WO2012051783A1 - Jet engine with parallel combustion chambers - Google Patents
Jet engine with parallel combustion chambers Download PDFInfo
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- WO2012051783A1 WO2012051783A1 PCT/CN2011/000300 CN2011000300W WO2012051783A1 WO 2012051783 A1 WO2012051783 A1 WO 2012051783A1 CN 2011000300 W CN2011000300 W CN 2011000300W WO 2012051783 A1 WO2012051783 A1 WO 2012051783A1
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- Prior art keywords
- power turbine
- duct
- jet
- jet propulsion
- compressor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
Definitions
- the present invention relates to the field of thermal energy, power and propulsion, and more particularly to a parallel combustor jet engine. Background technique
- a parallel combustor jet engine including a power turbine duct, a jet propulsion duct, an intake port, a compressor, and a power turbine, wherein the compressor is provided In the intake passage, the power turbine duct is in communication with the intake passage, a power turbine combustion chamber is disposed in the power turbine duct, and the power turbine is disposed in the power turbine combustion Inside the power turbine duct behind the chamber, the power turbine outputs power to the compressor, the jet propulsion duct is in communication with the intake port, and a jet propulsion is provided in the jet propulsion duct In the combustion chamber, the jet propulsion combustion chamber is in communication with the jet propulsion nozzle.
- a parallel combustor jet engine includes a power turbine duct, a jet propulsion duct, an intake passage, a compressor, and a power turbine, the compressor being disposed in the intake passage, the power turbine duct Communicating with the intake passage, a power turbine external combustion heating zone is disposed in the power turbine duct, and the power turbine is disposed at the power turbine culvert behind the power turbine external combustion heating zone Inside the track, the power turbine outputs power to the compressor, the jet propulsion duct is in communication with the intake port, and a jet propulsion combustion chamber is disposed in the jet propulsion duct, the jet propulsion combustion chamber Connected to the jet propulsion nozzle.
- the power turbine duct set is disposed within the jet propulsion duct.
- the power turbine ducts are juxtaposed with the jet propulsion ducts.
- One of the power turbine ducts is juxtaposed with two or more of the jet propulsion ducts.
- the rotational speed of the power turbine is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan jet engine.
- the diameter of the power turbine is smaller than the diameter of a power turbine of a conventional turbojet engine having the same propulsion force and the diameter of a power turbine of a conventional turbofan jet engine having an equivalent propulsion force. Pressure and pressure at the compressor outlet of the turbofan engine.
- a fan is provided in front of the compressor.
- the principle of providing the power turbine combustion chamber and the jet propulsion combustion chamber is to divide the high pressure air generated by the compressor and the intake passage into at least two parts, at least a part of which enters Deriving a power turbine duct, the remainder entering the jet propulsion duct, and the high pressure air entering the power turbine duct drives the power turbine to rotate after a combustion chemical reaction occurs in the power turbine combustor,
- the power turbine pushes the compressor to rotate, and the high pressure air entering the jet propulsion duct enters the combustion reaction reaction in the jet propulsion combustion chamber without the requirement of propulsion of the working fluid passing through the power turbine Propulsion nozzles generate propulsion.
- the principle of providing the power turbine external combustion heating zone and the jet propulsion combustion chamber is to divide the high pressure air generated by the compressor and the intake port into at least two parts, at least a part of which Entering the power turbine duct, the rest entering the jet propulsion duct, and the high pressure air entering the power turbine duct is driven to rotate the power turbine after being heated by the power turbine external combustion heating zone,
- the power turbine pushes the compressor to rotate, and there is no requirement for propulsion of the working fluid through the power turbine, and the heat source of the power turbine external combustion heating zone is introduced through the wall of the jet propulsion combustion chamber
- the working fluid of the power turbine duct has only one task, that is, As far as possible, all the energy of the working medium itself is used to drive the power turbine to rotate, and the compressor is outputted with power, and does not undertake or rarely undertake the task of obtaining the reverse thrust by the injection, so that a part of the impeller of the power turbine can be realized.
- the reduction of the flat working temperature can greatly increase the rotational speed of the power turbine, thereby greatly increasing the rotational speed of the compressor, increasing the pressure ratio of the compressor, and finally achieving the purpose of improving the efficiency of the engine.
- the working fluid passing through the duct of the power turbine that is, the working fluid passing through the power turbine does not bear or seldom undertake the task of obtaining the reverse thrust by the injection, so the dynamic turbine duct
- the flux can be greatly reduced.
- the impeller diameter of the power turbine can also be greatly reduced. Due to the reduction of the diameter of the power turbine impeller, the centrifugal force required by the impeller can be greatly reduced, so Increasing the rotational speed of the power turbine, achieving the increase in the rotational speed of the compressor, achieving a higher pressure ratio, and ultimately improving the efficiency of the engine.
