Centrifugal compressor return channel shape optimization using adjoint method

Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.

Bibliographic Details
Main Author: Guo, Wei, S.M. Massachusetts Institute of Technology
Other Authors: Qiqi Wang and Edward M. Greitzer.
Format: Thesis
Language:eng
Published: Massachusetts Institute of Technology 2014
Subjects:
Online Access:http://hdl.handle.net/1721.1/85801
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author Guo, Wei, S.M. Massachusetts Institute of Technology
author2 Qiqi Wang and Edward M. Greitzer.
author_facet Qiqi Wang and Edward M. Greitzer.
Guo, Wei, S.M. Massachusetts Institute of Technology
author_sort Guo, Wei, S.M. Massachusetts Institute of Technology
collection MIT
description Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.
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spelling mit-1721.1/858012019-04-09T16:27:47Z Centrifugal compressor return channel shape optimization using adjoint method Guo, Wei, S.M. Massachusetts Institute of Technology Qiqi Wang and Edward M. Greitzer. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Aeronautics and Astronautics. Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013. Cataloged from PDF version of thesis. Includes bibliographical references (pages 59-60). This thesis describes the construction of an automated gradient-based optimization process using the adjoint method and its application to centrifugal compressor return channel loss reduction. A proper objective function definition and a generalized geometry parametrization and manipulation algorithm were developed, and the appropriate adjoint equations and boundary conditions were derived for internal flow of an axisymmetric incompressible laminar flow. The adjoint-based gradient calculation was then validated against finite-difference calculations and embedded in a quasi- Newton optimization algorithm. An optimal design was proposed, which achieved an approximately 5% performance improvement compared to the baseline design in an incompressible laminar flow. The geometry was assessed in a compressible turbulent flow at the actual Mach number and Reynolds number and found to yield a 11% performance improvement for an axisymmetric channel with a previously optimized geometry. by Wei Guo. S.M. 2014-03-19T15:46:17Z 2014-03-19T15:46:17Z 2013 2013 Thesis http://hdl.handle.net/1721.1/85801 872104516 eng M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 60 pages application/pdf Massachusetts Institute of Technology
spellingShingle Aeronautics and Astronautics.
Guo, Wei, S.M. Massachusetts Institute of Technology
Centrifugal compressor return channel shape optimization using adjoint method
title Centrifugal compressor return channel shape optimization using adjoint method
title_full Centrifugal compressor return channel shape optimization using adjoint method
title_fullStr Centrifugal compressor return channel shape optimization using adjoint method
title_full_unstemmed Centrifugal compressor return channel shape optimization using adjoint method
title_short Centrifugal compressor return channel shape optimization using adjoint method
title_sort centrifugal compressor return channel shape optimization using adjoint method
topic Aeronautics and Astronautics.
url http://hdl.handle.net/1721.1/85801
work_keys_str_mv AT guoweismmassachusettsinstituteoftechnology centrifugalcompressorreturnchannelshapeoptimizationusingadjointmethod