS8-40000
Distribution Limits
Public
Copyright
Other