低压涡轮气动/声学一体化设计——总体参数优化

低压涡轮是航空发动机的重要噪声源之一,同时也是影响发动机单位推力耗油率的重要部件之一。为适应新一代发动机高效、低噪的设计目标,提出了基于传统涡轮设计流程的低压涡轮气动/声学一体化设计思路,并以某一典型民用发动机6级低压涡轮的设计要求为例,对末级功分配、通道外径、涡轮出口马赫数、叶片数目等涡轮总体参数进行了优化探索。结果表明,文中提出的设计思路可以在涡轮设计的总体参数选取阶段对涡轮效率和噪声同时进行有效评估,以便合理地选取涡轮总体参数,是一种可行的高效、低噪涡轮设计方法。

Aerodynamics/Acoustics Integration Design Method of Low Pressure Turbine Overall Parameters Optimization

Low pressure turbine is one of the main aircraft engine noise sources,and also an important component that effects the specific fuel consumption.To achieve the goals of high efficiency and low noise level in next generation engine,an integrated aerodynamic-acoustics design method was presented for low pressure turbine based on the traditional design process.A typical civil engine’s 6 stage low pressure turbine was chosen for the research,and the influence of the overall parameters such as final stage work distribution,duct outer radius,exit Mach number,blade number on the efficiency and noise level was discussed in detail.Research shows that the design method can evaluate aerodynamic efficiency and noise level effectively at the overall parameter selection stage of turbine design,and it is a feasible method to design high efficient and low noise turbine.