- the so-called “the power turbine to the compressor output power” means that the power turbine pushes the compressor to rotate, including a coaxial arrangement, and also includes a pushing action of a constant speed or a shifting structure via a gear or the like;
- the so-called power turbine combustion chamber refers to a combustion chamber disposed in the duct of the power turbine, and functions to generate a working fluid for pushing the power turbine;
- the so-called jet propulsion combustion chamber is disposed at the jet propulsion culvert a combustion chamber in the passage, the function of which is to generate a working fluid entering the propulsion nozzle, and the propulsion force is generated by the propulsion nozzle;
- the so-called power turbine external combustion heating zone refers to the wall of the dynamic turbine duct
- the function is to heat the high-pressure air in the duct of the power turbine, and the heat source may be heat from the jet propulsion combustion chamber wall, or may be other heat sources.
- the invention achieves high efficiency, low emissions and low cost of the turbojet 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
- 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 schematic structural view of Embodiment 5 of the present invention.
- Figure 6 is a schematic structural view of Embodiment 6 of the present invention.
- Figure 7 is a schematic structural view of Embodiment 7 of the present invention.
- Figure 8 is a schematic structural view of Embodiment 8 of the present invention.
- Figure 9 is a schematic view showing the structure of Embodiment 9 of the present invention.
- the parallel combustor jet engine shown in FIG. 1 includes a power turbine duct 1, a jet propulsion duct 2, an intake port 3, a compressor 4, and a power turbine 5, and the compressor 4 is disposed in the inlet In the air passage 3, the power turbine duct 1 is in communication with the air inlet 3, and a power turbine combustion chamber 6 is disposed in the power turbine duct 1, and the power turbine 5 is disposed in the Inside the power turbine duct 1 behind the power turbine combustion chamber 6, the power turbine 5 outputs power to the compressor 4, and the jet propulsion duct 2 communicates with the air inlet 3, a jet propulsion combustion chamber 7 is disposed in the jet propulsion duct 2, the jet propulsion combustion chamber 7 is in communication with the jet propulsion nozzle 8, and the power turbine duct 1 is set in the jet propulsion duct 2; Adjusting an air-fuel ratio in the power turbine combustion chamber 6 such that an air-fuel ratio in the power turbine combustion chamber 6 is greater than an air-fuel ratio in a combustion chamber of a conventional turbojet engine and an air-fuel ratio in
- the rotational speed of the power turbine 5 is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan engine, the diameter of the power turbine 5 being smaller than the conventional turbine having the same propulsion force
- the diameter of the power turbine of the jet engine and the diameter of the power turbine of a conventional turbofan engine having the same propulsion, the pressure of the output gas of the compressor 4 being greater than the pressure and turbofan of the compressor outlet of the conventional turbojet engine The pressure at the compressor outlet of the engine.
- the parallel combustor jet engine shown in FIG. 2 includes a power turbine duct 1, a jet propulsion duct 2, an intake port 3, a compressor 4, and a power turbine 5, and the compressor 4 is disposed in the inlet In the air passage 3, the power turbine duct 1 is in communication with the air inlet 3, and a power transmission is provided in the power turbine duct 1 a flat external combustion heating zone 60, the power turbine 5 is disposed inside the power turbine duct 1 behind the power turbine external combustion heating zone 60, and the power turbine 5 outputs the compressor 4 Power, the jet propulsion duct 2 is in communication with the intake passage 3, and a jet propulsion combustion chamber 7 is disposed in the jet propulsion duct 1 and the jet propulsion combustion chamber 7 is in communication with the jet propulsion nozzle 8
- the set of power turbine ducts 1 is disposed within the jet propulsion duct 2 .
- the rotational speed of the power turbine 5 is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan engine, the diameter of the power turbine 5 being smaller than the conventional turbine having the same propulsion force
- the diameter of the power turbine of the jet engine and the diameter of the power turbine of a conventional turbofan engine having the same propulsion, the pressure of the output gas of the compressor 4 being greater than the pressure and turbofan of the compressor outlet of the conventional turbojet engine The pressure at the compressor outlet of the engine.
- a parallel combustor jet engine as shown in FIG. 3 differs from the embodiment 2 in that: the power turbine duct 1 extends to the rear of the jet propulsion nozzle 8, the compressor 4 and the power Turbo 5 coaxial setting.
- the parallel combustor jet engine shown in Fig. 4 differs from the first embodiment in that a fan 330 is provided in front of the compressor 4.
- the parallel combustor jet engine shown in Fig. 5 differs from the embodiment 4 in that a fan duct 333 is provided at the fan 330.
- the parallel combustor jet engine shown in Fig. 6 differs from the first embodiment in that the parallel combustor jet engine further includes a starting device 10 that outputs power to the compressor 4.
- the parallel combustor jet engine shown in FIG. 7 differs from the second embodiment in that a fan 330 is disposed in front of the compressor 4 to constitute the jet propulsion combustion chamber 7 and the power turbine external combustion heating zone.
- the parallel combustor jet engine shown in Fig. 8 differs from the first embodiment in that the power turbine duct 1 is juxtaposed with the jet propulsion duct 2.
- the parallel combustor jet engine shown in Fig. 9 differs from the first embodiment in that one of the power turbine ducts 1 is juxtaposed with two of the jet propulsion ducts 2.
