The invention provides a turboshaft engine air inlet system with an efficient filtering function, and relates to the technical field of turboshaft engine helicopter power devices, the turboshaft engine air inlet system comprises a main air inlet pipe, one end of the main air inlet pipe is fixedly provided with a flow direction induction unit, and the other end of the main air inlet pipe is fixedly provided with a differential pressure driving closing valve. By arranging the flow direction inducer and the differential pressure driving closing valve structure, on one hand, under the action of external force, the front induction plate hinge of the flow direction inducer slides backwards in the front induction plate hinge guide rail groove to form a boss, so that gas and solid particles generate downward velocity components, and the particles are prevented from entering an air inlet pipe of an engine; the pressure difference driving closing valve can solve the suck-back condition generated by a particle discharging channel in a traditional inertia particle filtering air inlet channel, the optimal comprehensive aerodynamic performance in the full flight envelope of a helicopter can be achieved, and the risk that particles in the particle discharging channel are reversely sucked into an engine can be eliminated.

    本发明提供一种高效过滤功能的涡轴发动机进气系统,涉及涡轴发动机直升机动力装置技术领域,包括主进气管,所述主进气管的一端固定安装有流向诱导器,所述主进气管的另一端固定安装有压差驱动闭合阀。本发明,通过设置该流向诱导器和压差驱动闭合阀结构,一方面,在外力作用下,流向诱导器的前诱导板铰链在前诱导板铰链导轨槽中向后滑动,形成“凸台”,使气体和固体颗粒产生向下的速度分量,避免颗粒进入发动机进气管中,另一方面,压差驱动闭合阀可以解决传统惯性粒子过滤进气道中的粒子排放通道产生的“倒吸”状况,既可以实现直升机全飞行包线内的综合气动性能最优,又可以能排除将粒子排放通道中粒子反吸入发动机的风险。


    Access

    Download


    Export, share and cite



    Title :

    Turboshaft engine air inlet system with efficient filtering function


    Additional title:

    一种高效过滤功能的涡轴发动机进气系统


    Contributors:
    ZHONG FEIXIONG (author) / JIAO NAN (author)

    Publication date :

    2024-03-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    INLET SEAL FOR A TURBOSHAFT ENGINE

    STEEVES ZACHARIAH | European Patent Office | 2017

    Free access

    Inlet seal for a turboshaft engine

    STEEVES ZACHARIAH | European Patent Office | 2020

    Free access

    1995 Turboshaft Engine Survey

    Online Contents | 1995


    Turboshaft engine with axial compressor

    HANRAHAN PAUL R / KUPRATIS DANIEL BERNARD | European Patent Office | 2022

    Free access

    2001 Turboshaft Engine Survey

    Online Contents | 2001