多级涡轮过渡态气动热力性能试验

Transition State Aerodynamic and Thermodynamic Performance Experiment of Multi-Stage Turbine

针对因迟滞效应明显、气动热力特征复杂、工作状态不平衡导致涡轮过渡状态难以实现试验模拟的问题,开展了涡轮过渡态变化特征分析,从N-S方程组的求解过程入手,考虑时变定解条件的相似性,得到了适用于过渡态涡轮性能试验的相似模拟方法。基于某稳态涡轮试验设备,构建了涡轮过渡态试验环境。针对过渡态测控需求,构建了统一的同步控制测试平台。最终在某五级涡轮试验件平台上,完成了多级涡轮过渡态气动热力性能试验验证。结果表明,在过渡态过程中,部分空气腔内的压力和试验件的轴向力表现出了明显的迟滞和不同步特征,涡轮扭矩效率和涡轮进口换算流量明显偏离了稳态过程,最大偏离程度大于20%。

Aiming at the problem that it is difficult to realize experimental simulation of turbine transition state due to obvious hysteresis effect,complex aerodynamic and thermal characteristics,and imbalance of working state,the characteristics of turbine transition state changes are analyzed,and starting from the solution process of the N-S equation system,a similar simulation method applicable to the transition state turbine performance test is obtained by taking into account the similarity of time-varying fixed-solution conditions.Based on a steady-state turbine test facility,a turbine transition state test environment is constructed.A united synchronized control test platform is constructed to meet the transition state measurement and control requirements.On a five-stage turbine test rig,a multi-stage turbine transition aerothermal test is completed at last.The results show that during the transition state process,the pressure in part of the air cavity and the axial force of the test rig exhibit obvious hysteresis and unsynchronized characteristics.The turbine torque efficiency and turbine inlet conversion flow rate deviate significantly from the steady state process,with a maximum deviation of more than 20%.