Constrained Adjoint-Based Aerodynamic Shape Optimization of a Single-Stage Transonic Compressor

Author:

Walther Benjamin1,Nadarajah Siva2

Affiliation:

1. e-mail:

2. e-mail:  Department of Mechanical Engineering, McGill University, Montreal, Quebec, H3A 2S6, Canada

Abstract

This paper develops a discrete adjoint formulation for the constrained aerodynamic shape optimization in a multistage turbomachinery environment. The adjoint approach for viscous internal flow problems and the corresponding adjoint boundary conditions are discussed. To allow for a concurrent rotor/stator optimization, a nonreflective adjoint mixing-plane formulation is proposed. A sequential-quadratic programming algorithm is utilized to determine an improved airfoil shape based on the objective function gradient provided by the adjoint solution. The functionality of the proposed optimization method is demonstrated by the redesign of a midspan section of a single-stage transonic compressor. The objective is to maximize the isentropic efficiency while constraining the mass flow rate and the total pressure ratio.

Publisher

ASME International

Subject

Mechanical Engineering

Reference32 articles.

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2. Jameson, A., 1995 “Optimum Aerodynamic Design Using CFD and Control Theory,” AIAA 12th Computational Fluid Dynamics Conference, AIAA Paper No. 1995–1729.

3. An Introduction to the Adjoint Approach to Design;Flow, Turbul. Combust,2000

4. Multi-Element High-Lift Configuration Design Optimization Using Viscous Continuous Adjoint Method;Journal of Aircr.,2004

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