WO2019127936A1 - Structure de buse, dispositif de jet et moteur - Google Patents

Structure de buse, dispositif de jet et moteur Download PDF

Info

Publication number
WO2019127936A1
WO2019127936A1 PCT/CN2018/079768 CN2018079768W WO2019127936A1 WO 2019127936 A1 WO2019127936 A1 WO 2019127936A1 CN 2018079768 W CN2018079768 W CN 2018079768W WO 2019127936 A1 WO2019127936 A1 WO 2019127936A1
Authority
WO
WIPO (PCT)
Prior art keywords
liquid
nozzle structure
flow path
nozzle
port
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2018/079768
Other languages
English (en)
Chinese (zh)
Inventor
刘若鹏
栾琳
李娜
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenzhen Kuang Chi Space Technology Co Ltd
Original Assignee
Shenzhen Kuang Chi Space Technology Co Ltd
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 Shenzhen Kuang Chi Space Technology Co Ltd filed Critical Shenzhen Kuang Chi Space Technology Co Ltd
Publication of WO2019127936A1 publication Critical patent/WO2019127936A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors

Definitions

  • the utility model relates to the technical field of rocket engines, in particular to a nozzle structure, an injection device and an engine.
  • Liquid rocket engines are usually provided with an injection device for jetting and igniting two components (liquid fuel and gas oxidant), and the atomizing injection effect of the injection device on the liquid fuel determines the combustion efficiency of the liquid fuel, and also directly It is about the performance of liquid rocket engines.
  • the injection device of the existing liquid rocket engine has a poor atomization effect on the liquid fuel, thereby causing insufficient combustion of the liquid fuel, thereby affecting the working performance of the liquid rocket engine, so that the liquid rocket engine cannot meet different injection conditions, Rocket propulsion performance.
  • the main object of the present invention is to provide a nozzle structure, an injection device and an engine to solve the problem that the atomization effect of the injection device in the prior art on the liquid fuel is poor, thereby causing insufficient combustion of the liquid fuel and affecting the liquid rocket. Problems with the performance of the engine.
  • a nozzle structure comprising: a nozzle body having a liquid flow passage, a first end of the liquid flow passage being a liquid inlet port, and a second liquid flow passage The end is a liquid injection port; the vortex device is arranged in the liquid flow channel and located at the liquid injection port; the nozzle body further has an air flow channel, the first end of the air flow channel is an air inlet port, and the second end of the air flow channel is a gas
  • the injection port is disposed at a distance from the liquid injection port to shear the cone-shaped atomized liquid fuel ejected from the liquid injection port.
  • the liquid flow path includes a liquid flow path section, a necking flow path section and a jet flow path section which are sequentially connected, wherein the cross-sectional area of the constricted flow path section gradually decreases in a direction away from the liquid flow path section,
  • the cross-sectional area of the jet flow path section is smaller than the cross-sectional area of the liquid flow path section, and the swirler is disposed in the liquid flow path section, the necked flow path section forms a swirl chamber, and the jet flow path section has a liquid ejection port.
  • the nozzle body has a cylindrical shape
  • the cylindrical nozzle body includes a first barrel and a second barrel that are connected to each other, wherein the liquid flow passage penetrates the first barrel and the second barrel along the axial direction of the nozzle body
  • the connection between the first cylinder and the second cylinder forms a stepped structure, and the air inlet port of the air flow passage is opened on the step surface of the step structure, and the air flow passage extends in the second cylinder body.
  • the air flow channels are plural, and the plurality of air flow channels are disposed around the outer circumference of the liquid flow channel.
  • a swirling groove is formed on the swirler, and a swirling passage is formed between the guiding groove and the inner wall surface of the nozzle body.
  • the swirl channel extends in a spiral shape.
  • an injection device comprising: a casing having a liquid collecting chamber and a collecting chamber spaced apart from each other, wherein the housing is further provided with a liquid inlet hole and an air inlet hole, wherein the liquid inlet The hole communicates with the liquid collecting chamber, the air inlet hole communicates with the air collecting chamber; the nozzle structure, the nozzle structure is disposed in the outer casing, and the liquid inlet port of the nozzle structure communicates with the liquid collecting chamber, and the air inlet port of the nozzle structure is connected with the air collecting chamber
  • the nozzle structure is the above nozzle structure.
  • the nozzle structure is plural, and the plurality of nozzle structures are spaced apart around the axis of the outer casing.
  • the spraying device further includes a hydraulic detecting portion and a gas pressure detecting portion, and the liquid pressure measuring hole and the gas pressure measuring hole are further disposed on the outer casing, and the hydraulic detecting portion is disposed at the liquid pressure measuring hole to detect the pressure in the liquid collecting chamber, The air pressure detecting portion is disposed at the gas pressure measuring hole to detect the pressure in the air collecting chamber.
