CN114810424A - Engine active cooling cavity structure based on spray cooling - Google Patents
Engine active cooling cavity structure based on spray cooling Download PDFInfo
- Publication number
- CN114810424A CN114810424A CN202210473407.0A CN202210473407A CN114810424A CN 114810424 A CN114810424 A CN 114810424A CN 202210473407 A CN202210473407 A CN 202210473407A CN 114810424 A CN114810424 A CN 114810424A
- Authority
- CN
- China
- Prior art keywords
- cavity
- cooling
- coolant
- engine
- throat
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 73
- 239000007921 spray Substances 0.000 title claims abstract description 34
- 239000002826 coolant Substances 0.000 claims abstract description 42
- 238000005507 spraying Methods 0.000 claims abstract description 5
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 3
- 230000009471 action Effects 0.000 claims description 13
- 238000002485 combustion reaction Methods 0.000 claims description 9
- 230000005686 electrostatic field Effects 0.000 claims description 8
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 230000001965 increasing effect Effects 0.000 description 11
- 239000007788 liquid Substances 0.000 description 11
- 238000000889 atomisation Methods 0.000 description 10
- 239000012530 fluid Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000004907 flux Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000001172 regenerating effect Effects 0.000 description 4
- 108091053398 TRIM/RBCC family Proteins 0.000 description 3
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000003116 impacting effect Effects 0.000 description 3
- 239000003350 kerosene Substances 0.000 description 3
- 239000012528 membrane Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 230000005068 transpiration Effects 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
Images
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
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F02K7/18—Composite ram-jet/rocket engines
Abstract
The invention discloses an engine active cooling cavity structure based on spray cooling, which comprises: engine throat, it is the column cavity, encloses by double shell, forms the cavity structure between double shell, and wherein, the middle part of outer casing is protruding to the outside, and the cavity of formation is: the front end and the rear end are in slit shapes, and the middle part is an outward-expanding concave cavity; a plurality of atomizing nozzles are arranged on the outer shell and positioned in the cavity in a circumferential direction at intervals, and each atomizing nozzle is perpendicular to the wall surface of the outer shell where the atomizing nozzle is positioned; the atomizing nozzles are used for spraying the coolant to the inner shell in the cavity and cover the wall surface of the whole inner shell, and the coolant sprayed by the adjacent atomizing nozzles does not have an overlapping area on the wall surface of the inner shell; each atomizing nozzle is connected to the same pole of a high voltage power supply for providing an electrical charge to the sprayed coolant. By adopting a throat cavity structure of the rocket engine and using a spray cooling method, the cooling is more uniform and the coolant distribution is optimized.
Description
Technical Field
The invention belongs to the technical field of heat transfer and flow, and particularly relates to an engine throat with an active cooling concave cavity structure.
Background
The stability and reusability of an engine propulsion system place high demands on its thermal protection. The conventional active cooling mode of the rocket engine comprises the following steps: regenerative cooling, film cooling, transpiration cooling, and impingement cooling. For an ejection rocket in an RBCC engine, regenerative cooling is adopted in an ejection mode, and the throat heat flow density is usually 10MW/m 2 ～100MW/m 2 Single regenerative cooling is difficult to meet thermal protection requirements; the membrane can effectively reduce the temperature of the wall surface, but the efficiency of membrane cooling and the length of the covered wall surface have higher requirements on the flow rate of the coolant, and part of fuel for liquid membrane cooling cannot participate in combustion, so that the thrust performance of the engine is reduced; transpiration cooling is in fact a limiting form of film cooling, also increasing thrust losses. For impingement cooling, the defects still exist, the heat exchange is not uniform, and the cooled surface has a larger temperature gradient; the coolant is unevenly distributed, which can affect the uniformity of cooling of the engine case.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an engine active cooling cavity structure based on spray cooling aiming at the defects of the prior art, wherein the rocket engine throat cavity structure is adopted, and a spray cooling method is used, so that the cooling is more uniform, and the coolant distribution is optimized.
