基于建立的舰船大功率多级轴流压气机气动设计体系，开展了舰船用某型大功率燃气轮机压气机设计研究，完成了6级轴流压气机的气动设计。进行了一维反问题设计、一维特性计算分析、S2反问题计算、叶片造型以及三维CFD计算分析。各级载荷分布从前面级到后面级逐渐降低，叶展方向按照等压比分配以避免径向掺混损失过大，S2设计并没有严格遵循传统的设计规律（等环量、等反动度等），而是基于一维设计方案通过不断调整优化获得的。根据CDA的特点，开发了可用于工程应用的叶片造型程序，可实现不同中弧线、不同厚度分布调节，能够实现叶片弯、掠等功能。三维数值模拟结果表明，考虑动叶叶顶具有0.5 mm间隙的情况下，6级压气机设计点效率达到89.75%，设计转速下的喘振裕度为22.5%，同时具有较好的变工况性能。

Based on the established aerodynamic design system for high-power multistage axial-flow compressor,a design case of a high-power gas turbine compressor was carried out,and the aerodynamic design of the six-stage axial compressor was completed.The design of onedimension inverse problem,S2 inverse problem calculation,blade modeling and 3D CFD calculation and analysis were carried out.The load distribution at various stages was gradually reduced from the front stage to the rear stage,while the load in the spanwise direction was distributed in accordance with the isobaric ratio in order to avoid excessive radial mixing loss.The design of S2 does not strictly follow the traditional design rules (such as equal circulation,equal reaction degree,etc.),while is based on onedimensional design parameters,which was obtained through continuous adjustment of design parameters.According to the CDA technical feature,a blade modeling program for engineering practice was developed,which can realize the functions of different camber line,different thickness distributions,and bending and sweeping of stack line.The three-dimensional numerical simulation results show that with consideration of the 0.5 mm clearance of the rotor blade tip,the design efficiency of the six-stage compressor can reach 89.75%,the surge margin of the design speed cine is 22.5%,and the off-design conditions is also very well.

TH45

国家科技重大专项（2017-Ⅰ-0006-0019）；船舶与海洋工程动力系统国家工程实验室-海洋工程燃气轮机实验室资助