  • an engine including an engine body and an injection device disposed on the engine body, the injection device being the above-described injection device.
  • the liquid fuel moves in the liquid flow channel and is atomized by the centrifugal force of the vortex device and is ejected by the liquid injection port, and the liquid fuel injected is in a cone shape.
  • the gas oxidant moves in the gas flow passage and is ejected by the gas injection port. Since the gas injection port is spaced apart from the liquid injection port, the gas oxidant ejected from the gas injection port can be sprayed toward the liquid ejection port.
  • the atomized liquid fuel produces a shearing effect, achieves the effect of secondary atomization, and the effect of double atomization of the liquid fuel ensures the mixing effect of the liquid fuel and the gas combustion improver, thereby improving the combustion efficiency of the liquid fuel, thereby Improves engine performance, allowing the engine to adapt to different injection conditions.
  • Figure 1 shows a schematic front view of an injection device in accordance with an alternative embodiment of the present invention
  • Figure 2 shows a bottom view of the injection device of Figure 1;
  • Figure 3 is a schematic view showing the internal structure of the injection device of Figure 1;
  • FIG. 4 shows a front schematic view of a nozzle structure in accordance with an alternative embodiment of the present invention
  • Figure 5 is a top plan view showing the nozzle structure of Figure 4.
  • Figure 6 is a front elevational cross-sectional view taken along line A-A of Figure 5;
  • Fig. 7 is a front cross-sectional view showing the line B-B in Fig. 5.
  • the utility model provides a nozzle structure and injection.
  • the engine includes an engine body and an injection device disposed on the engine body, the injection device being the above-described and below-described injection device, as shown in FIGS. 1 to 3, the injection device including the outer casing 1 and the nozzle structure 2,
  • the outer casing 1 has a liquid collecting chamber 110 and a gas collecting chamber 120.
  • the outer casing 1 is further provided with a liquid inlet hole 130 and an air inlet hole 140.
  • the liquid inlet hole 130 communicates with the liquid collecting chamber 110, and the air inlet hole 140
  • the air collection chamber 120 is in communication
  • the nozzle structure 2 is disposed in the outer casing 1
  • the liquid inlet port 12 of the nozzle structure 2 is in communication with the liquid collection chamber 110.
  • the air inlet port 15 of the nozzle structure 2 is in communication with the air collection chamber 120.
  • the nozzle structure 2 is The nozzle structure described above and below.
  • the engine of the present application is preferably a rocket engine
  • the injection device uses the nozzle structure 2 to inject liquid fuel and gas oxidant into the engine body, wherein the liquid fuel is stored in the sump 110 in a short term and is configured by the nozzle structure 2
  • the gas oxidizer is discharged in a short-term concentration and stored in the plenum 120 and ejected by the nozzle structure 2, and the gas oxidant is preferably oxygen.
  • the nozzle structure includes a nozzle body 10 and a swirler 20, wherein the nozzle body 10 has a liquid flow path 11, and the first end of the liquid flow path 11 is a liquid inlet port 12, and the liquid flow channel 11
  • the second end is a liquid ejection port 13
  • the swirler 20 is disposed in the liquid flow channel 11 and located at the liquid ejection port 13 .
  • the nozzle body 10 further has an air flow channel 14 , and the first end of the air flow channel 14 is an air inlet port 15 .
  • the second end of the air flow passage 14 is a gas injection port 16, and the gas injection port 16 is spaced apart from the liquid injection port 13 to cause shearing of the cone-shaped atomized liquid fuel ejected from the liquid ejection port 13.
  • the liquid fuel moves in the liquid flow path 11 and is atomized by the centrifugal force of the vortex device 20 and is ejected by the liquid ejecting port 13, and the ejected liquid fuel has a conical mist shape, and the gas ignites.
  • the agent moves within the gas flow passage 14 and is ejected by the gas injection port 16, and the gas injection port 16 is disposed at a distance from the liquid injection port 13, so that the gas oxidant ejected from the gas injection port 16 can be ejected to the liquid ejection port 13.
  • the cone-shaped atomized liquid fuel produces a shearing effect, achieving the effect of secondary atomization, and the effect of double atomization of the liquid fuel ensures the mixing effect of the liquid fuel and the gas combustion improver, and improves the liquid fuel.
  • the combustion efficiency which improves the performance of the engine, allows the engine to adapt to different injection conditions.
  • the liquid flow path 11 includes a liquid flow path section 111, a necking flow path section 112, and a jet flow path section 113 which are sequentially connected, wherein the cross-sectional area of the constricted flow path section 112 is away from the liquid flow.
  • the direction of the track section 111 gradually decreases, the cross-sectional area of the jet flow path section 113 is smaller than the cross-sectional area of the liquid flow path section 111, and the swirler 20 is disposed in the liquid flow path section 111, and the constricted flow path section 112 forms a spiral.
