The invention provides a distributed hybrid propulsion system with turbine engines and an aircraft, the aircraft comprises a fuselage and wings, the hybrid propulsion system comprises blade tip turbine engines and high-pressure air generators, the wings are symmetrically arranged on the two sides of the fuselage, the end part of each wing is provided with a tilting device, and each tilting device is provided with a blade tip turbine engine and a high-pressure air generator. The blade tip turbine engines are installed on the tilting devices at the ends of the wings, the tilting devices can drive the blade tip turbine engines to rotate, and the high-pressure air generator is arranged in the fuselage and provides high-pressure air for combustion chambers of the blade tip turbine engines. The tilting device is controlled to drive the posture of the turbine engine, so that the aircraft has various flight postures such as vertical take-off and landing, horizontal cruise flight and tilting flight, the blade tip turbine engine does not need to be provided with an air compressor component, and also does not need to be provided with a complex circuit and a transmission system, and the aircraft has the advantages of being light in weight, low in cost, high in reliability and high in flight speed.

    本发明提供一种具有涡轮发动机的分布式混动推进系统及飞行器,飞行器包括机身和机翼,混动推进系统包括叶尖涡轮发动机和高压空气发生器,机翼对称设置在机身两侧,每个机翼的端部均安装有倾转装置,叶尖涡轮发动机安装在各机翼端部的倾转装置上,可由倾转装置带动叶尖涡轮发动机转动,高压空气发生器设置在机身内部,为各叶尖涡轮发动机的燃烧室提供高压空气。通过控制倾转装置带动涡轮发动机的位姿,令飞行器具有垂直起降、水平巡航飞行和倾转飞行等多种飞行姿态,且叶尖涡轮发动机无需设置压气机部件,也无需设置复杂电路和传动系统,具有重量轻、成本低、可靠性高、飞行速度快的优点。


    Access

    Download


    Export, share and cite



    Title :

    Distributed hybrid propulsion system with turbine engine and aircraft


    Additional title:

    一种具有涡轮发动机的分布式混动推进系统及飞行器


    Contributors:
    ZHOU JIN (author) / GUO QINGLIN (author) / FANG QUANSHEN (author) / WANG TAO (author) / ZHOU SIPING (author)

    Publication date :

    2023-06-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Aircraft propulsion system with turbine engine and exhaust condenser

    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

    Free access

    AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER

    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

    Free access

    Aircraft propulsion system with turbine engine and exhaust condenser

    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

    Free access

    HYBRID ELECTRIC AIRCRAFT SYSTEM WITH DISTRIBUTED PROPULSION

    SCHWARZ FREDERICK M / BAIG ZUBAIR AHMED | European Patent Office | 2019

    Free access

    Aircraft propulsion system with turbine engine and exhaust condenser

    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

    Free access