半埋入紧凑S形进气道/风扇耦合流动机理研究

The blended wing body (BWB) aircraft featuring highly integrated airframe-propulsion systems requires boundary layer ingesting (BLI) compact s-inlet to provide the needed airflow to the engine to improve lift-to-drag ratio and stealth performance. However, the BLI compact s-inlet produces distorted flow profiles that can cause performance and stability changes in embedded engines. This project investigates integrated half flush-mounted compact S-inlet/fan systems coupled flow mechanism on a test that can simulate the boundary layer over a ramp. The measurement techniques include porous dynamic pressure probe, surface oil-flow visualization. Numerical simulations are also conducted. It will reveal mechanism of the compact S-shaped internal flow separation, the complex vortex structure and distortion. It will be discussed how the inlet distortion propagates in the fan blade passage and its impact on the fan aerodynamic performance and stability margin. The achievement of this project will supply the foundational theory for advanced integrated engine/airframe design.

未来飞机/推进系统高度集成的翼身融合飞机通过置于飞机尾部的半埋入紧凑S形进气道吸入机身附面层为发动机提供所需流量，以提高升阻比和隐身性。然而，大量机身附面层低能流体吸入会导致S形进气道出口畸变成倍增加，对下游风扇气动性能带来巨大挑战，从而影响发动机整体气动性能和稳定性。本申请项目拟以半埋入紧凑S形进气道与风扇耦合流动机理为主题，以能调节吸入附面层厚度的进气道-风扇部件试验台为试验载体，借助多孔动态压力探针及表面油流等试验测量技术，并辅之以全三维非定常数值模拟，掌握附面层吸入条件下紧凑S形进气道内部流动分离、复杂涡系结构及出口畸变的形成机理，揭示进气道出口畸变在风扇叶片通道中的传播过程及其对风扇气动性能、稳定裕度的影响规律，以期达到附面层吸入下的半埋入式紧凑S形进气道与风扇耦合机制，为我国高性能军民用飞机和发动机一体化设计提供基础性理论支撑。

未来飞机/推进系统高度集成的翼身融合飞机通过置于飞机尾部的半埋入紧凑S形进气道吸 入机身附面层为发动机提供所需流量，以提高升阻比和隐身性。然而，大量机身附面层低能流 体吸入会导致S形进气道出口畸变成倍增加，对下游风扇气动性能带来巨大挑战，从而影响发动机整体气动性能和稳定性。本项目以半埋入紧凑S形进气道与风扇耦合流动机理为主题，以能调节吸入附面层厚度的进气道-风扇部件试验台为试验载体，借助多孔动态压力探针及表面油流等试验测量技术，并辅之以全三维非定常数值模拟，掌握附面层吸入条件下紧凑S形进气道内部流动分离、复杂涡系结构及出口畸变的形成机理，揭示进气道出口畸变在风扇叶片通道中的传播过程及其对风扇气动性能、稳定裕度的影响规律，为我国高性能军民用飞机和发动机一体化设计提供基础性理论支撑。