Design study of turbomachine blades by optimization and inverse techniques

A. C. Nerurkar, Thong Q Dang, E. S. Reddy, D. R. Reddy

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A design method based on parametric optimization techniques coupled directly with a CFD analysis code for turbomachine blades is presented. The blade geometry is parameterized and the optimization method is used to search for a blade geometry that will minimize a design objective function. The design flow criteria employed in this study include matching a prescribed swirl schedule in the bladed region (unconstrained optimization) and minimizing the stagnation pressure loss due to shock waves for a prescribed overall change in swirl across the blade row (constrained optimization). The method is demonstrated for two-dimensional cascaded blades in the transonic- and supersonic-flow regimes for inviscid flows. A comparative study of the blades designed by the optimization technique and an existing inverse method is presented.

Original languageEnglish (US)
Title of host publication32nd Joint Propulsion Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9780000000002
StatePublished - 1996
Event32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States
Duration: Jul 1 1996Jul 3 1996

Other

Other32nd Joint Propulsion Conference and Exhibit, 1996
CountryUnited States
CityLake Buena Vista
Period7/1/967/3/96

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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    Nerurkar, A. C., Dang, T. Q., Reddy, E. S., & Reddy, D. R. (1996). Design study of turbomachine blades by optimization and inverse techniques. In 32nd Joint Propulsion Conference and Exhibit American Institute of Aeronautics and Astronautics Inc, AIAA.