WO2012019419A1 - 风动透平冲压发动机 - Google Patents

风动透平冲压发动机 Download PDF

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Publication number
WO2012019419A1
WO2012019419A1 PCT/CN2011/000230 CN2011000230W WO2012019419A1 WO 2012019419 A1 WO2012019419 A1 WO 2012019419A1 CN 2011000230 W CN2011000230 W CN 2011000230W WO 2012019419 A1 WO2012019419 A1 WO 2012019419A1
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WO
WIPO (PCT)
Prior art keywords
turbine
pneumatic
pneumatic turbine
ramjet engine
compressor
Prior art date
Application number
PCT/CN2011/000230
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English (en)
French (fr)
Inventor
靳北彪
Original Assignee
Jin Beibiao
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Filing date
Publication date
Application filed by Jin Beibiao filed Critical Jin Beibiao
Publication of WO2012019419A1 publication Critical patent/WO2012019419A1/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/04—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/10—Application in ram-jet engines or ram-jet driven vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/10—Application in ram-jet engines or ram-jet driven vehicles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the invention relates to the field of thermal energy and power, and more particularly to a pneumatic turbine.
  • ramjet engines require high-speed motion to obtain a sufficiently high gas pressure to achieve a satisfactory combustion environment. Therefore, ramjet engines have the problem of having to perform high-speed motion (generally to achieve several Mach or more) to work effectively.
  • high-speed motion generally to achieve several Mach or more
  • turbojet engine and turbofan engine are still widely used as jet engines. Both engines are in high temperature gas due to the rotating shaft and the gas turbine. Medium, so it is difficult to manufacture, the cost is high, and the speed of the gas turbine is difficult to reach a higher level. Because gas turbines are difficult to reach higher levels, these two types of engines are also difficult to drive at higher speeds. use.
  • a pneumatic turbine ramjet engine includes a ram inlet, a combustion chamber, a propulsion nozzle and a pneumatic turbine, the ram inlet being in communication with the combustion chamber, the combustion chamber being in communication with the propulsion nozzle
  • a compressor is disposed in front of and/or inside the ram inlet, and the pneumatic turbine outputs power to the compressor.
  • the compressor is disposed at a front portion of the ram inlet.
  • the compressor is disposed in the middle of the ram inlet.
  • the compressor is disposed at a rear portion of the ram inlet.
  • the compressor is disposed in a high static pressure zone of the ram inlet located in front of the combustion chamber.
  • the aerodynamic turbine outputs power to the compressor via a transmission.
  • the transmission is set to a magnetic gear transmission.
  • the aerodynamic turbine and the compressor are juxtaposed in a direction perpendicular to the advancing direction.
  • the pneumatic turbine ramjet engine further includes an oxidant source, and a high pressure oxidant inlet is provided in the combustion chamber, and the oxidant source is in communication with the high pressure oxidant inlet via an oxidant high pressure pump.
  • the aerodynamic turbine ramjet engine also includes a rocket engine that is juxtaposed with the propulsion nozzle.
  • the pneumatic turbine ramjet engine further includes a pneumatic turbine duct, the wind turbine is disposed in the wind turbine duct, and the stamping air inlet is disposed in the wind turbine duct .
  • the aerodynamic turbine ramjet engine further includes a pneumatic turbine duct, the wind turbine is disposed in the aerodynamic turbine duct, and the wind turbine duct is disposed in the stamping air inlet .
  • the aerodynamic turbine ramjet engine further includes a pneumatic turbine duct, the aerodynamic turbine is disposed in the aerodynamic turbine duct, and the ram inlet and the aerodynamic turbine duct are juxtaposed Settings.
  • the principle of the present invention is to use a relatively high-speed moving airflow formed outside the intake port of a ramjet engine to make a pneumatic turbine using a ramjet for linear, curved or circular motion, the pneumatic turbine being disposed upstream of the ramjet combustion chamber.
  • the compressor outputs power, which will increase the speed of the airflow that has entered the ramjet intake and/or will enter the ramjet intake, which is increased by the increased speed of the pressurized airflow in the ram inlet
  • the kinetic energy is converted into pressure energy in the nip, and the pressure is further increased to form an efficient combustion condition.