Abstract
A jet engine with parallel combustion chambers is provided, which includes a power turbine duct (1), a jet-propelment duct (2), an intake duct (3), an air compressor (4) and a power turbine (5). The air compressor (4) is arranged in the intake duct (3), and the power turbine duct (1) is communicated with the intake duct (3). A power turbine combustion chamber (6) is disposed in the power turbine duct (1). The power turbine (5) is arranged in the power turbine duct (1) behind the power turbine combustion chamber (6). The power turbine (5) outputs power to the air compressor (4). The jet-propelment duct (2) is communicated with the intake duct (3). In the jet-propelment duct (2) is provided a jet-propelment combustion chamber (7) which is communicated with a jet-propelment nozzle (8). The engine realizes high efficiency, low pollutant emission and low cost.
Description
燃烧室并联的喷气发动机 技术领域 Jet engine with parallel combustion chamber
本发明涉及热能、 动力与推进领域， 尤其是一种并联燃烧室喷气发动机。 背景技术 The present invention relates to the field of thermal energy, power and propulsion, and more particularly to a parallel combustor jet engine. Background technique
传统涡轮喷气发动机或涡轮风扇发动机经过动力透平的工质仍然具有很 高的温度、 压力， 再通过喷管喷出获得反推力， 换句话说， 在这类发动机中， 通过动力透平的工质具有两个任务： 一是推动动力透平旋转， 二是要经过喷管 喷出获得反推力。 这种结构设置必然导致动力透平的叶轮全部均在高温下工 作， 所以需要造价昂贵的材料的量较大， 最终导致这类发动机的成本升高。 因 此， 急需发明一种动力透平的一部分叶轮在较高温度下工作， 另一部分叶轮在 相对较低的温度下工作，或者动力透平的所有叶轮均在较低温度下工作的涡轮 喷气发动机或涡轮风扇发动机。 Conventional turbojet or turbofan engines still have high temperature and pressure through the power of the turbine, and then sprayed through the nozzle to obtain the reverse thrust. In other words, in this type of engine, through the power turbine Quality has two tasks: one is to push the power turbine to rotate, and the other is to spray the nozzle to obtain the reverse thrust. This structural arrangement inevitably results in all of the impellers of the power turbine operating at high temperatures, so the amount of material that is expensive to manufacture is large, ultimately resulting in an increase in the cost of such engines. Therefore, it is urgent to invent a part of a power turbine that operates at a higher temperature, another part of the impeller operates at a relatively low temperature, or all of the impellers of a power turbine operate at a lower temperature or Turbofan engine.
发明内容 Summary of the invention
为了解决上述问题， 本发明提出的技术方案如下- 一种并联燃烧室喷气发动机，包括动力透平涵道、喷气推进涵道、进气道、 压气机和动力透平， 所述压气机设在所述进气道内， 所述动力透平涵道与所述 进气道连通， 在所述动力透平涵道内设动力透平燃烧室， 所述动力透平设置在 所述动力透平燃烧室后方的所述动力透平涵道内部，所述动力透平对所述压气 机输出动力， 所述喷气推进涵道与所述进气道连通， 在所述喷气推进涵道内设 喷气推进燃烧室， 所述喷气推进燃烧室与喷气推进喷管连通。 In order to solve the above problems, the technical solution proposed by the present invention is as follows - a parallel combustor jet engine including a power turbine duct, a jet propulsion duct, an intake port, a compressor, and a power turbine, wherein the compressor is provided In the intake passage, the power turbine duct is in communication with the intake passage, a power turbine combustion chamber is disposed in the power turbine duct, and the power turbine is disposed in the power turbine combustion Inside the power turbine duct behind the chamber, the power turbine outputs power to the compressor, the jet propulsion duct is in communication with the intake port, and a jet propulsion is provided in the jet propulsion duct In the combustion chamber, the jet propulsion combustion chamber is in communication with the jet propulsion nozzle.
一种并联燃烧室喷气发动机，包括动力透平涵道、喷气推进涵道、进气道、 压气机和动力透平， 所述压气机设在所述进气道内， 所述动力透平涵道与所述 进气道连通， 在所述动力透平涵道内设动力透平外燃加热区， 所述动力透平设 置在所述动力透平外燃加热区后方的所述动力透平涵道内部，所述动力透平对 所述压气机输出动力， 所述喷气推进涵道与所述进气道连通， 在所述喷气推进 涵道内设喷气推进燃烧室， 所述喷气推进燃烧室与喷气推进喷管连通。 A parallel combustor jet engine includes a power turbine duct, a jet propulsion duct, an intake passage, a compressor, and a power turbine, the compressor being disposed in the intake passage, the power turbine duct Communicating with the intake passage, a power turbine external combustion heating zone is disposed in the power turbine duct, and the power turbine is disposed at the power turbine culvert behind the power turbine external combustion heating zone Inside the track, the power turbine outputs power to the compressor, the jet propulsion duct is in communication with the intake port, and a jet propulsion combustion chamber is disposed in the jet propulsion duct, the jet propulsion combustion chamber Connected to the jet propulsion nozzle.
所述动力透平涵道套装设置在所述喷气推进涵道内。
所述动力透平涵道与所述喷气推进涵道并列设置。 The power turbine duct set is disposed within the jet propulsion duct. The power turbine ducts are juxtaposed with the jet propulsion ducts.
