跨声速轴流压气机失速边界预测方法

研究了跨声速、单级设计压比为1.82的Stage 35轴流压气机与单级设计压比为2.05的Stage37轴流压气机在不同转速下的特性.在HARIKA原型程序基础上,改进了其叶排效率、落后角、理论能头计算模型,采用了两种轴流压气机失速边界的预测方法,第1种为HARIKA原型程序的分离流量预测方法,第2种为Koch所提出的失速静压升系数预测方法,所得特性计算结果与实验点吻合较好,Stage 35设计点效率的误差由原型的3.9%降低到改进后的1.5%,Stage 37设计点效率的误差由3.1%降低到1.9%.两种预测方法对失速边界流量的预测误差最小分别可达1.3%与1.6%,表明两种失速边界预测方法都是可行的.

Prediction method of stall margin in axial-flow transonic compressor

Performance of single stage axial-flow transonic compressor Stage 35 of design pressure ratio 1.82 and Stage 37 of design pressure ratio 2.05 at different rotation speeds was presented. Based on the HARIKA program, three models for respectively predicting cascade efficiency, deviation angle and head rise were improved. Two methods for predicting stall margin of axial-flow compressors were used. The first one was separation mass flow prediction method in HARIKA program. The second one was stalling static pressure rise coefficient prediction method proposed by Koch. Good agreement was achieved between the computation results and experiment data. The efficiency error of Stage 35 at design point decreases from 3.9% to 1.5%. The efficiency error of Stage 37 decreases from 3.1% to 1.9%. The minimum error of mass flow of stall margin predicted by two methods is 1.3% and 1.6% respectively. The result indicates that two methods used to predict stall margin are feasible.