Research Papers

Multipoint Design Optimization of a Transonic Compressor Blade by Using an Adjoint Method

[+] Author and Article Information
Jiaqi Luo

Postdoctoral Researcher
e-mail: jiaqil81@gmail.com

Chao Zhou

Assistant Professor
e-mail: czhou@pku.edu.cn
College of Engineering,
Peking University,
Beijing 100871, China

Feng Liu

Department of Mechanical and
Aerospace Engineering,
University of California,
Irvine, CA 92697-3975
e-mail: fliu@uci.edu

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 29, 2013; final manuscript received July 7, 2013; published online September 27, 2013. Editor: Ronald Bunker.

J. Turbomach 136(5), 051005 (Sep 27, 2013) (10 pages) Paper No: TURBO-13-1087; doi: 10.1115/1.4025164 History: Received May 29, 2013; Revised July 07, 2013

This paper presents the application of a viscous adjoint method to the multipoint design optimization of a rotor blade through blade profiling. The adjoint method requires about twice the computational effort of the flow solution to obtain the complete gradient information at each operating condition, regardless of the number of design parameters. NASA Rotor 67 is redesigned through blade profiling. A single point design optimization is first performed to verify the effectiveness and feasibility of the optimization method. Then in order to improve the performance for a wide range of operating conditions, the blade is redesigned at three operating conditions: near peak efficiency, near stall, and near choke. Entropy production through the blade row combined with the constraints of mass flow rate and total pressure ratio is used as the objective function. The design results are presented in detail and the effects of blade profiling on performance improvement and shock/tip-leakage interaction are examined.

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Fig. 1

Comparisons of operating characteristics of Rotor 67

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Fig. 2

Spanwise distributions of total pressure ratio, total temperature ratio and flow turning

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Fig. 3

Blade profiles perturbed by shape function

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Fig. 4

Comparisons of gradients

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Fig. 5

Contours of relative isentropic Mach number on the blade surface (a) pressure side and (b) suction side

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Fig. 6

Blade profiles and distributions of relative isentropic Mach number at different spans

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Fig. 7

Spanwise distributions of (a) total pressure ratio and adiabatic efficiency and (b) total temperature ratio and flow turning

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Fig. 8

Contours of relative Mach number at different axial locations (a) 40% chord, (b) 80% chord, and (c) 110% chord

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Fig. 9

Pressure contours on a blade-to-blade stream surface at the blade tip (a) reference and (b) optimized

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Fig. 10

Operating characteristics of the reference and the optimized blades (a) total pressure ratio and (b) adiabatic efficiency

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Fig. 11

Contours of relative Mach number on a blade-to-blade stream surface at the blade tip (a) near P.E. and (b) near stall




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