In order to solve the technical problem, the invention adopts the technical scheme that an engine active cooling cavity structure based on spray cooling comprises: engine throat, it is the column cavity, encloses by double shell, forms the cavity structure between double shell, and wherein, the middle part of outer casing is protruding to the outside, and the cavity of formation is: the front end and the rear end are in slit shapes, and the middle part is an outward-expanding concave cavity;
the front end of the engine throat is used for being connected with the combustion chamber, and the concave cavity is communicated with the cooling cavity of the combustion chamber; the rear end of the engine throat is used for being connected with the spray pipe, and the concave cavity is communicated with the cooling cavity of the spray pipe;
a plurality of atomizing nozzles are arranged on the outer shell and positioned at the concave cavity in a circumferential direction at intervals, and each atomizing nozzle is perpendicular to the wall surface of the outer shell where the atomizing nozzle is positioned; the atomizing nozzles are used for spraying the coolant to the inner shell in the cavity and cover the wall surface of the whole inner shell, and the coolant sprayed by the adjacent atomizing nozzles does not have an overlapping area on the wall surface of the inner shell;
each atomizing nozzle is connected to the same pole of a high voltage power supply for providing an electrical charge to the sprayed coolant.
Further, the height H of the concave cavity is 1-2 times of the radius R of the throat part; the top length of the cavity is L,
furthermore, the number of the atomizing nozzles is six, and the atomizing nozzles are arranged at equal intervals.
The invention also discloses a working mode of the engine active cooling cavity structure based on spray cooling, which is characterized by comprising the following working modes: the coolant is evenly injected into each atomizing nozzle in equal quantity, and is connected with a high-voltage power supply, an electrostatic field is formed in the concave cavity, the coolant is crushed into tiny liquid drops under the action of the electrostatic field, the tiny liquid drops carry the same charges and repel each other, the tiny liquid drops are crushed again and impact the inner shell of the concave cavity, and the high-heat-flow area of the throat is cooled through convection heat exchange and phase change heat absorption.
The invention has the following advantages: 1. the spray cooling has a certain atomization angle, the area of the coolant impacting the wall surface is large, and the speed is uniform. The turbulence degree in the whole throat cooling interlayer is increased by directly impacting the hot surface through high-speed liquid drops, the specific surface area of the coolant in spray cooling is larger, the heat exchange area of the fluid is increased, and the circumferential multi-nozzle structure enhances the mutual heat exchange in the fluid, is favorable for reducing the temperature gradient in the fluid, increasing the convective heat exchange coefficient of the coolant and the wall surface and enhancing the heat exchange effect; and effectively solve the uneven problem of coolant flow secondary distribution. 2. Under the action of electrostatic force, secondary cooling in the atomization process does not need the action of pneumatic force any more, the spray Weber number is indirectly increased, the atomization characteristic is enhanced, the specific surface area of the coolant is increased, and the speed is more uniform. 3. The coolant has the same charge, the coolant is atomized under the action of an electrostatic field formed by the nozzle and the hot surface, the atomized liquid drops have the same charge, and the repulsive force improves the atomization efficiency and further improves the cooling performance. In addition, the electrostatic force enables the coolant to be more easily adsorbed on the hot surface, the heat exchange quality flux is enhanced, and the heat exchange is enhanced. 3. The method can effectively solve the problem that the coolant of the RBCC engine cannot be atomized in the high-altitude lean air environment.
Drawings
FIG. 1 is a schematic diagram of a spray cooling based engine according to the present invention;
FIG. 2 is a schematic diagram of an active cooling cavity configuration for a spray cooling based engine according to the present invention;
FIG. 3 is a schematic diagram of a spray cooled engine active cooling cavity configuration with a high voltage electrostatic power supply connected in accordance with the present invention;
FIG. 4 is a schematic diagram of the arrangement of the atomizing nozzles in the throat of the engine.