一个所述动力透平涵道与两个或多个所述喷气推进涵道并列设置。 One of the power turbine ducts is juxtaposed with two or more of the jet propulsion ducts.
调整所述动力透平燃烧室内的空燃比使所述动力透平燃烧室内的空燃比 大于传统涡轮喷气发动机燃烧室内的空燃比和涡扇喷气发动机燃烧室内的空 燃比， 以实现所述动力透平在温度相对较低的环境中工作。 Adjusting an air-fuel ratio in the power turbine combustion chamber such that an air-fuel ratio in the power turbine combustion chamber is greater than an air-fuel ratio in a combustion chamber of a conventional turbojet engine and an air-fuel ratio in a combustion chamber of a turbofan engine to achieve the power turbine Work in a relatively low temperature environment.
所述动力透平的转速设为高于传统涡轮喷气发动机的动力透平的转速和 涡扇喷气发动机的动力透平的转速。 The rotational speed of the power turbine is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan jet engine.
所述动力透平的直径小于具有同等推进力的传统涡轮喷气发动机的动力 透平的直径和具有同等推进力的传统涡扇喷气发动机的动力透平的直径。 压力和涡扇发动机的压气机出口的压力。 The diameter of the power turbine is smaller than the diameter of a power turbine of a conventional turbojet engine having the same propulsion force and the diameter of a power turbine of a conventional turbofan jet engine having an equivalent propulsion force. Pressure and pressure at the compressor outlet of the turbofan engine.
在所述压气机的前方设风扇。 A fan is provided in front of the compressor.
本发明中，设有所述动力透平燃烧室和所述喷气推进燃烧室的方案的原理 是将由所述压气机和所述进气道产生的高压空气至少分成两部分，其中至少一 部分进入所述动力透平涵道， 其余进入所述喷气推进涵道， 进入所述动力透平 涵道的高压空气在所述动力透平燃烧室发生燃烧化学反应后推动所述动力透 平旋转， 所述动力透平推动所述压气机旋转， 对通过所述动力透平的工质没有 推进的要求，进入所述喷气推进涵道的高压空气在所述喷气推进燃烧室发生燃 烧化学反应后进入所述推进喷管产生推进力。 本发明中， 设有所述动力透平外 燃加热区和所述喷气推进燃烧室的方案的原理是将由所述压气机和所述进气 道产生的高压空气至少分成两部分， 其中至少一部分进入所述动力透平涵道， 其余进入所述喷气推进涵道，进入所述动力透平涵道的高压空气在所述动力透 平外燃加热区被加热后推动所述动力透平旋转，所述动力透平推动所述压气机 旋转， 对通过所述动力透平的工质没有推进的要求， 所述动力透平外燃加热区 的热源是通过所述喷气推进燃烧室的壁传入的热量，进入所述喷气推进涵道的 高压空气在所述喷气推进燃烧室发生燃烧化学反应后进入所述推进喷管产生 推进力。 In the present invention, the principle of providing the power turbine combustion chamber and the jet propulsion combustion chamber is to divide the high pressure air generated by the compressor and the intake passage into at least two parts, at least a part of which enters Deriving a power turbine duct, the remainder entering the jet propulsion duct, and the high pressure air entering the power turbine duct drives the power turbine to rotate after a combustion chemical reaction occurs in the power turbine combustor, The power turbine pushes the compressor to rotate, and the high pressure air entering the jet propulsion duct enters the combustion reaction reaction in the jet propulsion combustion chamber without the requirement of propulsion of the working fluid passing through the power turbine Propulsion nozzles generate propulsion. In the present invention, the principle of providing the power turbine external combustion heating zone and the jet propulsion combustion chamber is to divide the high pressure air generated by the compressor and the intake port into at least two parts, at least a part of which Entering the power turbine duct, the rest entering the jet propulsion duct, and the high pressure air entering the power turbine duct is driven to rotate the power turbine after being heated by the power turbine external combustion heating zone, The power turbine pushes the compressor to rotate, and there is no requirement for propulsion of the working fluid through the power turbine, and the heat source of the power turbine external combustion heating zone is introduced through the wall of the jet propulsion combustion chamber The heat, the high-pressure air entering the jet propulsion duct, enters the propulsion nozzle to generate propulsion after a combustion chemical reaction occurs in the jet propulsion combustion chamber.
在本发明的这两个方案中， 所述动力透平涵道的工质只有一个任务， 就是
尽可能利用工质本身的一切能量推动所述动力透平旋转，对所述压气机输出动 力， 不承担或很少成承担通过喷射获得反推力的任务， 这样就可以实现动力透 平的一部分叶轮在较高温度下工作， 另一部分叶轮在相对较低的温度下工作， 或者动力透平的所有叶轮均在较低温度下工作的目的， 从而降低发动机的成 本； 不仅如此， 由于所述动力透平工作温度的降低， 可以大幅度提高所述动力 透平的转速， 从而大幅度提高所述压气机的转速， 提高所述压气机的压比， 最 终达到提高发动机的效率的目的。 In the two solutions of the present invention, the working fluid of the power turbine duct has only one task, that is, As far as possible, all the energy of the working medium itself is used to drive the power turbine to rotate, and the compressor is outputted with power, and does not undertake or rarely undertake the task of obtaining the reverse thrust by the injection, so that a part of the impeller of the power turbine can be realized. Working at higher temperatures, another part of the impeller operates at a relatively lower temperature, or all of the impellers of the power turbine operate at lower temperatures, thereby reducing the cost of the engine; The reduction of the flat working temperature can greatly increase the rotational speed of the power turbine, thereby greatly increasing the rotational speed of the compressor, increasing the pressure ratio of the compressor, and finally achieving the purpose of improving the efficiency of the engine.
