2007 Fiscal Year Final Research Report Summary
Study on Advanced Cooling Configurations for Gas Turbine Hot Parts
| Project/Area Number |
17360462
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Energy engineering
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| Research Institution | Tokyo University of Agriculture and Technology |
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Principal Investigator |
YOSHIDA Toyoaki Tokyo University of Agriculture and Technology, Institute of Symbiotic Science and Technology, Professor (60358497)
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| Co-Investigator(Kenkyū-buntansha) |
FUKUYAMA Yoshitaka Japan Aerospace Exploration Agency, Institute of Aerospace Technology, Manager for Research Planning (20371099)
YAMANE Takashi Japan Aerospace Exploration Agency, Aviation Program Group, Section Leader (30358501)
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| Project Period (FY) |
2005 – 2007
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| Keywords | Energy Efficient Engine / Aerospace Engineering / Energy Saving / Thermal Engineering / Suppression of CO_2 Emission / Jet Engine / Gas Turbine / Cooling Technology |
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| Research Abstract |
1. Basic Experimental Analyses
Two kinds of advanced cooling configurations for turbine blades, transpiration (integrated) cooling configuration and multi-slot cooling configuration, were adopted as research subjects. At the Tokyo University of Agriculture and Technology (TAT), experimental aerodynamic analyses were conducted with the use of enlarged transparent test models made of acrylic resin, a low-speed wind tunnel and a blower for cooling air supply. Reynolds number and representative length of the cooling configuration were systematically changed. Detailed cooling air flow fields were observed by applying the Particle Image Velocimetry (PIV) method which utilizes laser light sheets, a high-speed camera and image processing software together with a computer system. By the flow observation, the relation between a cooling air velocity field and a cooling configuration was made clear and thus cooling effectiveness of the test model was well explained by the feature of the relation. T
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hese flow field observations constituted a useful data base for the development of advanced air-cooled turbine blades. As for the multi-slot cooling configuration, numerical analyses of cooling air flow fields were also conducted. By comparing the resulting flow fields from the experimental and numerical analyses, usefulness of the present numerical work was qualitatively verified.
2. Heat Transfer Analyses under Simulated Practical Conditions
At the Japan Aerospace Exploration Agency (JAXA), heat transfer analyses were conducted for the above two cooling configurations under simulated practical conditions with the use of a high-temperature wind tunnel. Flat plate test models made of stainless steel were used. Wall surface temperature was mainly measured with an infrared camera. As to the integrated cooling configuration, semicircle test models were also investigated that simulate the shape of the leading edge of turbine blades. As to flat plate film cooling, a constituting member of the integrated cooling configuration, conjugate numerical analyses that solved velocity and temperature fields together were performed. At the THI Corporation numerical analyses were also conducted for the two cooling configurations under the same conditions as those of the experiments with the use of commercially available software. From these analyses, excellent cooling configurations were investigated and useful data base was constituted.
These results were published in the journals of the Gas Turbine Society of Japan and presented in several domestic lecture meetings and international symposia. As for the multi-slot cooling configuration, a patent was applied to the Japan Patent Office. Less
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Research Products
(24 results)