Wherein: 1. an engine throat; 1-1. outer shell; 1-2. inner shell; 2. an atomizing nozzle; 3. a high voltage power supply; 4. a combustion chamber; 5. and (4) a spray pipe.
Detailed Description
The invention discloses an engine active cooling cavity structure based on spray cooling, which is shown in figures 1 and 2 and comprises: the engine throat 1 is a columnar cavity and is enclosed by a double-layer shell, a cavity structure is formed between the double-layer shell, wherein the middle part of the outer shell 1-1 protrudes to the outside, and the formed cavity is as follows: the front end and the rear end are in slit shapes, and the middle part is an outwardly expanded concave cavity a. The height H of the concave cavity (a) is 1-2 times of the throat radius R; the top length of the concave cavity (a) is L,
a plurality of atomizing nozzles 2 are arranged on the outer shell 1-1 and positioned at the concave cavity a at intervals in a circumferential direction, and each atomizing nozzle 2 is perpendicular to the wall surface of the outer shell where the atomizing nozzle is positioned; the atomizing nozzle 2 is used for spraying coolant to the inner shell in the concave cavity, and the coolant covers the whole wall surface of the inner shell. The optimum design is that the coolant sprayed by adjacent atomizing nozzles 2 does not overlap on the inner housing 1-2 wall.
As shown in fig. 3, each atomizing nozzle 2 is connected to the same pole of the high voltage power supply 3, the high voltage power supply 3 is used for providing charges to the sprayed coolant molecules, the coolant is broken into tiny droplets under the action of an electrostatic field, and further broken under the action of the repulsion force of like charges, and the tiny droplets impact the throat part to exchange heat, so that the high heat flow area of the throat part is cooled through convection heat exchange and phase change heat absorption. In addition, the coolant is more easily adsorbed on the hot surface by the electrostatic field, so that the heat exchange quality flux is enhanced, and the heat exchange is enhanced.
The coolant is sprayed out from each atomizing nozzle 2, the atomization is carried out for the first time, the spraying process to the hot surface is secondary atomization cooling, under the action of electrostatic force, the secondary cooling in the atomization process does not need the action of pneumatic force any more, the spray Weber number is indirectly increased, the atomization characteristic is enhanced, the specific surface area of the coolant is increased, and the speed is more uniform.
As shown in fig. 4, the nozzles are arranged along the circumferential direction of the engine throat, and the number of the nozzles can be designed according to the optimal spray area corresponding to spray cooling according to different application conditions. When the six atomizing nozzles 2 are arranged at equal intervals, the sprayed coolant has no overlapping area on the wall surface of the inner shell 1-2, and the cooling effect is best.
The numerical simulation and steady state calculation of the active cooling cavity structure of the engine based on spray cooling in the invention are as follows:
the fuel system is as follows: oxygen, kerosene, total flow: 1kg/s, and the oxygen-fuel ratio O/F is 4; wherein the flow rate of kerosene as a coolant is 200g/s, the initial temperature is 300K, when six atomizing nozzles 2 are adopted, the flow rate of a single nozzle is 36.7g/s, the spray cone angle is 40 degrees, and the diameter of a nozzle outlet is 0.6 mm.
The cooling temperature and heat transfer coefficient of the cooling of the re-entrant structures in the present invention are shown in tables 1 and 2, along with various other cooling means and structures. As can be seen from the data in the table, the spray cooling of the present invention has a small heat exchange area compared to the regenerative cooling, but the cooling method itself is smallThe high heat exchange coefficient is achieved, and the cooling requirement of the throat part of the engine can be met. In the invention, the specific surface area of the liquid drop is increased, the heat absorption capacity is strong, and the heat exchange efficiency is improved. The heat flow density of the throat of the ejection rocket under the ejection mode of the RBCC engine is 2.4 multiplied by 10 7 W/m 2 Coefficient of heat transfer
Wherein T is w And T 0 Wall temperature and kerosene initial temperature, q is heat flux density.
