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Structural Tailoring of SSME Blades (vanes)The engine blade design optimization program STAEBL (Structural Tailoring of Engine Blades) is available at the NASA Lewis computer facility. The analysis capabilities of this program were extended to typical loading conditions for SSME turbopump blades including thermal and pressure loading. Input files for representative SSME blade designs were developed and sample optimization studies for these blades completed. The structural tailoring program combines a general optimization package and a finite element blade analysis package. The analysis package's capabilities include natural frequency, maximum stress, and forced response computation, and fatigue life and flutter analysis. Optimization is performed using the feasible directions method. The current design is modified by perturbing the design variables so that the design constraints are satisfied while the objective function, such as blade weight, is reduced at the maximum rate. The program's geometric design variables include blade thickness distribution, thickness to chord ratios, and root chord.
Document ID
19850019648
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rubinstein, R.
(Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1985
Publication Information
Publication: NASA. Lewis Research Center Struct. Integrity and Durability of Reusable Space Propulsion Systems
Subject Category
Structural Mechanics
Accession Number
85N27960
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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