离心式压气机凭借其较大的单级压比在中小型航空动力装置中具有广泛应用。而对转式压气机通过两组转子反向协同旋转实现高负荷输出。以整级总压比≥9.00、质量流量3.70kg/s、整级等熵总总效率≥70.00%为设计目标，开展高负荷对转离心式压气机的气动设计与数值模拟研究。基于一维设计方法完成叶轮基本几何参数、叶片前尾缘几何角等关键参数的确定。通过数值模拟对初步设计方案进行验证后，针对下游叶栅实施两处关键改进，得到两种改型方案。数值模拟结果表明：改进后的设计方案总压比与流量参数均满足设计要求，验证了所提出设计方法的可行性。

Centrifugal compressors have been widely used in small and medium-sized aviation power plants due to their relatively large single-stage pressure ratio. The contra-rotating compressor achieves high-pressure ratio output through the coordinated reverse rotation of two sets of rotors. the design objectives are set as a total pressure ratio of the entire stage ≥ 9.00, a mass flow rate of 3.70 kg/s, and an isentropic total efficiency of the entire stage ≥ 70.00%. Carry out the aerodynamic design and numerical simulation research on the high-load contra-rotating centrifugal compressor. Based on the one-dimensional design method, determine the key parameters such as the basic geometric parameters of the impeller and the geometric angles of the leading and trailing edges of the blades. After verifying the preliminary design scheme through numerical simulation, Implement two key improvements for the downstream cascade. Two modified schemes are obtained. The results of the numerical simulation show that: The total pressure ratio and flow rate parameters of the improved design scheme both meet the design requirements. It verifies the feasibility of the proposed design method.