为了解决高速机载涡轮发电系统效率较低的问题，通过一维计算和三维数值模拟相结合的方法，对以拉法尔喷管作为静叶、三维叶片作为动叶的局部进气跨声速涡轮级进行了研究。在对原型涡轮级流场分析后，通过ISIGHT优化软件集成NX，NUMECA和ANSYS等模块，采用多岛遗传算法，以喷管扩张角、扩张部分长度、周向排布角度以及动叶叶片进口几何角、出口几何角和轴向弦长作为优化变量对涡轮级进行了优化设计。最终得到给定设计工况下的最优几何参数。优化结果表明：优化得到的涡轮级功率达到了74 530 W，效率达到了79.60%，较原型提升了5.1%。

In order to solve the problem of low efficiency of highspeed airborne turbine power generation systems, this paper investigates a transonic partialadmission turbine stage with a Rafael nozzle as the stator and a threedimensional blade as the rotor through a combination of onedimensional calculations and threedimensional numerical simulations. After analyzing the flow field of the prototype turbine stage, a multiisland genetic algorithm is used to optimise the design of the turbine stage using the nozzle expansion angle, expansion section length, circumferential arrangement angle, the blade inlet and outlet angles and axial chord length as optimisation variables, through the integration of NX, NUMECA and ANSYS modules using the ISIGHT optimisation software. Finally, the optimum geometry parameters under the given design conditions are obtained. The optimization result show that the optimized turbine stage achieves a power of 74.53 kW and an efficiency of 79.60% with an improvement of 5.1% over the prototype.

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黑龙江省科学基金-优秀青年基金（HSF20210056）；国家科技重大专项(J2019Ⅳ00080076)