Publication:
A multidisciplinary algorithm for the 3-D design optimization of transonic axial compressor blades

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Authors
Jones, James A.
Subjects
Design Optimization
Transonic Fan Blades
Bezier Geometry Package
Advisors
Shreeve, Raymond P.
Date of Issue
2002-06
Date
June 2002
Publisher
Monterey, California: Naval Postgraduate School
Language
Abstract
A new, multidisciplinary algorithm for the CFD design optimization of turbomachinery blades is presented. It departs from existing techniques in that it uses a simple, previously-developed Bezier geometry representation (BLADE-3D) that can be easily manipulated to achieve true 3-D changes in blade shape. The algorithm incorporates zero and first-order optimization techniques including sensitivity analyses and one-dimensional search methodology. It features an iterative finite element structural analysis as well as a cold shape correction procedure to ensure that the resulting blade meets steady-stress structural requirements. The process was applied to two different transonic fan designs - the Sanger rotor designed for the NPS Turbomachinery Laboratory and NASA Rotor 67, otherwise known as the 'NASA Fan'. The optimization objectives for the two designs were mass flow rate and polytropic efficiency respectively. Results for the Sanger rotor effort yielded an 8.1 % improvement in mass flow rate, a 5% improvement in total pressure ratio, and a 0.9 % increase in adiabatic efficiency. Application to the NASA Fan resulted in a 2.5 % increase in polytropic efficiency. The results validate the utility of the BLADE-3D Bezier geometry package for use in future development of automated optimization routines for turbomachinery blade design.
Type
Description
Series/Report No
Department
Aeronautics and Astronautics
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
xviii, 164 p. : ill. (some col.) ; 28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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