Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation
In order to understand the cooling procedure of aviation engine blade after titanium combustion, the finite element method was used to simulate the temperature and fluid field of ROTOR37 model after combustion occurred with 550℃ fire proof titanium alloy(TF550 titanium alloy) and 600℃ high temperatu...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | zho |
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Journal of Materials Engineering
2018-10-01
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| Series: | Cailiao gongcheng |
| Subjects: | |
| Online Access: |
http://jme.biam.ac.cn/CN/Y2018/V46/I10/37
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| _version_ | 1828078123309072384 |
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| author | LIANG Xian-ye MI Guang-bao LI Pei-jie CAO Jing-xia HUANG Xu |
| author_facet | LIANG Xian-ye MI Guang-bao LI Pei-jie CAO Jing-xia HUANG Xu |
| author_sort | LIANG Xian-ye |
| collection | DOAJ |
| description | In order to understand the cooling procedure of aviation engine blade after titanium combustion, the finite element method was used to simulate the temperature and fluid field of ROTOR37 model after combustion occurred with 550℃ fire proof titanium alloy(TF550 titanium alloy) and 600℃ high temperature titanium alloy(TA29 titanium alloy), respectively. The results show that the relative mach number influences the cooling procedure of blade, the cooling performance at the area of mach number about 0.7-1 is much higher than other area; compared with the leading edge, the cooling process of the tip is more complex, and the cooling rate is an order of magnitude lower than that of the leading edge. The difference of cooling temperature between TF550 titanium alloy and TA29 titanium alloy at tip combustion area is quite observable; and the maximum value occurs within the scope of 1000-2500K; the former is more than 100K lower than the latter, the value is reduced into 30K within the scope of 300-500K. The temperature distortion of the flow field would increase the intensity of the surge, the effect of combustion on the surge margin should be fully considered during the design of the blade. |
| first_indexed | 2024-04-11T02:41:30Z |
| format | Article |
| id | doaj.art-cd8f0f4f313047cba7fd40920211a98f |
| institution | Directory Open Access Journal |
| issn | 1001-4381 1001-4381 |
| language | zho |
| last_indexed | 2024-04-11T02:41:30Z |
| publishDate | 2018-10-01 |
| publisher | Journal of Materials Engineering |
| record_format | Article |
| series | Cailiao gongcheng |
| spelling | doaj.art-cd8f0f4f313047cba7fd40920211a98f2023-01-02T18:56:04ZzhoJournal of Materials EngineeringCailiao gongcheng1001-43811001-43812018-10-014610374610.11868/j.issn.1001-4381.2018.000182201810000182Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical SimulationLIANG Xian-ye0MI Guang-bao1LI Pei-jie2CAO Jing-xia3HUANG Xu4National Center of Novel Materials for International Research, Tsinghua University, Beijing 100084, ChinaAviation Key Laboratory of Science and Technology on Advanced Titanium Alloys, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, ChinaNational Center of Novel Materials for International Research, Tsinghua University, Beijing 100084, ChinaAviation Key Laboratory of Science and Technology on Advanced Titanium Alloys, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, ChinaAviation Key Laboratory of Science and Technology on Advanced Titanium Alloys, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, ChinaIn order to understand the cooling procedure of aviation engine blade after titanium combustion, the finite element method was used to simulate the temperature and fluid field of ROTOR37 model after combustion occurred with 550℃ fire proof titanium alloy(TF550 titanium alloy) and 600℃ high temperature titanium alloy(TA29 titanium alloy), respectively. The results show that the relative mach number influences the cooling procedure of blade, the cooling performance at the area of mach number about 0.7-1 is much higher than other area; compared with the leading edge, the cooling process of the tip is more complex, and the cooling rate is an order of magnitude lower than that of the leading edge. The difference of cooling temperature between TF550 titanium alloy and TA29 titanium alloy at tip combustion area is quite observable; and the maximum value occurs within the scope of 1000-2500K; the former is more than 100K lower than the latter, the value is reduced into 30K within the scope of 300-500K. The temperature distortion of the flow field would increase the intensity of the surge, the effect of combustion on the surge margin should be fully considered during the design of the blade. http://jme.biam.ac.cn/CN/Y2018/V46/I10/37 titanium combustioncoolingthree dimensional thermo-fluid couplenumerical simulationaero-engine |
| spellingShingle | LIANG Xian-ye MI Guang-bao LI Pei-jie CAO Jing-xia HUANG Xu Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation Cailiao gongcheng titanium combustion cooling three dimensional thermo-fluid couple numerical simulation aero-engine |
| title | Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation |
| title_full | Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation |
| title_fullStr | Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation |
| title_full_unstemmed | Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation |
| title_short | Cooling Process of Titanium Alloy Blades After Combustion Using Three Dimensional Heat Flow Coupling Numerical Simulation |
| title_sort | cooling process of titanium alloy blades after combustion using three dimensional heat flow coupling numerical simulation |
| topic | titanium combustion cooling three dimensional thermo-fluid couple numerical simulation aero-engine |
| url |
http://jme.biam.ac.cn/CN/Y2018/V46/I10/37
|
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