三级高负荷压气机改型设计与流动分析

This article is based on the 9FA heavy-duty gas turbine final stage compressor, aiming to improve the pressure ratio, efficiency, and expand the margin. It redesigns a three-stage high-load compressor that breaks through the conventional load. In the design process, three-dimensional blade technology is used in the end region of the stator blades. Comparative analysis was conducted on the changes in key parameters such as efficiency, pressure ratio, and total pressure loss at the outlet of each stage before and after the modification. The results show that, compared to the prototype, the three-dimensional blade technology effectively controls the separation of the stator blade corner by transferring the boundary layer on the wall while maintaining consistent inlet flow angle and outlet Mach number. The modified three-stage high-load compressor achieves an efficiency of 90.08%, a pressure ratio of 1.393, and a surge margin of 25.5% near the design point.