  • the flow chamber, the jet flow path section 113 has a liquid ejection port 13.
  • the liquid fuel leaves the nozzle structure 2 in a column shape, and then, the liquid flow path 11 of the nozzle structure 2 generates a lower pressure to make the liquid fuel
  • the generation of a certain axial velocity causes the liquid fuel to move downstream, and at the same time, due to the presence of the swirler 20 in the liquid flow path section 111, the liquid fuel is subjected to centrifugal force, so that the liquid fuel is ejected from the constricted flow path section 112.
  • the rotation speed When there is a certain rotation speed, the rotation speed is converted into the radial speed and the tangential speed of the constricted flow path section 112 in a short time, so the liquid fuel rapidly increases in size in the radial direction, so that the liquid fuel is tapered.
  • the shape gradually expands; however, this trend does not develop unrestrictedly because the surface tension of the liquid fuel increases as the tapered profile of the liquid fuel expands, and the surface of the liquid fuel in the shape of a cone
  • the radius of curvature decreases, which together determine the injection pattern of the liquid fuel, so when the liquid fuel develops to a certain peak in the radial direction, it is subjected to its surface.
  • the influence of the force begins to shrink, and at the same time, the degree of rotation of the liquid fuel begins to increase, but this reduced form does not develop unrestricted because the liquid fuel shrinks to near the necked flow path section 112.
  • the neck-shaped flow path section 112 will periodically move along the axis in a figure-eight shape.
  • the pressure in the liquid flow path 11 is further increased, the liquid fuel is still scattered radially in a hollow state, but the previous phenomenon no longer occurs.
  • the nozzle body 10 has a cylindrical shape, and the cylindrical nozzle body 10 includes a first cylindrical body 17 and a second cylindrical body 18 connected thereto, wherein the liquid flow channel 11 is along the nozzle body 10 .
  • the first cylindrical body 17 and the second cylindrical body 18 are axially penetrated, and the joint between the first cylindrical body 17 and the second cylindrical body 18 forms a stepped structure, and the air inlet port 15 of the air flow passage 14 is opened on the step surface 19 of the stepped structure.
  • the air flow passage 14 extends within the second cylinder 18.
  • the airflow passage 14 extends in a curve or includes a plurality of linear flow passage segments that are in communication.
  • the air flow passages 14 are plural, and the plurality of air flow passages 14 are spaced around the outer circumference of the liquid flow passage 11. Settings. Thus, it is ensured that the plurality of gas injection ports 16 of the plurality of gas flow passages 14 are disposed around the outer circumference of the liquid ejection port 13.
  • the air flow passages 14 are four, and the four air flow passages 14 are equally spaced around the outer circumference of the liquid flow passage 11.
  • the swirler 20 is provided with a flow guiding groove 21, and a swirling passage is formed between the flow guiding groove 21 and the inner wall surface of the nozzle body 10.
  • the swirl channel extends helically. This ensures that the swirler 20 acts as a swirling effect on the liquid fuel.
  • the nozzle structure 2 in order to improve the working performance of the engine and increase the power output of the engine, the nozzle structure 2 is plural, and the plurality of nozzle structures 2 are spaced apart around the axis of the casing 1.
  • the nozzle structure 2 is three, and the three nozzle structures 2 are equally spaced around the axis of the outer casing 1.
  • the injection device further includes a hydraulic pressure detecting portion and a gas pressure detecting portion.
  • the outer casing 1 is further provided with a liquid pressure measuring hole 150 and a gas pressure measuring hole 160.
  • the hydraulic pressure detecting portion is disposed at the liquid pressure measuring hole 150 to detect The pressure in the liquid collection chamber 110 is provided at the gas pressure measuring hole 160 to detect the pressure in the gas collection chamber 120.
  • orientation words such as “front, back, up, down, left, right", “horizontal, vertical, vertical, horizontal” and “top, bottom”, etc. are indicated.
  • Azimuth or positional relationship is generally based on the orientation or positional relationship shown in the drawings, and is merely for the convenience of the description of the present invention and the simplified description, which are not intended to indicate or imply the indicated device.
  • the components must have a specific orientation or be constructed and operated in a specific orientation, and thus are not to be construed as limiting the scope of the invention; the orientations “inside and outside” refer to the inside and outside of the contours of the components themselves.
  • spatially relative terms such as “above”, “above”, “on top”, “above”, etc., may be used herein to describe as in the drawings.
  • the exemplary term “above” can include both “over” and "under”.
  • the device can also be positioned in other different ways (rotated 90 degrees or at other orientations) and the corresponding description of the space used herein is interpreted accordingly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)

