间冷循环涡轮气动方案

Research on aerodynamic case of intercooling cycle turbine

以间冷循环燃气轮机总体对动力涡轮的设计要求为目标,进行了间冷循环动力涡轮气动方案改型设计研究。计算采用成熟的轴流涡轮一维气动设计软件Concept NREC Axial,在一维气动损失模型的选用方面,通过对某型机性能复算进行了验证。方案改型计算在满足间冷循环燃机总体对动力涡轮的参数进行大规模调整的前提下,以尽量保留原型机的高可靠性为目标,并综合考虑了性能与改型难度的平衡,完成了多个方案的计算。结果表明,经过改型设计的涡轮可以基本满足间冷循环的要求。

In this paper revised aerodynamic design of intercooling cycle power turbine was performed,aimed the demand of intercooling cycle gas turbine general design. All computing work performed by a reliable turbine performance computing software Concept NREC Axial,the chosen of the loss model wasverified by check computation of a certain gas turbine. Several revised cases were researched,aimed to keep a balance of performace and difficult of the revise and to keep the high reliability of original machine as more as possible, and base the fact that the performance parameter of power turbine has been changed greatly compared with original machine by intercooling cycle gas turbine general design. The results show that the requests to turbine of intercooling cycle can be basically fulfilled by the revised design of turbine.