As shown by data in the table, the six-nozzle arrangement has the best cooling performance, and the spray areas are not overlapped and just cover the heat exchange surface of the throat part.
TABLE 1 Cooling temperature of throat inner wall surface by different cooling methods
TABLE 2 Heat transfer coefficients for different cooling modes
Likewise, the improvement in spray cooling over coolant redistribution is shown in table 3.
TABLE 3 exit mass concentrations of different channels
From the results in table 3, it is intuitive that spray cooling has better flow secondary distribution performance. The front end is closer to the engine combustion chamber, the design flow is highest, and the requirements that the temperature of the front end engine combustion chamber is high and the required coolant is large are met.
During engine operation, coolant enters the cavity a from the inlet through the atomizing nozzle 2. The coolant is charged by contacting with a high-voltage electrode, is broken into tiny liquid drops under the action of an electrostatic field, is further broken under the action of repulsion force of like-charge charges, strikes the throat part, exchanges heat, and cools a high-heat-flow area of the throat part through convection heat exchange and phase-change heat absorption.
Under the action of electrostatic force, secondary cooling in the atomization process does not need the action of pneumatic force any more, the spray Weber number is indirectly increased, the atomization characteristic is enhanced, the specific surface area of the coolant is increased, and the speed is more uniform. After the liquid drops directly impact the hot surface, the charged liquid drops and the hot surface have stronger adsorption force, so that the splashing effect of the liquid drops impacting the wall is reduced, and the heat exchange mass flux is enhanced. The circumferential multi-nozzle structure enhances the mutual heat exchange in the fluid, and is beneficial to reducing the temperature gradient in the fluid. The coolant absorbs heat and flows into the front combustion chamber to be combusted.
Claims (4)
1. An engine active cooling cavity structure based on spray cooling, comprising: engine throat (1), it is the column cavity, encloses by double-deck casing, forms the cavity structure between double-deck casing, and wherein, the middle part of outer casing (1-1) is to outside protruding, and the cavity of formation is: the front end and the rear end are in slit shapes, and the middle part is an outward-expanding concave cavity (a);
the front end of the engine throat part (1) is used for being connected with the combustion chamber (4), and the concave cavity (a) is communicated with a cooling cavity of the combustion chamber (4); the rear end of the engine throat part (1) is connected with the spray pipe (5), and the concave cavity (a) is communicated with the cooling cavity of the spray pipe (5);
a plurality of atomizing nozzles (2) are arranged on the outer shell (1-1) and positioned at the concave cavity (a) in a circumferential direction at intervals, and each atomizing nozzle (2) is perpendicular to the wall surface of the outer shell where the atomizing nozzle is positioned; the atomizing nozzles (2) are used for spraying coolant onto the inner shell in the concave cavity and cover the wall surface of the whole inner shell, and the coolant sprayed by the adjacent atomizing nozzles (2) does not have an overlapping area on the wall surface of the inner shell (1-2);
each atomizing nozzle (2) is connected to the same pole of a high voltage power supply (3), the high voltage power supply (3) being used to provide an electrical charge to the sprayed coolant.
2. The active cooling cavity structure of the engine based on spray cooling as claimed in claim 1, wherein the height H of the cavity (a) is 1-2 times of the throat radius R; the top length of the cavity (a) is L,
3. the active cooling cavity structure of the spray cooling-based engine is characterized in that the number of the atomizing nozzles (2) is six, and the six atomizing nozzles are arranged at equal intervals.