本发明中由于通过所述动力透平涵道的工质，也就是通过所述动力透平的 工质不承担或很少承担通过喷射获得反推力的任务，所以所述动力透平涵道的 通量可以大幅度降低， 为此， 所述动力透平的叶轮直径也可以大幅度降低， 由 于所述动力透平叶轮直径的降低， 叶轮所需要承担的离心力也会大幅度降低， 所以， 可以提高所述动力透平的转速， 实现所述压气机转速的提高， 达到更高 压比， 最终提高发动机的效率。 In the present invention, the working fluid passing through the duct of the power turbine, that is, the working fluid passing through the power turbine does not bear or seldom undertake the task of obtaining the reverse thrust by the injection, so the dynamic turbine duct The flux can be greatly reduced. For this reason, the impeller diameter of the power turbine can also be greatly reduced. Due to the reduction of the diameter of the power turbine impeller, the centrifugal force required by the impeller can be greatly reduced, so Increasing the rotational speed of the power turbine, achieving the increase in the rotational speed of the compressor, achieving a higher pressure ratio, and ultimately improving the efficiency of the engine.
本发明所谓 "所述动力透平对所述压气 输出动力"是指所述动力透平推 动所述压气机旋转， 包括同轴设置， 也包括经过齿轮等的等速或变速结构的推 动作用； 所谓的动力透平燃烧室是指设置在所述动力透平涵道内的燃烧室， 其 作用是产生推动所述动力透平的工质； 所谓喷气推进燃烧室是指设置在所述喷 气推进涵道内的的燃烧室， 其作用是产生进入所述推进喷管的工质， 通过所述 推进喷管产生推进力； 所谓的动力透平外燃加热区是指所述动力透平涵道壁的 一部分， 其作用是对所述动力透平涵道内的高压空气进行加热， 其热源可以是 自所述喷气推进燃烧室壁传来的热量， 也可以是其他热源。 The so-called "the power turbine to the compressor output power" means that the power turbine pushes the compressor to rotate, including a coaxial arrangement, and also includes a pushing action of a constant speed or a shifting structure via a gear or the like; The so-called power turbine combustion chamber refers to a combustion chamber disposed in the duct of the power turbine, and functions to generate a working fluid for pushing the power turbine; the so-called jet propulsion combustion chamber is disposed at the jet propulsion culvert a combustion chamber in the passage, the function of which is to generate a working fluid entering the propulsion nozzle, and the propulsion force is generated by the propulsion nozzle; the so-called power turbine external combustion heating zone refers to the wall of the dynamic turbine duct In one part, the function is to heat the high-pressure air in the duct of the power turbine, and the heat source may be heat from the jet propulsion combustion chamber wall, or may be other heat sources.
本发明中，根据公知技术，可在本发明所公开的并联燃烧室喷气发动机中， 设置一切必要的部件、 单元或系统。 In the present invention, all necessary components, units or systems can be provided in the parallel combustor jet engine disclosed in the present invention in accordance with known techniques.
本发明的有益效果如下： The beneficial effects of the present invention are as follows:
本发明实现了涡轮喷气发动机的高效、 低排放和低造价。 The invention achieves high efficiency, low emissions and low cost of the turbojet engine.
附图说明 DRAWINGS
图 1为本发明实施例 1的结构示意图； 1 is a schematic structural view of Embodiment 1 of the present invention;
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； 2 is a schematic structural view of Embodiment 2 of the present invention; 3 is a schematic structural view of Embodiment 3 of the present invention;
图 4为本发明实施例 4的结构示意图； 4 is a schematic structural view of Embodiment 4 of the present invention;
图 5为本发明实施例 5的结构示意图； Figure 5 is a schematic structural view of Embodiment 5 of the present invention;
图 6为本发明实施例 6的结构示意图； Figure 6 is a schematic structural view of Embodiment 6 of the present invention;
图 7为本发明实施例 7的结构示意图； Figure 7 is a schematic structural view of Embodiment 7 of the present invention;
图 8为本发明实施例 8的结构示意图； Figure 8 is a schematic structural view of Embodiment 8 of the present invention;
图 9为本发明实施例 9的结构示意图。 Figure 9 is a schematic view showing the structure of Embodiment 9 of the present invention.