  • the intake air and fuel are combusted in the combustion chamber and then ejected at high speed through the propulsion nozzle to obtain the driving force of the ramjet engine.
  • the ramjet engine is the simplest engine at present, but due to its structure and circulation form, the high-speed airflow can only compress itself. This requires high-speed airflow with a relatively high speed (ie kinetic energy) to achieve the pressure in the combustion chamber. Some heights, good combustion efficiency and high-speed jet air flow, create conditions for ramjet engines to achieve high propulsion. In order to achieve this process, it is necessary to make the speed of the ramjet engine a few Mach or more, which severely limits the practical application of the ramjet engine.
  • the essence of the disclosed pneumatic turbine ramjet engine is to utilize a part of the high-speed airflow to help another part of the high-speed airflow to achieve the required stamping conditions and static pressure, thereby realizing the efficient operation of the ramjet, the essence of which is the stamping pressure and the wind.
  • the gas pressure generated by the compressor driven by the moving turbine is superimposed to increase the pressure of the airflow before the combustion reaction in the ramjet engine.
  • the pneumatic turbine ramjet disclosed by the present invention can produce a low-cost spray by eliminating the need for a high-cost, expensive power turbine in the combustion chamber and in the high-temperature airflow after the combustion chamber.
  • the gas engine can be used to manufacture various types of aircraft, such as airplanes and missiles.
  • the so-called pneumatic turbine refers to a turbine that outputs power under the action of a gas flow (ie, an impeller mechanism);
  • the so-called ram inlet refers to an intake port of a ramjet engine (also referred to as a diffuser),
  • the high-speed airflow converts kinetic energy into pressure energy in its interior;
  • the so-called propulsion nozzle refers to a nozzle that converts the energy of high-temperature and high-pressure gas into a high-speed jet of kinetic energy to obtain a reaction force;
  • the so-called compressor refers to an impeller-type compressor, and the air is The compressor is boosted;
  • the so-called pneumatic turbine duct is a gas passage with a pneumatic turbine inside, which is used to push the pneumatic turbine more efficiently with high-speed airflow.
  • the "the pneumatic turbine outputs power to the compressor” means that the pneumatic turbine rotates under the action of the airflow, and the rotary power is used to rotate the compressor, 3 inches. Another air flow is supercharged, and the pneumatic turbine can transmit power to the compressor in any form of transmission, such as coaxial transmission, transmission via a shifting mechanism, etc.;
  • the purpose of the mechanism to transmit power to the compressor is to adjust the transmission ratio to meet the requirements of different conditions such as take-off, endurance and landing of the aircraft.
  • the purpose of setting the oxidant source is to meet the requirements of the engine thrust for different working conditions such as take-off, endurance and landing of the aircraft. For example, when the aircraft takes off, the supercharging capacity of the compressor is also lower due to the lower speed. Low, at which time the thrust can be increased by introducing an oxidant into the combustion chamber and increasing the amount of fuel, and it is only necessary to introduce an oxidant into the combustion chamber as necessary.
  • the purpose of providing a rocket engine in the system of the disclosed turbomachinery ramjet engine is also to meet engine thrust requirements for different operating conditions such as take-off, cruising and landing of the aircraft, which can be operated only when necessary.
  • the term "front” refers to the direction from the inlet of the ram inlet to the opposite direction of the flow of the airflow; the so-called “upstream” refers to the upstream of the flow of the airflow; the so-called oxidant refers to a substance that can react with the fuel, such as oxygen, Hydrogen peroxide, etc.
  • the so-called high static pressure zone refers to a region where the gas pressure before combustion is high in the ram inlet; the purpose of setting the compressor in the high static pressure zone is to increase the compressor Work efficiency.
  • the pneumatic turbine can be set as an upwind angle adjustable pneumatic turbine to meet the needs of different working conditions.
  • all necessary components, units, and systems such as valves, pumps, sensors, various mechanisms, and control systems are provided where necessary in accordance with well-known techniques in the fields of thermal energy and power (including the field of jet engines).
