Design study of turbomachine blades by optimization and inverse techniques

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

Research output: Contribution to conferencePaper

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)
DOIs
StatePublished - 1996
Event32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States
Duration: Jul 1 1996Jul 3 1996

Conference

Conference32nd 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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  • Cite this

    Nerurkar, A. C., Dang, T. Q., Reddy, E. S., & Reddy, D. R. (1996). Design study of turbomachine blades by optimization and inverse techniques. Paper presented at 32nd Joint Propulsion Conference and Exhibit, 1996, Lake Buena Vista, United States. https://doi.org/10.2514/6.1996-2555