具体实施方式 detailed description
实施例 1 Example 1
如图 1所示的并联燃烧室喷气发动机， 包括动力透平涵道 1、 喷气推进涵 道 2、 进气道 3、 压气机 4和动力透平 5， 所述压气机 4设在所述进气道 3内， 所述动力透平涵道 1与所述进气道 3连通，在所述动力透平涵道 1内设动力透 平燃烧室 6， 所述动力透平 5设置在所述动力透平燃烧室 6后方的所述动力透 平涵道 1内部， 所述动力透平 5对所述压气机 4输出动力， 所述喷气推进涵道 2与所述进气道 3连通， 在所述喷气推进涵道 2内设喷气推进燃烧室 7， 所述 喷气推进燃烧室 7与喷气推进喷管 8连通，所述动力透平涵道 1套装设置在所 述喷气推进涵道 2内； 调整所述动力透平燃烧室 6内的空燃比使所述动力透平 燃烧室 6内的空燃比大于传统涡轮喷气发动机燃烧室内的空燃比和涡扇喷气发 动机燃烧室内的空燃比，以实现所述动力透平 5在温度相对较低的环境中工作。 所述动力透平 5的转速设为高于传统涡轮喷气发动机的动力透平的转速和涡扇 喷气发动机的动力透平的转速，所述动力透平 5的直径小于具有同等推进力的 传统涡轮喷气发动机的动力透平的直径和具有同等推进力的传统涡扇喷气发 动机的动力透平的直径，所述压气机 4的输出气体的压力大于传统涡轮喷气发 动机的压气机出口的压力和涡扇发动机的压气机出口的压力。 The parallel combustor jet engine shown in FIG. 1 includes a power turbine duct 1, a jet propulsion duct 2, an intake port 3, a compressor 4, and a power turbine 5, and the compressor 4 is disposed in the inlet In the air passage 3, the power turbine duct 1 is in communication with the air inlet 3, and a power turbine combustion chamber 6 is disposed in the power turbine duct 1, and the power turbine 5 is disposed in the Inside the power turbine duct 1 behind the power turbine combustion chamber 6, the power turbine 5 outputs power to the compressor 4, and the jet propulsion duct 2 communicates with the air inlet 3, a jet propulsion combustion chamber 7 is disposed in the jet propulsion duct 2, the jet propulsion combustion chamber 7 is in communication with the jet propulsion nozzle 8, and the power turbine duct 1 is set in the jet propulsion duct 2; Adjusting an air-fuel ratio in the power turbine combustion chamber 6 such that an air-fuel ratio in the power turbine combustion chamber 6 is greater than an air-fuel ratio in a combustion chamber of a conventional turbojet engine and an air-fuel ratio in a combustion chamber of a turbofan engine to achieve Power turbine 5 in a relatively low temperature environment jobs. The rotational speed of the power turbine 5 is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan engine, the diameter of the power turbine 5 being smaller than the conventional turbine having the same propulsion force The diameter of the power turbine of the jet engine and the diameter of the power turbine of a conventional turbofan engine having the same propulsion, the pressure of the output gas of the compressor 4 being greater than the pressure and turbofan of the compressor outlet of the conventional turbojet engine The pressure at the compressor outlet of the engine.
实施例 2 Example 2
如图 2所示的并联燃烧室喷气发动机， 包括动力透平涵道 1、 喷气推进涵 道 2、 进气道 3、 压气机 4和动力透平 5， 所述压气机 4设在所述进气道 3内， 所述动力透平涵道 1与所述进气道 3连通，在所述动力透平涵道 1内设动力透
平外燃加热区 60， 所述动力透平 5设置在所述动力透平外燃加热区 60后方的 所述动力透平涵道 1内部， 所述动力透平 5对所述压气机 4输出动力， 所述喷 气推进涵道 2与所述进气道 3连通，在所述喷气推进涵道 1内设喷气推进燃烧 室 7， 所述喷气推进燃烧室 7与喷气推进喷管 8连通， 所述动力透平涵道 1套 装设置在所述喷气推进涵道 2内。所述动力透平 5的转速设为高于传统涡轮喷 气发动机的动力透平的转速和涡扇喷气发动机的动力透平的转速，所述动力透 平 5的直径小于具有同等推进力的传统涡轮喷气发动机的动力透平的直径和具 有同等推进力的传统涡扇喷气发动机的动力透平的直径，所述压气机 4的输出 气体的压力大于传统涡轮喷气发动机的压气机出口的压力和涡扇发动机的压 气机出口的压力。 The parallel combustor jet engine shown in FIG. 2 includes a power turbine duct 1, a jet propulsion duct 2, an intake port 3, a compressor 4, and a power turbine 5, and the compressor 4 is disposed in the inlet In the air passage 3, the power turbine duct 1 is in communication with the air inlet 3, and a power transmission is provided in the power turbine duct 1 a flat external combustion heating zone 60, the power turbine 5 is disposed inside the power turbine duct 1 behind the power turbine external combustion heating zone 60, and the power turbine 5 outputs the compressor 4 Power, the jet propulsion duct 2 is in communication with the intake passage 3, and a jet propulsion combustion chamber 7 is disposed in the jet propulsion duct 1 and the jet propulsion combustion chamber 7 is in communication with the jet propulsion nozzle 8 The set of power turbine ducts 1 is disposed within the jet propulsion duct 2 . The rotational speed of the power turbine 5 is set to be higher than the rotational speed of the power turbine of the conventional turbojet engine and the rotational speed of the power turbine of the turbofan engine, the diameter of the power turbine 5 being smaller than the conventional turbine having the same propulsion force The diameter of the power turbine of the jet engine and the diameter of the power turbine of a conventional turbofan engine having the same propulsion, the pressure of the output gas of the compressor 4 being greater than the pressure and turbofan of the compressor outlet of the conventional turbojet engine The pressure at the compressor outlet of the engine.