  • a high-pressure oxidant injection port may be provided in the ram inlet and/or a high-pressure working fluid injection port may be provided in the propulsion nozzle to assist the present.
  • the disclosed pneumatic turbine ramjet engine is activated.
  • turbomachinery ramjet engine there are no moving parts in the high temperature airflow after the combustion chamber and the combustion chamber, which reduces the manufacturing cost of the jet engine.
  • Embodiment 1 is a schematic structural view of Embodiment 1 of the present invention.
  • Embodiment 2 is a schematic structural view of Embodiment 2 of the present invention.
  • Embodiment 3 is a schematic structural view of Embodiment 3 of the present invention.
  • Embodiment 4 is a schematic structural view of Embodiment 4 of the present invention.
  • Figure 5 is a cross-sectional view taken along line A-A of Figure 4.
  • Figure 6 is a schematic structural view of Embodiment 5 of the present invention.
  • Figure 7 is a schematic structural view of Embodiment 6 of the present invention.
  • Figure 8 is a schematic structural view of Embodiment 7 of the present invention.
  • FIG. 9 is a schematic structural view of Embodiment 8 of the present invention.
  • Figure 10 is a schematic structural view of Embodiment 9 of the present invention.
  • Figure 1 is a schematic structural view of Embodiment 10 of the present invention.
  • the pneumatic turbine ramjet engine shown in Fig. 1 comprises a ram inlet 1, a combustion chamber 2, a propulsion nozzle 3 and a pneumatic turbine 4, and the ram inlet 1 is in communication with the combustion chamber 2, the combustion chamber 2 and the propulsion
  • the nozzle 3 is connected, and a compressor 100 is provided inside the ram inlet 1, and the pneumatic turbine 4 outputs power to the compressor 100.
  • the compressor 100 may also be disposed at the front of the ram inlet 1, or The compressor 100 is disposed in the middle of the ram inlet 1, or the compressor 100 is disposed at the rear of the ram inlet 1; the purpose of this arrangement is to increase the efficiency of the compressor 100.
  • the pneumatic turbine ramjet engine shown in FIG. 2 differs from the first embodiment in that: the pneumatic turbine ramjet engine further includes a pneumatic turbine duct 5, and the wind turbine turbine 4 is disposed in the wind turbine culvert. In the road 5, the ram inlet 1 is provided in the wind turbine duct 5 .
  • the pneumatic turbine ramjet engine shown in FIG. 3 differs from the second embodiment in that: a compressor 100 is provided inside the ram inlet 1, and the compressor 100 is disposed in a ram inlet port located in front of the combustion chamber 2. 1 in the high static pressure zone.
  • the purpose of providing the compressor in the high static pressure zone is to increase the operating efficiency of the compressor.
  • the wind turbine ramjet shown in FIG. 4 and FIG. 5 differs from the first embodiment in that: the pneumatic turbine ramjet engine further comprises a pneumatic turbine duct 5, and the wind turbine 4 is arranged in the air. In the turbine duct 5, the pneumatic turbine duct 5 is arranged in the ram inlet 1.
  • the pneumatic turbine ramjet engine shown in FIG. 6 differs from the first embodiment in that: the aerodynamic turbine ramjet engine further includes a pneumatic turbine duct 5, and the wind turbine turbine 4 is disposed in the wind turbine culvert. In the road 5, the ram inlet 1 and the aerodynamic turbine duct 5 are arranged side by side.
  • the pneumatic turbine ramjet shown in Fig. 7 differs from the third embodiment in that the pneumatic turbine 4 outputs power to the compressor 100 via the transmission 410.
  • the purpose of the aerodynamic turbine to output power to the compressor via the transmission is to adjust the transmission ratio to meet the requirements of different conditions such as aircraft take-off, endurance and landing.
  • the pneumatic turbine ramjet engine shown in Fig. 8 differs from the embodiment 6 in that the transmission 410 is set as the magnetic gear transmission 41 1 .
  • Example 8 The pneumatic turbine ramjet engine shown in Fig. 9 differs from the first embodiment in that the aerodynamic turbine 4 and the compressor 100 are juxtaposed in a direction perpendicular to the advancing direction.
