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Integration of rocket turbine design and analysis through computer graphicsAn interactive approach with engineering computer graphics is used to integrate the design and analysis processes of a rocket engine turbine into a progressive and iterative design procedure. The processes are interconnected through pre- and postprocessors. The graphics are used to generate the blade profiles, their stacking, finite element generation, and analysis presentation through color graphics. Steps of the design process discussed include pitch-line design, axisymmetric hub-to-tip meridional design, and quasi-three-dimensional analysis. The viscous two- and three-dimensional analysis codes are executed after acceptable designs are achieved and estimates of initial losses are confirmed.
Document ID
19880060806
Document Type
Conference Paper
Authors
Hsu, Wayne (Rockwell International Corp. Canoga Park, CA, United States)
Boynton, Jim (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 88-2991
Funding Number(s)
CONTRACT_GRANT: NAS8-40000
Distribution Limits
Public
Copyright
Other