RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE
In view of the problem that the gas turbine blades rely more on the long-term test of the whole machine in the later stage to expose the insufficient design, this paper takes the gas turbine blades of an engine as an example to study the low cycle fatigue life of gas turbine blades. Firstly, the str...
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| Format: | Article |
| Language: | zho |
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Editorial Office of Journal of Mechanical Strength
2022-01-01
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| Series: | Jixie qiangdu |
| Subjects: | |
| Online Access: | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2022.04.036 |
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| author | ZHANG Di QIAN ZhengMing MI Dong XUAN HaiJun ZHAO YongMing |
| author_facet | ZHANG Di QIAN ZhengMing MI Dong XUAN HaiJun ZHAO YongMing |
| author_sort | ZHANG Di |
| collection | DOAJ |
| description | In view of the problem that the gas turbine blades rely more on the long-term test of the whole machine in the later stage to expose the insufficient design, this paper takes the gas turbine blades of an engine as an example to study the low cycle fatigue life of gas turbine blades. Firstly, the stress-strain analysis of gas turbine blade is carried out under typical cycles. It is determined that the main failure mode of gas turbine blade is low cycle fatigue failure controlled by strain fatigue. According to the principle of linear damage accumulation, the low cycle fatigue life of gas turbine blade is predicted. Then, a design method of low cycle fatigue test of turbine blade on rotating test-bed is innovatively proposed. The method uses open-loop electromagnetic induction coil to heat the blade, realizes the temperature field of gas turbine rotor with temperature gradient through heat conduction, and determines the test speed of gas turbine rotor according to the principle of strain equivalence. The test results show that the predicted service life of gas turbine blade is within 5 times of service life dispersion zone, and the crack position of component test blade is consistent with the test results of the whole machine. |
| format | Article |
| id | doaj-art-9698da09cdcb4530ba101da14a746b1d |
| institution | Kabale University |
| issn | 1001-9669 |
| language | zho |
| publishDate | 2022-01-01 |
| publisher | Editorial Office of Journal of Mechanical Strength |
| record_format | Article |
| series | Jixie qiangdu |
| spelling | doaj-art-9698da09cdcb4530ba101da14a746b1d2025-01-15T02:24:02ZzhoEditorial Office of Journal of Mechanical StrengthJixie qiangdu1001-96692022-01-01441013101629913996RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINEZHANG DiQIAN ZhengMingMI DongXUAN HaiJunZHAO YongMingIn view of the problem that the gas turbine blades rely more on the long-term test of the whole machine in the later stage to expose the insufficient design, this paper takes the gas turbine blades of an engine as an example to study the low cycle fatigue life of gas turbine blades. Firstly, the stress-strain analysis of gas turbine blade is carried out under typical cycles. It is determined that the main failure mode of gas turbine blade is low cycle fatigue failure controlled by strain fatigue. According to the principle of linear damage accumulation, the low cycle fatigue life of gas turbine blade is predicted. Then, a design method of low cycle fatigue test of turbine blade on rotating test-bed is innovatively proposed. The method uses open-loop electromagnetic induction coil to heat the blade, realizes the temperature field of gas turbine rotor with temperature gradient through heat conduction, and determines the test speed of gas turbine rotor according to the principle of strain equivalence. The test results show that the predicted service life of gas turbine blade is within 5 times of service life dispersion zone, and the crack position of component test blade is consistent with the test results of the whole machine.http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2022.04.036Aero-engineTurbine bladeLow cycle fatigueFatigue lifeTest design method |
| spellingShingle | ZHANG Di QIAN ZhengMing MI Dong XUAN HaiJun ZHAO YongMing RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE Jixie qiangdu Aero-engine Turbine blade Low cycle fatigue Fatigue life Test design method |
| title | RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE |
| title_full | RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE |
| title_fullStr | RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE |
| title_full_unstemmed | RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE |
| title_short | RESEARCH ON LOW CYCLE FATIGUE LIFE OF GAS TURBINE BLADE OF AN AERO-ENGINE |
| title_sort | research on low cycle fatigue life of gas turbine blade of an aero engine |
| topic | Aero-engine Turbine blade Low cycle fatigue Fatigue life Test design method |
| url | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2022.04.036 |
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