Airworthiness compliance method for aero-engine on surge/stall with distortion conditions
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摘要:
为研究畸变条件下航空发动机对喘振/失速特性适航条款的符合性验证方法，将用于发动机稳定性评定的畸变试验方法应用于适航领域。以某型大涵道比涡扇发动机为研究对象，采用数值模拟方法研究了其在0°～30°迎角条件下的部件特性，并依据所得畸变图谱设计了不同结构的畸变发生器。结果表明：所设计的畸变发生器可以在一定程度上较好地模拟出不同迎角工况的畸变图谱、风扇的气动特性及流场特征，喘振裕度最大偏差4.32%。总结出发动机喘振裕度与不同迎角和畸变发生器之间的变化关系，用以确定适航条款要求的稳定工作范围。依据中国民用航空规章，发展了一种进气畸变条件下航空发动机喘振/失速特性符合性验证方法，并明确了其在型号合格审定过程的任务阶段。
Abstract:In order to study the verification method of aero-engine’s compliance with the airworthiness terms of surge/stall characteristics under distortion conditions, the distortion test method for engine stability evaluation was applied to the airworthiness field. And a turbofan engine with large bypass ratio was taken as the object, the component characteristics at 0°—30° attack angles were simulated, and the distortion generators with different structures were designed according to the obtained distortion map. The results showed that the designed distortion generator can better simulate the distortion map, aerodynamic performance and flow field characteristics of the fan at different attack angles to a certain extent, and the maximum deviation of stability margin was 4.32%. The relationship between engine surge margin, different attack angles and distortion generator was summarized to determine the stable working range required by airworthiness terms. According to China Civil Aviation Regulations, a method for verifying the compliance of aero-engine surge/stall characteristics with inlet distortion was developed, and its task stage in the model qualification process was defined.
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图 4 短舱风扇计算模型网格无关性验证
Figure 4. Mesh independency investigation of nacelle and fan calculation model
图 5 发动机性能测试平台及数值校核
Figure 5. Aero-engine performance test platform and numerical verification
图 10 畸变发生器计算模型网格无关性验证
Figure 10. Mesh independency investigation of distortion generator calculation model
图 11 不同迎角工况与月牙式畸变发生器方案AIP图谱对比
Figure 11. Comparison of AIP maps under different attack angles and various crescent distortion generator schemes
图 13 组合插板方案与30°迎角工况图谱
Figure 13. Combined plugboard scheme and 30° attack angle working condition map
图 14 风扇99%叶高S1流面熵云图
Figure 14. Entropy contour of S1 flow surface at 99% blade height of fan
图 16 不同迎角和插板方案风扇特性对比
Figure 16. Comparison of fan characteristics at different attack angles and plugboard schemes
图 18 喘振/失速特性符合性验证流程及其在型号合格审定过程所处阶段
Figure 18. Surge/stall characteristic compliance verification process and its stage in the model qualification process
表 1 风扇和OGV设计参数
Table 1. Design parameters of fan and OGV
设计参数 数值 风扇数 14 转速/（r/min） 13069 叶顶间隙/mm 0.5 风扇展弦比 1.46 OGV数 40 总增压比 1.19 涵道比 6.851 
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表 2 不同参数畸变发生器设计和计算方案
Table 2. Design and calculation scheme of distortion generator with different parameters
畸变发生器类型 方案 H*/% κ L/mm X/mm 月牙式插板 M1 1 5.714 Ⅰ100/Ⅱ150/Ⅲ200/Ⅳ350/Ⅴ700 M2 2 5.711 Ⅰ100/Ⅱ150/Ⅲ200/Ⅳ350/Ⅴ700 M3 3 5.705 Ⅰ100/Ⅱ150/Ⅲ200/Ⅳ350/Ⅴ700 M4 5 5.682 Ⅰ100/Ⅱ150/Ⅲ200/Ⅳ350/Ⅴ700 组合式插板A CA1 5.5 5.219 100 Ⅰ110/Ⅱ120/Ⅲ130 CA2 6 5.219 100 Ⅰ110/Ⅱ120/Ⅲ130 组合式插板B CB1 5.5 5.714 100 Ⅰ110/Ⅱ120/Ⅲ130 CB2 6 5.714 100 Ⅰ110/Ⅱ120/Ⅲ130
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