Abstract: In order to study transient response characteristics of unsteady flow of rotor-stator cavity of aero-engine， a CFD calculation model of rotor-stator cavity was established and the numerical simulation methodbased on UDF of Fluent was used to study the transient response characteristics of the rotor-stator cavity wherethe inlet pressure is changed by the step function，the ramp function and the sine function with the correspondingevaluation index of transient response characteristics proposed. The results show that there is a significant differ.ence in the transient response characteristics of the rotor-stator cavity under different intake functions，and the transient response of the flow parameters in the cavity has different degrees of hysteresis under the same intakefunction. The response time of the average total pressure in the cavity increases by 3369.2% with the dimension.less step coefficient of the step function ranging from 1.025 to 1.3，and increases by 163.9% with the ramp time of ramp function increasing from 0.01 to 0.16 s，and shrinks to 45.6% with the angular velocity of sine functionranging from 22 to 55rad/s. There is a overshoot phenomenon of the average total temperature of the system underdifferent intake functions，and the peak time and overshoot are closely related with the type of intake function.

Key words: Transient response；Rotor-stator cavity；Intake function；Unsteady flow

摘要： 为研究航空发动机转静盘腔非稳态流动的瞬态响应特性，建立了转静盘腔 CFD计算模型，采用基于 Fluent用户自定义函数( UDF)编程的非稳态数值计算方法，分别研究了进口压力以阶跃函数、斜坡函数和正弦函数变化时转静盘腔的瞬态响应特性，并提出了相应的瞬态响应特性评价指标。结果表明:不同进气函数下的转静盘腔瞬态响应特性存在明显差异，同一进气函数下盘腔中各流动参数的瞬态响应存在不同程度的滞后。阶跃函数的无量纲跃升幅值由 1.025变化到 1.3时，盘腔平均总压的响应时间增加了 3369.2%；斜坡函数的斜坡时间由 0.01s增加到 0.16s时，盘腔平均总压的响应时间增加了 163.9%；而正弦函数的角速度由 22rad/s变化到 55rad/s时，盘腔平均总压的响应时间缩短了 45.6%。不同进气函数下转静盘腔平均总温随时间的变化曲线均呈现出明显的过冲现象，其峰值时间和超调量变化规律与进气函数类型密切相关。

关键词: 瞬态响应；转静盘腔；进气函数；非稳态流动