实施例 3 Example 3
如图 3所示的并联燃烧室喷气发动机， 其与实施例 2的区别在于： 所述动 力透平涵道 1延伸至所述喷气推进喷管 8的后方，所述压气机 4和所述动力透 平 5同轴设置。 A parallel combustor jet engine as shown in FIG. 3 differs from the embodiment 2 in that: the power turbine duct 1 extends to the rear of the jet propulsion nozzle 8, the compressor 4 and the power Turbo 5 coaxial setting.
实施例 4 Example 4
如图 4所示的并联燃烧室喷气发动机， 其与实施例 1的区别在于： 在所述 压气机 4的前方设风扇 330。 The parallel combustor jet engine shown in Fig. 4 differs from the first embodiment in that a fan 330 is provided in front of the compressor 4.
实施例 5 Example 5
如图 5所示的并联燃烧室喷气发动机， 其与实施例 4的区别在于： 在所述 风扇 330外设风扇涵道 333。 The parallel combustor jet engine shown in Fig. 5 differs from the embodiment 4 in that a fan duct 333 is provided at the fan 330.
实施例 6 Example 6
如图 6所示的并联燃烧室喷气发动机， 其与实施例 1的区别在于： 所述并 联燃烧室喷气发动机还包括启动装置 10， 所述启动装置 10对所述压气机 4输 出动力。 The parallel combustor jet engine shown in Fig. 6 differs from the first embodiment in that the parallel combustor jet engine further includes a starting device 10 that outputs power to the compressor 4.
实施例 7 Example 7
如图 7所示的并联燃烧室喷气发动机， 其与实施例 2的区别在于： 在所述 压气机 4的前方设风扇 330构成所述喷气推进燃烧室 7与所述动力透平外燃加 热区 60并联的涡轮风扇发动机。
如图 8所示的并联燃烧室喷气发动机， 其与实施例 1的区别在于： 所述动 力透平涵道 1与所述喷气推进涵道 2并列设置。 The parallel combustor jet engine shown in FIG. 7 differs from the second embodiment in that a fan 330 is disposed in front of the compressor 4 to constitute the jet propulsion combustion chamber 7 and the power turbine external combustion heating zone. 60 parallel turbofan engines. The parallel combustor jet engine shown in Fig. 8 differs from the first embodiment in that the power turbine duct 1 is juxtaposed with the jet propulsion duct 2.
实施例 9 Example 9
如图 9所示的并联燃烧室喷气发动机， 其与实施例 1的区别在于： 一个所 述动力透平涵道 1与两个所述喷气推进涵道 2并列设置。 The parallel combustor jet engine shown in Fig. 9 differs from the first embodiment in that one of the power turbine ducts 1 is juxtaposed with two of the jet propulsion ducts 2.
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。
It is apparent that the present invention is not limited to the above embodiment, and many variations are possible. All modifications that can be directly derived or associated from the disclosure of the present invention are considered to be within the scope of the present invention.
Claims
权 利 要 求 Rights request
一种并联燃烧室喷气发动机， 包括动力透平涵道 （1 )、 喷气推进涵道 (2)、 进气道 （3)、 压气机 （4) 和动力透平 （5)， 其特征在于： 所述压气机 (4) 设在所述进气道 （3) 内， 所述动力透平涵道 （1 ) 与所述进气道 （3) 连 通， 在所述动力透平涵道 （1 ) 内设动力透平燃烧室 （6)， 所述动力透平 （5) 设置在所述动力透平燃烧室 （6)后方的所述动力透平涵道（1 ) 内部， 所述动 力透平 （5) 对所述压气机 （4) 输出动力， 所述喷气推进涵道 （2) 与所述进 气道 （3) 连通， 在所述喷气推进涵道（2) 内设喷气推进燃烧室 （7)， 所述喷 气推进燃烧室 （7) 与喷气推进喷管 （8) 连通。 A parallel combustor jet engine includes a power turbine duct (1), a jet propulsion duct (2), an air intake (3), a compressor (4), and a power turbine (5), characterized by: The compressor (4) is disposed in the intake passage (3), and the power turbine duct (1) is in communication with the intake passage (3), and the dynamic turbine duct (1) a power turbine combustion chamber (6) is disposed, the power turbine (5) is disposed inside the power turbine duct (1) behind the power turbine combustion chamber (6), and the power is transmitted through Level (5) outputting power to the compressor (4), the jet propulsion duct (2) is in communication with the intake port (3), and jet propulsion combustion is arranged in the jet propulsion duct (2) The chamber (7), the jet propulsion combustion chamber (7) is in communication with the jet propulsion nozzle (8).
