大涵道比发动机多级低压涡轮试验技术研究

Research on Multistage Low Pressure Turbine Test Technology for High Bypass Ratio Aeroengine

涡轮试验是检验涡轮性能是否达标的重要过程。基于某全尺寸涡轮试验器、现有涡轮试验方法和试验规范,通过对试验器进行适当设备改造,结合试验涡轮的进出口压力、温度、流量和功率等参数的耦合关系,形成针对大涵道比涡扇发动机多级低压涡轮性能试验状态评估、过程控制和数据分析方法,并通过国内某型大涵道比涡扇发动机多级低压涡轮试验进行验证。试验结果表明:基于试验参数耦合关系的试验状态评估、过程控制和数据分析方法有效,填补了国内大涵道比涡扇发动机多级低压涡轮试验方法和试验数据的空白,同时,该型发动机低压涡轮的效率达到设计指标,处于国内先进水平,所述方法可为国内后续多级低压涡轮试验提供参考。

Turbine test is a significant process to test whether turbine characteristics is up to standard. Based on a full-scale turbinetester,the existing turbine test methods and test specifications and combined with the coupling relations of inlet and outlet pressure,temperature,flow rate and power of the test turbine,a method of high bypass ratio turbofan characteristic test evaluation,process control andtest data analysis for multistage low pressure turbine was developed through the appropriate equipment modification of the tester. Adomestic high bypass ratio turbofan with multistage low pressure turbine test was verified. The test results show that the characteristic testevaluation,process control and data analysis based on the coupling relations of test parameters are effective,and fill the blank of test methodand test data for domestic high bypass ratio turbofan with multistage low pressure turbine. At the same time,the efficiency of the lowpressure turbine of this type of engine reaches the design target and is advanced in China. The method can be used as a reference for thedomestic subsequent multistage low pressure turbine test.