| 姜新瑞，齐 鹏，康 凯，王瑞舟.航空发动机锤击波特性参数测量[J].航空发动机,2024,50(6):144-148 |
| 航空发动机锤击波特性参数测量 |
| Measurement of Aeroengine Hammershock Characteristics |
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| DOI： |
| 中文关键词: 锤击波特性 测量试验 喘振超压比 进气插板 航空发动机 |
| 英文关键词:hammershock characteristics measurement surge overpressure ratio inlet insert plate aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 中文摘要: |
| 为了得到航空发动机喘振后锤击波特性参数，开展了锤击波参数测量试验。讨论了不同的发动机逼喘方式对锤击波测
量参数的影响，制定了锤击波特性参数测量方案，使用喘振超压、喘振超压压比以及喘振超压加载时间等特性参数进行锤击波的
评估。采用进气插板的方法通过改变插板深度得到了发动机起飞状态与巡航状态下发动机喘振后的锤击波特性参数，并对试验
结果进行了分析。结果表明：在不同发动机状态下喘振产生的锤击波强度不同；锤击波产生后沿轴向向前传播，在传播过程中强
度有不断提高的趋势，但基本上是均匀传播，发动机喘振超压比为1.116～1.570；锤击波强度越高，传播的速度越快，锤击波加载
时间为9.1～48.8 ms。 |
| 英文摘要: |
| Measurement experimental investigations were carried out to obtain hammershock characteristics parameters after an
aeroengine surge. The influence of different surge initiating methods on hammershock parameters measurement was discussed, the measure?
ment method for hammershock characteristics was formulated, and parameters such as surge overpressure, surge overpressure ratio, and
surge overpressure loading time were used to evaluate hammershock characteristics. By using an inlet insert plate distortion generator and
varying the plate depth, the hammershock characteristic parameters after engine surge under the take-off and cruise conditions were
obtained, and the test results were analyzed. The results show that the hammershock intensities generated by surge differ under different
engine conditions. the generated hammershock propagates upstream axially, its intensity exhibits an increasing trend during propagation,
but it basically propagates uniformly, the surge overpressure ratios range from 1.116 to 1.57. The higher the intensity of the hammershock,
the faster the propagation speed is. The hammershock loading time ranges from 9.1ms to 48.8ms. |
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