4. An operation mode of an active cooling cavity structure of an engine based on spray cooling according to any one of claims 1-3, characterized by the following operation mode: the coolant is evenly injected into the atomizing nozzles (2) in equal quantity, a high-voltage power supply (3) is connected, an electrostatic field is formed in the concave cavity (a), the coolant is broken into tiny droplets under the action of the electrostatic field, the tiny droplets carry the same charges and are mutually repelled and broken again, the tiny droplets impact the inner shell of the concave cavity (a), and the high-heat-flow area of the throat is cooled through convection heat transfer and phase-change heat absorption.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210473407.0A CN114810424B (en) | 2022-04-29 | 2022-04-29 | Engine active cooling concave cavity structure based on spray cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210473407.0A CN114810424B (en) | 2022-04-29 | 2022-04-29 | Engine active cooling concave cavity structure based on spray cooling |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114810424A true CN114810424A (en) | 2022-07-29 |
| CN114810424B CN114810424B (en) | 2024-02-02 |
Family
ID=82511781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210473407.0A Active CN114810424B (en) | 2022-04-29 | 2022-04-29 | Engine active cooling concave cavity structure based on spray cooling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114810424B (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6244041B1 (en) * | 1999-01-21 | 2001-06-12 | Otkrytoe Aktsioneroe Obschestvo “Nauchao-Proizvodatveabnoe Obiedianie Nauchao-Proizvodatvesnoe Obiediane “Energomash” Imeni Akademika V.P. Glushko” | Liquid-propellant rocket engine chamber and its casing |
| US20030154720A1 (en) * | 2002-02-20 | 2003-08-21 | John Boehnlein | Ejector based engines |
| CN101000136A (en) * | 2006-01-09 | 2007-07-18 | 斯奈克玛 | Cooling of a multimode injection device for a combustion chamber, particularly for a gas turbine |
| US20090288390A1 (en) * | 2008-05-23 | 2009-11-26 | Thomas Clayton Pavia | Simplified thrust chamber recirculating cooling system |
| US20110005193A1 (en) * | 2009-07-07 | 2011-01-13 | Thomas Clayton Pavia | Method and apparatus for simplified thrust chamber configurations |
| CN106949497A (en) * | 2017-03-10 | 2017-07-14 | 中国人民解放军装备学院 | A kind of re-generatively cooled dual channel scheme of use Spray Wall-Impingement enhanced heat exchange |
| CN108457768A (en) * | 2017-08-30 | 2018-08-28 | 上海空间推进研究所 | A kind of direct current cold wall type engine chamber |
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN109595096A (en) * | 2018-12-03 | 2019-04-09 | 上海空间推进研究所 | A kind of ejector filler operatic tunes temperature barrier |
| CN109812352A (en) * | 2019-03-06 | 2019-05-28 | 中南大学 | Rocket ejector and its thermal protection structure and thermal protection method |
| CN110792531A (en) * | 2019-11-22 | 2020-02-14 | 中国人民解放军战略支援部队航天工程大学 | Intelligent atomizing nozzle based on high-voltage discharge and spraying control system |
| US20200373141A1 (en) * | 2019-05-21 | 2020-11-26 | Accion Systems, Inc. | Apparatus for electrospray emission |
| CN112177804A (en) * | 2020-09-16 | 2021-01-05 | 上海空间推进研究所 | Low-temperature engine suitable for space device |
| US20210324818A1 (en) * | 2016-09-30 | 2021-10-21 | Arianegroup Sas | Chilldown device and method |
-
2022
- 2022-04-29 CN CN202210473407.0A patent/CN114810424B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6244041B1 (en) * | 1999-01-21 | 2001-06-12 | Otkrytoe Aktsioneroe Obschestvo “Nauchao-Proizvodatveabnoe Obiedianie Nauchao-Proizvodatvesnoe Obiediane “Energomash” Imeni Akademika V.P. Glushko” | Liquid-propellant rocket engine chamber and its casing |
