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Research Papers

A Database of Optimal Airfoils for Axial Compressor Throughflow Design

[+] Author and Article Information
Markus Schnoes

German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
e-mail: markus.schnoes@dlr.de

Eberhard Nicke

German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 16, 2016; final manuscript received October 4, 2016; published online January 24, 2017. Editor: Kenneth Hall.

J. Turbomach 139(5), 051008 (Jan 24, 2017) (9 pages) Paper No: TURBO-16-1243; doi: 10.1115/1.4035075 History: Received September 16, 2016; Revised October 04, 2016

Airfoil shapes tailored to specific inflow conditions and loading requirements can offer a significant performance potential over classic airfoil shapes. However, their optimal operating range has to be matched thoroughly to the overall compressor layout. This paper describes methods to organize a large set of optimized airfoils in a database and its application in the throughflow design. Optimized airfoils are structured in five dimensions: inlet Mach number, blade stagger angle, pitch–chord ratio, maximum thickness–chord ratio, and a parameter for aerodynamic loading. In this space, a high number of airfoil geometries are generated by means of numerical optimization. During the optimization of each airfoil, the performance at design and off-design conditions is evaluated with the blade-to-blade flow solver MISES. Together with the airfoil geometry, the database stores automatically calibrated correlations which describe the cascade performance in throughflow calculation. Based on these methods, two subsonic stages of a 4.5-stage transonic research compressor are redesigned. Performance of the baseline and updated geometry is evaluated with 3D CFD. The overall approach offers accurate throughflow design incorporating optimized airfoil shapes and a fast transition from throughflow to 3D CFD design.

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Figures

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Fig. 1

Design parameters of airfoil geometry

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Fig. 2

Blade geometry and comparison between correlation and MISES calculations for a typical stator profile

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Fig. 3

Definition of operating points for optimization

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Fig. 5

Airfoil geometry, computed isentropic Mach number, and loss characteristic for three DLR-Rig250 airfoils in comparison to airfoils interpolated from the presented database

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Fig. 4

Variation of blade geometry for each design requirement while maintaining a constant value for the remaining requirements

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Fig. 6

Speed lines of each configuration at reference speed

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Fig. 7

Stage total pressure ratios and efficiencies for each configuration at design point

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Fig. 8

Inflow angles, outflow angles, and working ranges given by correlation for both rear stages and each configuration at design point

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