| 应用端弯叶片增加压气机喘振裕度 |
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| 引用本文： | 蔡运金,钟玉玲,钱鲁泓.应用端弯叶片增加压气机喘振裕度[J].航空动力学报,1988,3(3):215-218,281. |
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| 作者姓名： | 蔡运金 钟玉玲 钱鲁泓 |
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| 作者单位： | 沈阳航空发动机制造公司
(蔡运金，钟玉玲)，沈阳航空发动机制造公司(钱鲁泓) |
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| 摘 要： | 本文介绍了某型高压压气机考虑端壁附面层影响改进设计的端弯叶片,试验证明:喘振裕度增加7.3％,效率提高4.1％,流量、压比变化很小。飞行试验证明:解决了空中停车问题,在飞行包线内能保证可靠稳定工作,发动机和飞机性能都有较大的提高。
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| 收稿时间： | 2/1/1988 12:00:00 AM |
APPLICATION OF END-BEND BLADE FOR ENHANCING SURGE MARGIN |
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| Cai Yunjin,Zhong Yuling and Qian Luhong.APPLICATION OF END-BEND BLADE FOR ENHANCING SURGE MARGIN[J].Journal of Aerospace Power,1988,3(3):215-218,281. |
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| Authors: | Cai Yunjin Zhong Yuling and Qian Luhong |
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| Institution: | Shenyang Aeroengine Company;Shenyang Aeroengine Company;Shenyang Aeroengine Company |
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| Abstract: | The blade end-bend technique is applied to the first and second stators of the HP compressor of a twin-spool engine to ameliorate the flow on the second and third rotors. The tests of the modified engine show that its surge margin and efficiency are enhanced by 7.3 and 4.1 percent respectively, but the flow and pressure ratio vary only a little. The flight tests prove that the shutdown of the engine which occurred in flight has been eliminated, so that the engine can operate reliably and stably within the overall flight envelope, and the performances of the engine and the aircraft has been improved significantly. |
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