在航空柱塞泵的进油端集成涡轮增压系统，有利于提高航空液压系统的集成度，并解决柱塞泵在高转速下因吸油不足而产生的空化、脱靴等难题。针对涡轮增压系统中叶片和压水室流道的优化设计问题，基于熵产理论对增压系统中的能量损失及其空间分布进行了研究，构建了涡轮自增压轴向柱塞泵的流体域模型，探究压水室形式、断面形状、进口宽度、断面面积变化规律以及涡轮叶片形式与熵产率的关系，以熵产最小为目标优化涡轮增压系统的结构：涡轮采用扭曲叶片，压水室采用螺旋形、断面形状采用圆弧形、压水室进口宽度采用8 mm、断面面积变化规律为U型时，增压系统的总熵产下降约0.032 W/K，较优化前降低了13%，增压值上升约0.22 bar，较优化前增加7%。最后采用试制的样机搭建试验系统，测试了直叶片形式和扭曲叶片形式的涡轮增压值，试验结果与仿真结果基本一致。

The integration of turbocharging system at the inlet end of aviation piston pump is conducive to improving the integration of aviation hydraulic system， and solving the problems of cavitation and boot removal caused by insufficient oil absorption of the plunger pump at high speed. Aiming at the optimization design of blades and pressurized chamber flow channels in turbocharging system， the energy loss and spatial distribution in the pressurized system are studied based on the entropy production theory， and the fluid domain model of the turbo self-boosting axial piston pump is constructed to explore the changes of pressurized chamber form， section shape， inlet width， section area， and the relationship between turbine blade form and entropy yield. The structure of the turbocharging system is optimized to minimize the entropy production， ie. when the turbine adopts twisted blades， the pressurized water chamber adopts a spiral shape， the cross-section shape adopts a circular arc， the inlet width of the pressurized water chamber adopts 8mm， and the cross-section area change law is U-shaped， the total entropy production of the pressurized system decreases by about 0.032 W/K， which is 13% lower than before optimization， and the boost value increases by about 0. 22 bar， 7% more than before optimization. Finally， the prototype was used to build the test system， and the turbocharging values in the form of straight blades and twisted blades were tested， and the test results were basically consistent with the simulation results.