  • the pneumatic turbine ramjet engine shown in FIG. 10 differs from the first embodiment in that: the pneumatic turbine ramjet engine further includes an oxidant source 2001, and a high-pressure oxidant inlet port 200 is disposed in the combustion chamber 2,
  • the oxidant source 2001 is in communication with the high pressure oxidant inlet 200 via an oxidant high pressure pump 2002.
  • the purpose of setting the oxidant source is to meet the requirements of engine thrust for different working conditions such as take-off, endurance and landing of the aircraft. For example, when the aircraft takes off, the compressor's supercharging capacity will be lower due to the lower speed.
  • the thrust can be increased by introducing an oxidant into the combustion chamber and increasing the amount of fuel, but it is only necessary to introduce an oxidant into the combustion chamber as necessary.
  • the pneumatic turbine ramjet engine shown in FIG. 11 differs from the first embodiment in that: the pneumatic turbine ramjet engine further includes a rocket engine 3000, which is juxtaposed with the propulsion nozzle 3 Settings.
  • the purpose of setting up the rocket engine is also to meet the engine thrust requirements of different operating conditions such as take-off, cruising and landing of the aircraft.
  • the rocket engine can only work when necessary.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
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Description

说 明 书
风动透平冲压发动机
技术领域
本发明涉及热能与动力领域， 尤其是一种风动透平冲压发动机。
背景技术
传统冲压发动机需要做高速运动才能获得足够高的气体压力， 进而才能获 得满意的燃烧环境， 所以冲压发动机存在必须作高速运动（一般说来要达到数 马赫以上）才能有效工作的难题。 然而作如此高速的运动会产生一系列难以解 决的问题，所以目前作为喷气式发动机被广泛应用的仍然是涡轮喷气发动机和 涡扇发动机， 这两种发动机由于转动轴和燃气透平都处于高温燃气之中， 所以 难以制造， 成本也高， 而且燃气透平的转速也很难达到更高的水平， 由于燃气 透平很难达到更高的水平， 所以这两类发动机也很难在更高速度下使用。