Abstract

L'invention concerne une structure de buse, un dispositif de jet et un moteur. La structure de buse (2) comprend : un corps de buse (10), le corps de buse (10) étant pourvu d'un canal d'écoulement de liquide (11), une première extrémité du canal d'écoulement de liquide (11) étant un orifice d'entrée de liquide (12), et une deuxième extrémité du canal d'écoulement de liquide (11) étant un orifice de jet de liquide (13) ; et une coupelle de turbulence (20), la coupelle de turbulence (20) étant disposée dans le canal d'écoulement de liquide (11) et située au niveau de l'orifice de jet de liquide (13). Le corps de buse (10) est aussi pourvu d'un canal d'écoulement d'air (14), une première extrémité du canal d'écoulement d'air (14) étant un orifice d'entrée d'air (15), et une deuxième extrémité du canal d'écoulement d'air (14) étant un orifice de jet d'air (16). L'orifice de jet d'air (16) est espacé de l'orifice de jet de liquide (13) de façon à exercer une action de cisaillement sur un cône de carburant liquide atomisé éjecté hors de l'orifice de jet de liquide (13). Le dispositif de jet résout le problème de la performance d'un moteur de fusée à carburant liquide qui est affectée par la combustion incomplète du carburant liquide à cause d'un mauvais effet d'atomisation sur le carburant liquide de dispositifs à jet dans l'état de la technique.
PCT/CN2018/079768 2017-12-25 2018-03-21 Structure de buse, dispositif de jet et moteur Ceased WO2019127936A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201721843393.8U CN207795422U (zh) 2017-12-25 2017-12-25 喷嘴结构、喷射装置和发动机
CN201721843393.8 2017-12-25

Publications (1)

Publication Number Publication Date
WO2019127936A1 true WO2019127936A1 (fr) 2019-07-04

Family

ID=63281144

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2018/079768 Ceased WO2019127936A1 (fr) 2017-12-25 2018-03-21 Structure de buse, dispositif de jet et moteur

Country Status (2)

Country Link
CN (1) CN207795422U (fr)
WO (1) WO2019127936A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112177798A (zh) * 2020-09-28 2021-01-05 上海空间推进研究所 适用于航天器发动机的隔热结构
CN116659869A (zh) * 2023-03-31 2023-08-29 西安航天动力研究所 用于发动机推力室点火喷嘴内涡流器的液试工装

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114434206B (zh) * 2022-03-14 2022-08-16 慧士通医疗器械有限公司 用于数控机床的层流控屑冷却组件及含该组件的数控机床
CN114354203B (zh) * 2022-03-18 2022-06-03 成都中科翼能科技有限公司 一种涡流器和喷嘴一体化性能试验装置

