涡轮发动机预旋供气系统温降和压比特性

In order to study the complex flow and heat transfer in the pre-swirl gas supply system of a gas turbine engine. The modeling method is adopted. Then, the engine prototype and the experimental model are highly similar based on the similarity criteria with the same flow and rotor Mach numbers. An experimental study of the high-speed pre-swirl gas supply system is then conducted. The variation law of flow and rotor Mach numbers on the system temperature drop and pressure characteristics is revealed under the condition of satisfying the gas supply flow rate and pressure. Within the range of experimental conditions of turbine disk rotational speeds of 4 800~9 207 r/min and flow rate ratios of 0. 45~0. 72, the result shows that system pressure and temperature ratios increase with the flow rate ratio; system temperature drop also increases with the flow coefficient of the pre-swirl nozzle. Particularly, the maximum system temperature drop can reach 23 K under the experimental conditions. With the increase in rotor Mach number, the system pressure ratio, system temperature ratio, and the flow coefficient of pre-swirl nozzles remain unchanged; however, the system temperature drop first increases and then decreases. Therefore, the system temperature drop is mainly determined by the temperature drop in the pre-swirl nozzle and can be effectively improved by pre-swirl nozzle optimization without changing the rotor disk structure.