如果能够发明一种充分利用冲压发动机和涡轮喷气发动机以及含涡扇发 动机的各自优点， 又能躲避在燃烧室内设置动力涡轮这一结构的新型发动机， 就可以使喷气发动机的制造成本大幅度降低。
发明内容
为了解决上述问题， 本发明提出的技术方案如下：
一种风动透平冲压发动机， 包括冲压进气道、 燃烧室、 推进喷管和风动透 平， 所述冲压进气道与所述燃烧室连通， 所述燃烧室与所述推进喷管连通， 在 所述冲压进气道的前方和 /或内部设压气机， 所述风动透平对所述压气机输出 动力。
所述压气机设在所述冲压进气道的前部。
所述压气机设在所述冲压进气道的中部。
所述压气机设在所述冲压进气道的后部。
所述压气机设在位于所述燃烧室前的所述冲压进气道的高静压区内。 所述风动透平经变速器对所述压气机输出动力。
所述变速器设为磁齿轮变速器。
所述风动透平和所述压气机在与前进方向垂直的方向上并列设置。 所述风动透平冲压发动机还包括氧化剂源，在所述燃烧室上设高压氧化剂 导入口， 所述氧化剂源经氧化剂高压泵与所述高压氧化剂导入口连通。
所述风动透平冲压发动机还包括火箭发动机，所述火箭发动机与所述推进 喷管并列设置。
所述风动透平冲压发动机还包括风动透平涵道，所述风动透平设在所述风 动透平涵道内， 所述冲压进气道设在所述风动透平涵道内。
所述风动透平冲压发动机还包括风动透平涵道，所述风动透平设在所述风 动透平涵道内， 所述风动透平涵道设在所述冲压进气道内。
所述风动透平冲压发动机还包括风动透平涵道，所述风动透平设在所述风 动透平涵道内， 所述冲压进气道和所述风动透平涵道并列设置。
本发明的原理是利用冲压发动机作直线、曲线或圆周运动时在冲压发动机 进气道以外形成的相对高速运动的气流推动风动透平， 此风动透平对设置在冲 压发动机燃烧室上游的压气机输出动力， 此压气机将已进入冲压发动机进气道 和 /或将要进入冲压发动机进气道的气流进行增速增压， 此被增速增压的气流 在冲压发动机进气道的增压区内将动能转换成压力能， 压力进一步提高， 形成 高效燃烧条件。进气和燃料在燃烧室内燃烧后通过推进喷管高速喷出， 使冲压 发动机获得推动力。
冲压发动机是目前结构最为简单的发动机，但是由于它的结构和循环形式 使得高速气流只能对自身压縮， 这样就要求高速气流具有相当高的速度（即动 能）才能使燃烧室内的压力达到应有的高度， 形成良好燃烧效率和高速喷射气 流， 为冲压发动机实现高推动力创造条件。 为了实现这一过程， 就必须使冲压 发动机的运动速度达到数马赫以上， 这样严重限制了冲压发动机实际应用。 本 发明所公开的风动透平冲压发动机的实质就是利用一部分高速气流帮助另一 部分高速气流达到所需要的冲压条件和静压压力， 实现冲压发动机的高效工 作，其实质是把冲压压力和由风动透平所带动的压气机所产生的气体压力相叠 加， 以提高冲压发动机内燃烧反应前的气流的压力。
本发明所公开的风动透平冲压发动机由于在燃烧室以及在燃烧室以后的 高温气流中不需要耐高温的造价昂贵的动力涡轮，所以可以制造出成本低的喷 气发动机， 可以用于制造各类飞行器， 如飞机、 导弹等。
本发明中， 所谓的风动透平是指在气流作用下输出动力的透平（即叶轮机 构）； 所谓的冲压进气道是指冲压发动机的进气道（也称为扩压器）， 高速气流 在其内部将动能转化成压力能； 所谓推进喷管是指将高温高压气体的能量变成 气体的动能高速喷射获得反作用力的喷管； 所谓压气机是指叶轮式压气机， 空 气在压气机内被升压； 所谓风动透平涵道是指内部设有风动透平的气体通道， 其作用是利用高速气流更有效地推到风动透平。
本发明中所谓 "所述风动透平对所述压气机输出动力"是指所述风动透平 在气流的作用下发生旋转， 利用这一旋转动力使所述压气机发生旋转， 3寸另一 股气流进行增压，所述风动透平对所述压气机传输动力的形式可以是任意一种 传输形式， 例如共轴传输、 经变速机构传输等； 所述风动透平经变速机构对所 述压气机传输动力的目的是通过调整传动比以满足飞行器起飞、续航和着陆等 不同工况的要求。
