航空涡扇发动机涡轮噪声适航性评估

江朝振; 闫国华; 张鸿; 宋迎东

doi:10.13224/j.cnki.jasp.2017.02.032

航空涡扇发动机涡轮噪声适航性评估

doi: 10.13224/j.cnki.jasp.2017.02.032

1.
中国民航大学中欧航空工程师学院,天津 300300
2.
中国民航大学航空工程学院,天津 300300
3.
南京航空航天大学能源与动力学院,南京 210016

基金项目: 中央高校基本科研业务费专项资金(3122013H001)

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出版历程
- 收稿日期: 2015-05-26
- 刊出日期: 2017-02-28

Noise airworthiness assessment of turbofan aero-engine turbine

摘要

摘要: 通过对涡轮噪声产生机理和主要影响因素的分析研究,建立航空涡扇发动机涡轮噪声级评估模型，编写了涡轮噪声级适航评估软件,使用该软件对比模型评估噪声与涡轮静态实验噪声,验证了模型的正确性,并结合某型发动机静态实验噪声数据和飞机噪声适航规章,对该型涡轮不同阶段的噪声进行适航性评估.结果显示:涡轮噪声在该型发动机进近转速下对发动机总噪声贡献量大,为了使涡轮噪声不影响发动机适航认证,该型发动机低压涡轮叶片数应小于50或者大于100,低压涡轮叶片直径应该小于0.9m.
- 噪声评估 /
- 航空涡扇发动机 /
- 噪声机理 /
- 涡轮噪声级 /
- 适航认证
Abstract: A model for noise level assessment of turbofan engine turbine was established and a program was written by studying the mechanism of noise generation and the main influential factors of the turbine; after using the static test noise of a type of engine to verify the model established, the turbine noise assessment on airworthiness certification was carried out at different rotation speeds based on the static test noise of that engine and the airworthiness certification regulation. Result showed that, turbine noise contributed a lot to this engine total noise when the engine rotation speed was at the stage of approaching and this turbine noise airworthiness certification required that number of low pressure turbine blades of this type of engine should be less than 50 or greater than 100, and the low pressure turbine blade diameter should be less than 0.9m.
- noise assessment /
- turbofan aeroengine /
- noise mechanism /
- turbine noise level /
- airworthiness certification

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参考文献(17)

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