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TECHNICAL PAPERS

Improvement of a Film-Cooled Blade by Application of the Conjugate Calculation Technique

[+] Author and Article Information
Karsten Kusterer

 B&B-AGEMA GmbH, Julicher Strasse 338, D-52070 Aachen, Germanykusterer@bub-agema

Torsten Hagedorn

 B&B-AGEMA GmbH, Julicher Strasse 338, D-52070 Aachen, Germany

Dieter Bohn

Institute of Steam and Gas Turbines,  Aachen University, Templergraben 55, D-52056 Aachen, Germanypost-bohn@idg.rwth-aachen.de

Takao Sugimoto

Gas Turbine Research & Development Center,  Kawasaki Heavy Industries, Ltd., Akashi 673-8666, Japansugimoto̱t@khi.co.jp

Ryozo Tanaka

Gas Turbine Research & Development Center,  Kawasaki Heavy Industries, Ltd., Akashi 673-8666, Japan

J. Turbomach 128(3), 572-578 (Feb 01, 2005) (7 pages) doi:10.1115/1.2183314 History: Received October 01, 2004; Revised February 01, 2005

The conjugate calculation technique has been used for the three-dimensional thermal load prediction of a film-cooled test blade of a modern gas turbine. Thus, it becomes possible to take into account the interaction of internal flows, external flow, and heat transfer without the prescription of heat transfer coefficients. The numerical models consist of all internal flow passages and cooling hole rows, including shaped holes. Based on the results, deficiencies of the test configuration close to the leading edge region and in the blade tip region have been detected, which lead to hot spots and surface areas of high thermal load. These regions of high thermal load have been confirmed by thermal index paint measurements in good agreement to the conjugate calculation results. Based on the experimental and numerical results, recommendations for the improvement of the blade cooling were derived and an improved blade-cooling configuration has been designed. The conjugate calculation results, as well as new measurement data, show that the changes in the cooling design have been successful with respect to cooling performance. Regions of high thermal load have vanished, and effective cooling is reached for all critical parts of the test blade.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

Film-cooled test blade (CONF A)

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Figure 2

Internal system of test configuration (CONF A)

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Figure 3

Thermal index paint measurements and comparison to conjugate calculation results of CONF A

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Figure 4

Interaction of cooling jets

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Figure 5

Part of internal geometry for CONF B

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Figure 6

Radial distribution of nondimensional boundary conditions for blade inlet (CONF B)

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Figure 7

Fluid temperatures for blade leading edge in radial sections in aerothermal calculation (CONF B)

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Figure 8

Stream tube visualization of cooling jets (CONF B)

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Figure 9

Thermal index paint measurements and comparison to conjugate calculation results of CONF B

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