Verification of Thermal Models of Internally Cooled Gas Turbine Blades
Numerical simulation of temperature field of cooled turbine blades is a required element of gas turbine engine design process. The verification is usually performed on the basis of results of test of full-size blade prototype on a gas-dynamic test bench. A method of calorimetric measurement in a mol...
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| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2018-01-01
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| Series: | International Journal of Rotating Machinery |
| Online Access: | http://dx.doi.org/10.1155/2018/6780137 |
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| _version_ | 1832549909078736896 |
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| author | Igor Shevchenko Nikolay Rogalev Andrey Rogalev Andrey Vegera Nikolay Bychkov |
| author_facet | Igor Shevchenko Nikolay Rogalev Andrey Rogalev Andrey Vegera Nikolay Bychkov |
| author_sort | Igor Shevchenko |
| collection | DOAJ |
| description | Numerical simulation of temperature field of cooled turbine blades is a required element of gas turbine engine design process. The verification is usually performed on the basis of results of test of full-size blade prototype on a gas-dynamic test bench. A method of calorimetric measurement in a molten metal thermostat for verification of a thermal model of cooled blade is proposed in this paper. The method allows obtaining local values of heat flux in each point of blade surface within a single experiment. The error of determination of local heat transfer coefficients using this method does not exceed 8% for blades with radial channels. An important feature of the method is that the heat load remains unchanged during the experiment and the blade outer surface temperature equals zinc melting point. The verification of thermal-hydraulic model of high-pressure turbine blade with cooling allowing asymmetrical heat removal from pressure and suction sides was carried out using the developed method. An analysis of heat transfer coefficients confirmed the high level of heat transfer in the leading edge, whose value is comparable with jet impingement heat transfer. The maximum of the heat transfer coefficients is shifted from the critical point of the leading edge to the pressure side. |
| format | Article |
| id | doaj-art-0dad2b5934c143a198631a853ced4e83 |
| institution | Kabale University |
| issn | 1023-621X 1542-3034 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Rotating Machinery |
| spelling | doaj-art-0dad2b5934c143a198631a853ced4e832025-02-03T06:08:14ZengWileyInternational Journal of Rotating Machinery1023-621X1542-30342018-01-01201810.1155/2018/67801376780137Verification of Thermal Models of Internally Cooled Gas Turbine BladesIgor Shevchenko0Nikolay Rogalev1Andrey Rogalev2Andrey Vegera3Nikolay Bychkov4National Research University Moscow Power Engineering Institute, 14 Krasnokazarmennaya Street, Moscow 111250, RussiaNational Research University Moscow Power Engineering Institute, 14 Krasnokazarmennaya Street, Moscow 111250, RussiaNational Research University Moscow Power Engineering Institute, 14 Krasnokazarmennaya Street, Moscow 111250, RussiaNational Research University Moscow Power Engineering Institute, 14 Krasnokazarmennaya Street, Moscow 111250, RussiaNational Research University Moscow Power Engineering Institute, 14 Krasnokazarmennaya Street, Moscow 111250, RussiaNumerical simulation of temperature field of cooled turbine blades is a required element of gas turbine engine design process. The verification is usually performed on the basis of results of test of full-size blade prototype on a gas-dynamic test bench. A method of calorimetric measurement in a molten metal thermostat for verification of a thermal model of cooled blade is proposed in this paper. The method allows obtaining local values of heat flux in each point of blade surface within a single experiment. The error of determination of local heat transfer coefficients using this method does not exceed 8% for blades with radial channels. An important feature of the method is that the heat load remains unchanged during the experiment and the blade outer surface temperature equals zinc melting point. The verification of thermal-hydraulic model of high-pressure turbine blade with cooling allowing asymmetrical heat removal from pressure and suction sides was carried out using the developed method. An analysis of heat transfer coefficients confirmed the high level of heat transfer in the leading edge, whose value is comparable with jet impingement heat transfer. The maximum of the heat transfer coefficients is shifted from the critical point of the leading edge to the pressure side.http://dx.doi.org/10.1155/2018/6780137 |
| spellingShingle | Igor Shevchenko Nikolay Rogalev Andrey Rogalev Andrey Vegera Nikolay Bychkov Verification of Thermal Models of Internally Cooled Gas Turbine Blades International Journal of Rotating Machinery |
| title | Verification of Thermal Models of Internally Cooled Gas Turbine Blades |
| title_full | Verification of Thermal Models of Internally Cooled Gas Turbine Blades |
| title_fullStr | Verification of Thermal Models of Internally Cooled Gas Turbine Blades |
| title_full_unstemmed | Verification of Thermal Models of Internally Cooled Gas Turbine Blades |
| title_short | Verification of Thermal Models of Internally Cooled Gas Turbine Blades |
| title_sort | verification of thermal models of internally cooled gas turbine blades |
| url | http://dx.doi.org/10.1155/2018/6780137 |
| work_keys_str_mv | AT igorshevchenko verificationofthermalmodelsofinternallycooledgasturbineblades AT nikolayrogalev verificationofthermalmodelsofinternallycooledgasturbineblades AT andreyrogalev verificationofthermalmodelsofinternallycooledgasturbineblades AT andreyvegera verificationofthermalmodelsofinternallycooledgasturbineblades AT nikolaybychkov verificationofthermalmodelsofinternallycooledgasturbineblades |