B207 COOLING TECHNOLOGIES OF TURBINE VANES AND BLADES FOR HIGH-TEMPERATURE GAS TURBINES(Gas turbine & forced convection heat transfer)
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概要
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The effectiveness of film cooling on turbine airfoils has been investigated experimentally using a low-speed wind tunnel cascade. Significant improvement in film cooling effectiveness is attained by adopting socalled "fan-shaped film cooling holes" rather than conventional circular hole geometry. The test results indicated good cooling characteristics for the case of a shaped film cooling geometry on turbine vane surfaces. For the design of cooled blades, an important factor is the effect of the rotating motion on the heat transfer coefficient for a serpentine flow passage with or without turbulence promoters. Corresponding heat transfer tests were conducted for a rotating flow passage in order to clarify this influence.
- 一般社団法人日本機械学会の論文
- 2000-10-01
著者
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Suenaga Kiyoshi
Takasago Research And Development Center Mitsubishi Heavy Industries Ltd
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Takeishi Ken-ichiro
Takasago Research And Development Center Mitsubishi Heavy Industries Ltd
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Takeishi Ken-ichiro
Takasago Research And Development Center Mitsubishi Heavy Industries Ltd.
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Tomita Yasuoki
Gas Turbine Designing Section, Takasago Machinery Works Mitsubishi Heavy Industries, Ltd.
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Tomita Yasuoki
Gas Turbine Designing Section Takasago Machinery Works Mitsubishi Heavy Industries Ltd.
関連論文
- Application of a 20kW Arc-Heated Wind Tunnel to Evaluation Tests of Wall Catalysis
- TS-48 An Experimental Study on the Film Cooling Effectiveness with Expanded Hole Geometry(Session C-1 Heat Transfer 1)
- TS-49 Large Eddy Simulation of a Two-Dimensional Impinging Jet on Flat Plate(Session C-2 Heat Transfer 2)
- B207 COOLING TECHNOLOGIES OF TURBINE VANES AND BLADES FOR HIGH-TEMPERATURE GAS TURBINES(Gas turbine & forced convection heat transfer)