本发明中， 设置氧化剂源的目的是为了满足飞行器起飞、续航和着陆等不 同工况对发动机推力的要求， 例如在飞行器起飞时， 由于速度较低， 所述压气 机的增压能力也会较低， 而这时可以通过向所述燃烧室内导入氧化剂并增加燃 料的量， 以增加推力， 只需在必要时向所述燃烧室内导入氧化剂。 在本发明所 公开风动透平冲压发动机的系统中设置火箭发动机的目的也是为了满足飞行 器起飞、续航和着陆等不同工况对发动机推力的要求， 所述火箭发动机可以只 在必要时工作。
本发明中， 所谓前方是指从冲压进气道进口向气流流动的反方向的指向； 所谓上游是指气流流动的上游； 所谓的氧化剂是指可以与燃料发生燃烧化学反 应的物质， 如氧、 双氧水等。
本发明中，所谓的高静压区是指处于所述冲压进气道内的燃烧前气体压力 较高的区域； 将所述压气机设在高静压区内的目的是为了提高所述压气机的工 作效率。
在本发明所公开风动透平冲压发动机中，所述风动透平可以设为迎风角可 调式风动透平， 以满足不同工况的需要。 本发明中， 根据热能与动力领域（包括喷气发动机领域） 的公知技术， 在 必要的地方设置阀、 泵、 传感器、 各类机构、 控制系统等一切必要的部件、 单 元和系统。
在本发明所公开风动透平冲压发动机中，在必要的时候可以在所述冲压进 气道内设高压氧化剂喷射口和 /或在所述推进喷管内设高压工质喷射口用来帮 助本发明所公开的风动透平冲压发动机启动。
本发明的有益效果如下：
在本发明所公开风动透平冲压发动机中，在燃烧室以及燃烧室以后的高温 气流中没有运动部件， 降低了喷气式发动机的制造成本。
附图说明
图 1为本发明实施例 1的结构示意图；
图 2为本发明实施例 2的结构示意图；
图 3为本发明实施例 3的结构示意图；
图 4为本发明实施例 4的结构示意图；
图 5为图 4的 A— A向剖视图；
图 6为本发明实施例 5的结构示意图；
图 7为本发明实施例 6的结构示意图；
图 8为本发明实施例 7的结构示意图；
图 9为本发明实施例 8的结构示意图；
图 10为本发明实施例 9的结构示意图；
图 1 1为本发明实施例 10的结构示意图。
具体实施方式
实施例 1
如图 1所示的风动透平冲压发动机， 包括冲压进气道 1、 燃烧室 2、 推进 喷管 3和风动透平 4， 冲压进气道 1 与燃烧室 2连通， 燃烧室 2与推进喷管 3 连通， 在冲压进气道 1的前方内部设压气机 100， 风动透平 4对压气机 100输 出动力。
具体实施时， 所述压气机 100还可以设在所述冲压进气道 1的前部， 或所 述压气机 100设在所述冲压进气道 1的中部，或所述压气机 100设在所述冲压 进气道 1的后部； 这样设置的目的是为了提高所述压气机 100的效率。
实施例 2
如图 2所示的风动透平冲压发动机， 其与实施例 1的区别在于： 风动透平 冲压发动机还包括风动透平涵道 5， 风动透平 4设在风动透平涵道 5内， 冲压 进气道 1设在风动透平涵道 5内。
实施例 3
如图 3所示的风动透平冲压发动机， 其与实施例 2的区别在于： 在冲压进 气道 1 的内部设压气机 100， 压气机 100设在位于燃烧室 2前的冲压进气道 1 的高静压区内。将所述压气机设在高静压区内的目的是为了提高所述压气机的 工作效率。
实施例 4
如图 4和图 5所示的风动透平冲压发动机， 其与实施例 1的区别在于： 风 动透平冲压发动机还包括风动透平涵道 5，风动透平 4设在风动透平涵道 5内， 风动透平涵道 5设在冲压进气道 1内。
实施例 5
如图 6所示的风动透平冲压发动机， 其与实施例 1的区别在于： 风动透平 冲压发动机还包括风动透平涵道 5， 风动透平 4设在风动透平涵道 5内， 冲压 进气道 1和风动透平涵道 5并列设置。
实施例 6
如图 7所示的风动透平冲压发动机， 其与实施例 3的区别在于： 风动透平 4经变速器 410对压气机 100输出动力。 所述风动透平经变速器对所述压气机 输出动力的目的是通过调整传动比以满足飞行器起飞、续航和着陆等不同工况 的要求。
实施例 7
如图 8所示的风动透平冲压发动机，其与实施例 6的区别在于：变速器 410 设为磁齿轮变速器 41 1。
实施例 8 如图 9所示的风动透平冲压发动机， 其与实施例 1的区别在于： 所述风动 透平 4和所述压气机 100在与前进方向垂直的方向上并列设置。
实施例 9
