WO2012051783A1 - Moteur à réaction pourvu de chambres de combustion parallèles - Google Patents

Moteur à réaction pourvu de chambres de combustion parallèles Download PDF

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Publication number
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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WO
WIPO (PCT)
Prior art keywords
power turbine
duct
jet
jet propulsion
compressor
Prior art date
Application number
PCT/CN2011/000300
Other languages
English (en)
Chinese (zh)
Inventor
靳北彪
Original Assignee
Jin Beibiao
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jin Beibiao filed Critical Jin Beibiao
Publication of WO2012051783A1 publication Critical patent/WO2012051783A1/fr

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Classifications

    • 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
    • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention se rapporte à un moteur à réaction pourvu de chambres de combustion parallèles, qui comprend un conduit (1) de turbine de travail, un conduit (2) de propulsion à réaction, un conduit d'admission (3), un compresseur d'air (4) et une turbine de travail (5). Le compresseur d'air (4) est agencé dans le conduit d'admission (3), et le conduit (1) de turbine de travail communique avec le conduit d'admission (3). Une chambre de combustion (6) de turbine de travail est disposée dans le conduit (1) de turbine de travail. La turbine de travail (5) est agencée dans le conduit (1) de turbine de travail derrière la chambre de combustion (6) de turbine de travail. La turbine de travail (5) sort de la puissance vers le compresseur d'air (4). Le conduit (2) de propulsion à réaction communique avec le conduit d'admission (3). Dans le conduit (2) de propulsion à réaction se trouve une chambre de combustion (7) de propulsion à réaction qui communique avec une buse (8) de propulsion à réaction. Le moteur permet d'obtenir une efficacité élevée, une émission d'agents polluants faible et un coût réduit.
PCT/CN2011/000300 2010-10-19 2011-02-25 Moteur à réaction pourvu de chambres de combustion parallèles WO2012051783A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN 201010511506 CN101975121A (zh) 2010-10-19 2010-10-19 涵道套装涡轮喷气发动机
CN201010511506.0 2010-10-19

Publications (1)

Publication Number Publication Date
WO2012051783A1 true WO2012051783A1 (fr) 2012-04-26

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PCT/CN2011/000300 WO2012051783A1 (fr) 2010-10-19 2011-02-25 Moteur à réaction pourvu de chambres de combustion parallèles

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CN (3) CN101975121A (fr)
WO (1) WO2012051783A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
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CN101975121A (zh) * 2010-10-19 2011-02-16 靳北彪 涵道套装涡轮喷气发动机
CN104018952A (zh) * 2014-03-22 2014-09-03 张鑫宇 一种飞机发动机
CN106677901A (zh) * 2015-11-10 2017-05-17 熵零股份有限公司 一种航空发动机
CN105697148B (zh) * 2016-04-11 2018-04-10 清华大学 涡轮发动机
CN108087149B (zh) * 2016-11-22 2020-05-19 江西洪都航空工业集团有限责任公司 一种高推重比低油耗的涡喷发动机
CN108252935A (zh) * 2016-12-29 2018-07-06 上海鼓风机厂有限公司 多级涵道式轴流压缩机
CN110486171A (zh) * 2017-08-29 2019-11-22 熵零技术逻辑工程院集团股份有限公司 一种轴传动外喷射式发动机冷却系统
CN109538376B (zh) * 2018-11-07 2021-01-26 中国航发湖南动力机械研究所 飞行器及其发动机
CN110985207A (zh) * 2019-12-30 2020-04-10 绵阳小巨人动力设备有限公司 一种微型双燃室变循环涡喷发动机
CN111779592A (zh) * 2020-06-01 2020-10-16 北京航空航天大学 一种引入并联燃烧室的混合排气涡扇发动机推进系统
CN111636976B (zh) * 2020-06-08 2021-10-19 清华大学 一种三涵道大推重比高效动力推进器
CN112945306B (zh) * 2021-02-05 2022-06-07 中国航发沈阳发动机研究所 一种同时测量双涵道喷管推力及流量的试验平台
CN114790955A (zh) * 2022-05-06 2022-07-26 哈尔滨工业大学 一种可以实现油电增程的混合动力发动机

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US4335573A (en) * 1970-09-02 1982-06-22 General Electric Company Gas turbine engine mixer
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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CN101975121A (zh) * 2010-10-19 2011-02-16 靳北彪 涵道套装涡轮喷气发动机
CN201818391U (zh) * 2010-10-19 2011-05-04 靳北彪 涵道套装涡轮喷气发动机

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US7770381B2 (en) * 2006-12-18 2010-08-10 General Electric Company Duct burning mixed flow turbofan and method of operation

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296800A (en) * 1967-01-10 Gas turbine power plant
US4335573A (en) * 1970-09-02 1982-06-22 General Electric Company Gas turbine engine mixer
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
CN1046958A (zh) * 1989-04-26 1990-11-14 通用电气公司 减小加力燃气涡轮发动机压差载荷的装置和方法
CN101975121A (zh) * 2010-10-19 2011-02-16 靳北彪 涵道套装涡轮喷气发动机
CN201818391U (zh) * 2010-10-19 2011-05-04 靳北彪 涵道套装涡轮喷气发动机

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CN102128101A (zh) 2011-07-20
CN101975121A (zh) 2011-02-16
CN202055935U (zh) 2011-11-30

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