Design study of turbomachine blades by optimization and inverse techniques

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

doi:10.2514/6.1996-2555

Design study of turbomachine blades by optimization and inverse techniques

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

Department of Mechanical & Aerospace Engineering

Research output: Contribution to conference › Paper › peer-review

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 language	English (US)
DOIs	https://doi.org/10.2514/6.1996-2555
State	Published - 1996
Event	32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States Duration: Jul 1 1996 → Jul 3 1996

Conference

Conference	32nd Joint Propulsion Conference and Exhibit, 1996
Country/Territory	United States
City	Lake Buena Vista
Period	7/1/96 → 7/3/96

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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10.2514/6.1996-2555

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title = "Design study of turbomachine blades by optimization and inverse techniques",

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.",

author = "Nerurkar, {A. C.} and Dang, {T. Q.} and Reddy, {E. S.} and Reddy, {D. R.}",

note = "Publisher Copyright: {\textcopyright} 1996, American Institute of Aeronautics and Astronautics, Inc.; 32nd Joint Propulsion Conference and Exhibit, 1996 ; Conference date: 01-07-1996 Through 03-07-1996",

year = "1996",

doi = "10.2514/6.1996-2555",

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TY - CONF

T1 - Design study of turbomachine blades by optimization and inverse techniques

AU - Nerurkar, A. C.

AU - Dang, T. Q.

AU - Reddy, E. S.

AU - Reddy, D. R.

PY - 1996

Y1 - 1996

N2 - 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.

AB - 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.

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T2 - 32nd Joint Propulsion Conference and Exhibit, 1996

Y2 - 1 July 1996 through 3 July 1996

ER -

Design study of turbomachine blades by optimization and inverse techniques

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