2、 一种并联燃烧室喷气发动机， 包括动力透平涵道 （1 )、 喷气推进涵道 (2)、 进气道 （3)、 压气机 （4) 和动力透平 （5)， 其特征在于： 所述压气机 2. A parallel combustor jet engine comprising a power turbine duct (1), a jet propulsion duct (2), an air inlet (3), a compressor (4) and a power turbine (5), characterized In: the compressor
(4)设在所述进气道（3) 内， 所述动力透平涵道 （1 ) 与所述进气道 （3) 连 通， 在所述动力透平涵道（1 ) 内设动力透平外燃加热区 （60)， 所述动力透平(4) disposed in the intake passage (3), the power turbine duct (1) is in communication with the intake passage (3), and is powered in the power turbine duct (1) Turbine external combustion heating zone (60), said power turbine
(5) 设置在所述动力透平外燃加热区 （60) 后方的所述动力透平涵道（1 ) 内 部， 所述动力透平 （5) 对所述压气机 （4) 输出动力， 所述喷气推进涵道（2) 与所述进气道（3)连通， 在所述喷气推进涵道（2) 内设喷气推进燃烧室（7)， 所述喷气推进燃烧室 （7) 与喷气推进喷管 （8) 连通。 (5) disposed inside the power turbine duct (1) behind the power turbine external combustion heating zone (60), the power turbine (5) outputting power to the compressor (4), The jet propulsion duct (2) is in communication with the intake passage (3), and a jet propulsion combustion chamber (7) is disposed in the jet propulsion duct (2), and the jet propulsion combustion chamber (7) is The jet propulsion nozzle (8) is connected.
3、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 所述动 力透平涵道 （1 ) 套装设置在所述喷气推进涵道 （2) 内。 3. A parallel combustor jet engine according to claim 1 or 2, characterized in that said power turbine duct (1) is arranged in said jet propulsion duct (2).
4、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 所述动 力透平涵道 （1 ) 与所述喷气推进涵道 （2) 并列设置。 A parallel combustor jet engine according to claim 1 or 2, characterized in that said power turbine duct (1) is juxtaposed with said jet propulsion duct (2).
5、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 一个所 述动力透平涵道 （1 ) 与两个或多个所述喷气推进涵道 （2) 并列设置。 A parallel combustor jet engine according to claim 1 or 2, characterized in that: one of said power turbine ducts (1) is juxtaposed with two or more of said jet propulsion ducts (2).
6、 如权利要求 1 所述并联燃烧室喷气发动机， 其特征在于： 调整所述动 力透平燃烧室 （6) 内的空燃比使所述动力透平燃烧室 （6) 内的空燃比大于传 统涡轮喷气发动机燃烧室内的空燃比和涡扇喷气发动机燃烧室内的空燃比， 以 实现所述动力透平 （5) 在温度相对较低的环境中工作。 6. The parallel combustor jet engine of claim 1 wherein: adjusting an air-fuel ratio in said power turbine combustor (6) such that an air-fuel ratio in said power turbine combustor (6) is greater than conventional The air-fuel ratio in the combustion chamber of the turbojet engine and the air-fuel ratio in the combustion chamber of the turbofan engine to achieve operation of the power turbine (5) in a relatively low temperature environment.
7、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 所述动 力透平 （5 ) 的转速设为高于传统涡轮喷气发动机的动力透平的转速和涡扇喷 气发动机的动力透平的转速。 7. The parallel combustor jet engine of claim 1 or 2, wherein: The speed of the force turbine (5) is set to be higher than the speed of the power turbine of the conventional turbojet engine and the speed of the power turbine of the turbofan jet engine.
8、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于: '所述动 力透平 （5) 的直径小于具有同等推进力的传统涡轮喷气发动机的动力透平的 直径和具有同等推进力的传统涡扇喷气发动机的动力透平的直径。 8. A parallel combustor jet engine according to claim 1 or 2, wherein: 'the power turbine (5) has a diameter smaller than that of a conventional turbojet engine having the same propulsion and has the same diameter The diameter of the power turbine of a conventional turbofan jet engine.
9、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 所述压 涡扇发动机的压气机出口的压力。 9. A parallel combustor jet engine according to claim 1 or 2, wherein: the pressure of the compressor outlet of the turbofan engine.
10、 如权利要求 1或 2所述并联燃烧室喷气发动机， 其特征在于： 在所述 压气机 （4) 的前方设风扇 （330)。 The parallel combustor jet engine according to claim 1 or 2, characterized in that a fan (330) is provided in front of the compressor (4).
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| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN104018952A (en) * | 2014-03-22 | 2014-09-03 | 张鑫宇 | Aircraft engine |
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- 2011-02-25 CN CN 201120047791 patent/CN202055935U/en not_active Expired - Fee Related
- 2011-02-25 CN CN2011100458073A patent/CN102128101A/en active Pending
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| US4813229A (en) * | 1985-03-04 | 1989-03-21 | General Electric Company | Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas |
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| CN201818391U (en) * | 2010-10-19 | 2011-05-04 | 靳北彪 | Duct-suited turbojet engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102128101A (en) | 2011-07-20 |
| CN101975121A (en) | 2011-02-16 |
| CN202055935U (en) | 2011-11-30 |
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