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TECHNICAL PAPERS

A Study of Advanced High-Loaded Transonic Turbine Airfoils

[+] Author and Article Information
Toyotaka Sonoda

Honda R&D Co. Ltd., Aircraft Engine R&D Center, Saitama 351-0193, Japan

Toshiyuki Arima

Honda R&D Co. Ltd., Wako Research Center, Saitama 351-0193, Japan

Markus Olhofer, Bernhard Sendhoff

 Honda Research Institute Europe GmbH, 63073 Offenbach, Germany

Friedrich Kost, P.-A. Giess

Institute of Propulsion Technology, German Aerospace Center (DLR), D-37073 Goettingen, Germany

http://www/dlr/de/at

J. Turbomach 128(4), 650-657 (Mar 01, 2004) (8 pages) doi:10.1115/1.2221325 History: Received October 01, 2003; Revised March 01, 2004

The development of high-performance turbine airfoils has been investigated under the condition of a supersonic exit Mach number. In order to obtain a new aerodynamic design concept for a high-loaded turbine rotor blade, we employed an evolutionary algorithm for numerical optimization. The target of the optimization method, which is called evolutionary strategy (ES), was the minimization of the total pressure loss and the deviation angle. The optimization process includes the representation of the airfoil geometry, the generation of the grid for a blade-to-blade computational fluid dynamics analysis, and a two-dimensional Navier-Stokes solver with a low-Re k-ε turbulence model in order to evaluate the performance. Some interesting aspects, for example, a double shock system, an early transition, and a redistribution of aerodynamic loading on blade surface, observed in the optimized airfoil, are discussed. The increased performance of the optimized blade has been confirmed by detailed experimental investigation, using conventional probes, hotfilms, and L2F system.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Baseline airfoil geometry and cascade parameters

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Figure 2

B-spline and initial blade

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Figure 3

Baseline (HL) and optimized (ES) airfoil geometries

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Figure 4

Computational grid used in numerical analysis: (a) overall; (b) enlargement

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Figure 5

Measurement planes inside cascade and downstream

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Figure 6

Schlieren photo of baseline cascade (HL) at Ma2is=1.2, α1=65deg: (a) EXP; (b) CFD

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Figure 7

Generation of separation bubble by a shock boundary layer interaction at Ma2is=1.5, α1=65deg: (a) Schlieren photo near impingement; (b) schematic figure of a shock/boundary layer interaction

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Figure 8

Schlieren photo of optimized cascade (ES) at Ma2is=1.2, α1=65deg: (a) EXP; (b) CFD

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Figure 9

Computed effect of dimple on airfoil surface Mach number distribution for optimized cascade (ES) at Ma2is=1.2, α1=65deg

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Figure 10

Measured airfoil surface Mach number distribution for baseline (HL) and optimized (ES) at design conditions at Ma2is=1.2, α1=65deg

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Figure 11

Comparison of CFD with EXP for airfoil Mach number distribution at Ma2is=1.2: (a) baseline (HL); (b) optimized (ES)

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Figure 12

Measured suction surface Mach number distribution around uncovered region for baseline HL airfoil at Ma2is=1.2

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Figure 13

Measured suction surface Mach number distribution around uncovered region for optimized ES airfoil at Ma2is=1.2

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Figure 14

Hot-film measurements along the suction surface of optimized ES airfoil at Ma2is=1.2, α1=65deg

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Figure 15

Measured total pressure loss coefficient in plane SS-37 at Ma2is=1.2, α1=65deg, x∕Cax=0.759

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Figure 16

Measured total pressure loss coefficient in plane SS-02 at Ma2is=1.2, α1=65deg, X∕Cax=0.993

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