| 弹用涡喷发动机燃烧室出口温度场试验与分析 |
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| 引用本文： | 郑严,沈倍毅.弹用涡喷发动机燃烧室出口温度场试验与分析[J].推进技术,2001,22(3):187-190,206. |
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| 作者姓名： | 郑严 沈倍毅 |
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| 作者单位： | 1. 哈尔滨工业大学能源科学与工程学院,
2. 航天机电集团公司31所, |
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| 摘 要： | 介绍了弹用涡喷发动机燃烧室部件试验，对试验结果进行了全面的分析，指出燃烧室模拟试验与发动机实际工况之间的差别，产生差别的原因以及试验修正的方法。通过试验数据的分析与处理给出了某弹用涡喷发动机燃烧室出口向温度分布、出口温度场和无因次温度场，分析结论可用于弹用涡喷发动机燃烧室出口温度场预测和涡轮导向器叶片热设计。
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| 关 键 词： | 涡轮喷气发动机 燃烧室 部件试验 温度分布 弹用涡轮喷气发动机 飞机 |
| 文章编号： | 1001-4055（2001）03-0187-05 |
Tests and analysis of exit temperature distribution of the combustor for missile turbojet |
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| ZHENG Yan and SHEN Bei-yi.Tests and analysis of exit temperature distribution of the combustor for missile turbojet[J].Journal of Propulsion Technology,2001,22(3):187-190,206. |
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| Authors: | ZHENG Yan and SHEN Bei-yi |
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| Institution: | ZHENG Yan 1,SHEN Bei-yi 2 |
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| Abstract: | The overall tests of exit temperature distribution of the combustor used in missile’s turbine jet engine were presented and the statistic analysis results for the tests were given.The differences between imitate tests of the combustor and reality working process of the engine were pointed out.The reasons causing the differences and modifying technique are given.In addition,the temperature distribute on radial and on exit field of combustor were presented.It is useful for the hot design of the turbine nozzle blades. |
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| Keywords: | Turbojet engine Combustor Component test Temperature distribution |
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