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0344463A1 (fr) * 1988-06-01 1989-12-06 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Injecteur du type coaxial pour chambre de combustion pour fusées
CN101782027A (zh) * 2009-01-19 2010-07-21 北京航空航天大学 适用于大流量的气气喷注器及设计方法
CN101956981A (zh) * 2010-07-08 2011-01-26 中国航天科技集团公司第六研究院第十一研究所 一种气液组元高室压大范围变工况燃烧器
CN203570457U (zh) * 2013-10-28 2014-04-30 北京航天动力研究所 一种两级掺混式喷嘴装置
CN103867340A (zh) * 2012-12-12 2014-06-18 中国人民解放军国防科学技术大学 一种双旋流喷注器
CN205277629U (zh) * 2015-10-30 2016-06-01 北京控制工程研究所 一种用于双组元喷注器的锥度式旋涡器结构

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0344463A1 (fr) * 1988-06-01 1989-12-06 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Injecteur du type coaxial pour chambre de combustion pour fusées
CN101782027A (zh) * 2009-01-19 2010-07-21 北京航空航天大学 适用于大流量的气气喷注器及设计方法
CN101956981A (zh) * 2010-07-08 2011-01-26 中国航天科技集团公司第六研究院第十一研究所 一种气液组元高室压大范围变工况燃烧器
CN103867340A (zh) * 2012-12-12 2014-06-18 中国人民解放军国防科学技术大学 一种双旋流喷注器
CN203570457U (zh) * 2013-10-28 2014-04-30 北京航天动力研究所 一种两级掺混式喷嘴装置
CN205277629U (zh) * 2015-10-30 2016-06-01 北京控制工程研究所 一种用于双组元喷注器的锥度式旋涡器结构

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112177798A (zh) * 2020-09-28 2021-01-05 上海空间推进研究所 适用于航天器发动机的隔热结构
CN112177798B (zh) * 2020-09-28 2021-11-23 上海空间推进研究所 适用于航天器发动机的隔热结构
CN116659869A (zh) * 2023-03-31 2023-08-29 西安航天动力研究所 用于发动机推力室点火喷嘴内涡流器的液试工装

Also Published As

Publication number Publication date
CN207795422U (zh) 2018-08-31

Similar Documents

Publication Publication Date Title
CN111594351B (zh) 一种变推力针栓喷注器
CN110779042B (zh) 旋转爆震燃烧室及具有其的发动机
CN110259604B (zh) 一种针栓喷注器
WO2019127936A1 (fr) Structure de buse, dispositif de jet et moteur
WO2013029476A1 (fr) Pompe à jet annulaire
CN203570457U (zh) 一种两级掺混式喷嘴装置
CN102716827A (zh) 气液两相压平衡广角均布细雾喷嘴
CN112474094B (zh) 一种超音速气流与旋流负压耦合的远程喷射方法及装置
CN101776026A (zh) 一种吸气式脉冲爆震发动机进气道
US20180171954A1 (en) Fluid injector orifice plate for colliding fluid jets
CN103115027A (zh) 超声速环流引射喷管
US8567198B2 (en) Injection nozzle having constant diameter pin and method for operating the injection nozzle
CN107314398B (zh) 一种两组元旋流自引射喷嘴
CN109631085A (zh) 后掠圆弧型气动雾化蒸发式稳定器
US7320440B2 (en) Low cost pressure atomizer
CN116928698A (zh) 一种喷嘴头、双燃料喷嘴及燃烧室
CN206746858U (zh) 高粘度流体多级高效雾化喷头
CN113756989B (zh) 一种旋流辅助雾化且旋流度可调的气/液针栓喷注器
CN113187637A (zh) 一种带交汇结构的复合孔喷嘴
CN117073011B (zh) 一种三通路双燃料喷嘴及燃烧室
CN208398081U (zh) 降低噪音的燃气喷嘴及燃烧器
CN114602675B (zh) 一种具有分流结构的降噪喷嘴
CN101382109B (zh) 直喷式柴油机喷油器及进气道
CN209909897U (zh) 一种液体燃烧喷嘴
CN114962065A (zh) 一种带中心锥体的新型激波聚焦起爆装置及操作方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18896800

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

32PN Ep: public notification in the ep bulletin as address of the adressee cannot be established

Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 17/11/2020)

122 Ep: pct application non-entry in european phase

Ref document number: 18896800

Country of ref document: EP

Kind code of ref document: A1