如图 10所示的风动透平冲压发动机， 其与实施例 1 的区别在于： 所述风 动透平冲压发动机还包括氧化剂源 2001，在所述燃烧室 2上设高压氧化剂导入 口 200，所述氧化剂源 2001经氧化剂高压泵 2002与所述高压氧化剂导入口 200 连通。 设置氧化剂源的目的是为了满足飞行器起飞、续航和着陆等不同工况对 发动机推力的要求， 例如在飞行器起飞时， 由于速度较低， 所述压气机的增压 能力也会较低， 而这时可以通过向所述燃烧室内导入氧化剂并增加燃料的量， 以增加推力， 但只需在必要时向所述燃烧室内导入氧化剂。
实施例 10
如图 1 1所示的风动透平冲压发动机， 其与实施例 1 的区别在于： 所述风 动透平冲压发动机还包括火箭发动机 3000， 所述火箭发动机 3000与所述推进 喷管 3并列设置。 设置火箭发动机的目的也是为了满足飞行器起飞、 续航和着 陆等不同工况对发动机推力的要求， 所述火箭发动机可以只在必要时工作。
显然， 本发明不限于以上实施例， 还可以有许多变形。 本领域的普通技术 人员， 能从本发明公开的内容直接导出或联想到的所有变形， 均应认为是本发 明的保护范围。

Claims

权 利 要 求
1、 一种风动透平冲压发动机， 包括冲压进气道 （1 )、 燃烧室 （2)、 推进 喷管 （3)和风动透平 （4)， 其特征在于： 所述冲压进气道 （1 ) 与所述燃烧室
(2 ) 连通， 所述燃烧室 （2) 与所述推进喷管 （3) 连通， 在所述冲压进气道 ( 1 )的前方和 /或内部设压气机（100)，所述风动透平（4)对所述压气机（100) 输出动力。
2、如权利要求 1所述风动透平冲压发动机，其特征在于：所述压气机（100) 设在所述冲压进气道 （1 ) 的前部。
3、如权利要求 1所述风动透平冲压发动机，其特征在于：所述压气机（100) 设在所述冲压进气道 （1 ) 的中部。
4、如权利要求 1所述风动透平冲压发动机，其特征在于：所述压气机（100) 设在所述冲压进气道 （1 ) 的后部。
5、如权利要求 1所述风动透平冲压发动机，其特征在于：所述压气机（100) 设在位于所述燃烧室 （2) 前的所述冲压进气道 （1 ) 的高静压区内。
6、 如权利要求 1 所述风动透平冲压发动机， 其特征在于： 所述风动透平 (4) 经变速器 （410) 对所述压气机 （100) 输出动力。
7、如权利要求 6所述风动透平冲压发动机，其特征在于：所述变速器（410) 设为磁齿轮变速器 （41 1 )。
8、 如权利要求 1 所述风动透平冲压发动机， 其特征在于： 所述风动透平 (4) 和所述压气机 （100) 在与前进方向垂直的方向上并列设置。
9、 如权利要求 1 所述风动透平冲压发动机， 其特征在于： 所述风动透平 冲压发动机还包括氧化剂源（2001 )， 在所述燃烧室（2)上设高压氧化剂导入 口 （200)， 所述氧化剂源 （2001 ) 经氧化剂高压泵 （2002 ) 与所述高压氧化剂 导入口 （200) 连通。
10、 如权利要求 1所述风动透平冲压发动机， 其特征在于： 所述风动透平 冲压发动机还包括火箭发动机 （3000)， 所述火箭发动机 （3000) 与所述推进 喷管 （3) 并列设置。
1 1、 如权利要求 1、 2、 3、 4、 5、 6、 7、 9或 10所述风动透平冲压发动机， 其特征在于： 所述风动透平冲压发动机还包括风动透平涵道 (5), 所述风动透: 平 （4) 设在所述风动透平涵道 （5 ) 内， 所述冲压进气道 （1 ) 设在所述风动 : 透平涵道 （5) 内。
12、 如权利要求 1、 2、 3、 4、 5、 6、 7、 9或 10所述风动透平冲压发动机， 其特征在于： 所述风动透平冲压发动机还包括风动透平涵道（5)， 所述风动透 平 （4) 设在所述风动透平涵道 （5 ) 内， 所述风动透平涵道 （5) 设在所述冲 压进气道 （1 ) 内。
13、 如权利要求 8、 9或 10所述风动透平冲压发动机， 其特征在于： 所述 风动透平冲压发动机还包括风动透平涵道 （5)， 所述风动透平 （4) 设在所述 风动透平涵道 （5) 内， 所述冲压进气道 （1 ) 和所述风动透平涵道 （5 ) 并列 设置。
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