非定常脉冲爆震来流下涡轮气动特征仿真研究

Simulation research of turbine aerodynamic feature under unsteady pulsed detonation inflow

中文关键词: 非定常  脉冲爆震  发动机  涡轮  气动  仿真

英文关键词: unsteady  pulsed detonation  engine  turbine  aerodynamic  simulation

中文摘要:

      脉冲爆震涡轮发动机是未来涡轮发动机的一种有潜力的发展方向。为了厘清具有强非定常性的脉冲爆震来流下涡轮的气动性能及流动特征，为脉冲爆震涡轮发动机涡轮的设计提供技术支撑，采用非定常进口总压与总温边界条件对某单级燃气涡轮的开展了瞬态数值仿真计算分析。研究结果表明由于进口来流的强非定常性，涡轮内部流动在爆震周期的前段时间并未完全建立起流动平衡，故进出口的流量不守恒；焓降功率与扭矩功率、焓降效率与扭矩效率不相等；在一个爆震周期内，动叶进口气流攻角的变化幅度达到40°，出口绝对气流角的变化幅度达到50°。在一个爆震周期中，只有约1/4的时间段涡轮的气动状态接近设计点，故一个爆震周期中涡轮的综合功率较低。

英文摘要:

      The pulsed detonation turbo engine is a promising developing trend of the future turbo engine. To clarify the aerodynamic performance and flow feature of the turbine under strong unsteady pulsed detonation inflow, and to support the aerodynamic design of the pulsed detonation turbo engine turbine, a transient flow numerical simulation and analysis was conducted by unsteady inlet total pressure and total temperature boundary conditions. The research shows because of the strong unsteadiness of inflow, no balance has built between the inner flow of the turbine, so the mass flow is not keeping equal between the inlet and outlet, so are the enthalpy drop power and torque power, the enthalpy drop efficiency and torque efficiency. During a detonation period, the rotor blade incidence has changed by 40 degrees. As there is only 1/4 time span near the turbine design point status, the comprehensive power in a detonation period are low.