| US20030154720A1 (en) * | 2002-02-20 | 2003-08-21 | John Boehnlein | Ejector based engines |
| CN101000136A (en) * | 2006-01-09 | 2007-07-18 | 斯奈克玛 | Cooling of a multimode injection device for a combustion chamber, particularly for a gas turbine |
| US20090288390A1 (en) * | 2008-05-23 | 2009-11-26 | Thomas Clayton Pavia | Simplified thrust chamber recirculating cooling system |
| US20110005193A1 (en) * | 2009-07-07 | 2011-01-13 | Thomas Clayton Pavia | Method and apparatus for simplified thrust chamber configurations |
| US20210324818A1 (en) * | 2016-09-30 | 2021-10-21 | Arianegroup Sas | Chilldown device and method |
| CN106949497A (en) * | 2017-03-10 | 2017-07-14 | 中国人民解放军装备学院 | A kind of re-generatively cooled dual channel scheme of use Spray Wall-Impingement enhanced heat exchange |
| CN108457768A (en) * | 2017-08-30 | 2018-08-28 | 上海空间推进研究所 | A kind of direct current cold wall type engine chamber |
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN109595096A (en) * | 2018-12-03 | 2019-04-09 | 上海空间推进研究所 | A kind of ejector filler operatic tunes temperature barrier |
| CN109812352A (en) * | 2019-03-06 | 2019-05-28 | 中南大学 | Rocket ejector and its thermal protection structure and thermal protection method |
| US20200373141A1 (en) * | 2019-05-21 | 2020-11-26 | Accion Systems, Inc. | Apparatus for electrospray emission |
| CN110792531A (en) * | 2019-11-22 | 2020-02-14 | 中国人民解放军战略支援部队航天工程大学 | Intelligent atomizing nozzle based on high-voltage discharge and spraying control system |
| CN112177804A (en) * | 2020-09-16 | 2021-01-05 | 上海空间推进研究所 | Low-temperature engine suitable for space device |
Non-Patent Citations (1)
| Title |
|---|
| 葛自良: "液体静电雾化现象及其应用", 自然杂志, vol. 22, no. 1, pages 37 - 40 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114810424B (en) | 2024-02-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108457768B (en) | Direct-flow cold-wall type engine combustion chamber | |
| CN108144758B (en) | Spray cooling device based on electrostatic atomization | |
| WO2021217792A1 (en) | Combustion assembly structure of turbojet engine | |
| CN103968418A (en) | Double-layer-wall heat insulation screen used for afterburner | |
| CN110594036B (en) | Active cooling double-nozzle support plate ejection rocket of rocket-based combined cycle engine | |
| US4974415A (en) | Staged, coaxial multiple point fuel injection in a hot gas generator | |
| CN111256168A (en) | Oil supply and cooling integrated air suction type pulse detonation engine structure | |
| CN109458271A (en) | A kind of rotation detonation engine air intake duct and jet pipe integrated design method | |
| CN110375331B (en) | Evaporating pipe structure for engine combustion chamber and engine combustion chamber structure | |
| CN108613217A (en) | A kind of partly-premixed injection device of distribution formula and combustion chamber | |
| CN114810424B (en) | Engine active cooling concave cavity structure based on spray cooling | |
| CN113739207B (en) | Rotary detonation combustion chamber adopting pneumatic inner column | |
| CN113669756B (en) | Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method | |
| CN113551265A (en) | Fuel nozzle and gas turbine | |
| CN112413580B (en) | Heavy oil burner using bubble atomizing nozzle and operation method thereof | |
| CN117404684A (en) | Direct-injection type plasma jet atomization double-layer fuel spray rod with air cooling structure | |
| CN116146981B (en) | Injection panel using air film cooling partition plate nozzle | |
| CN113757723B (en) | Composite impact air film cooling wall type flame stabilizer and combustion chamber | |
| CN113295422B (en) | Modularized single-double-throat switching type steam generating device | |
| CN210304177U (en) | Jet swirl nozzle structure and spraying device | |
| JPH05332164A (en) | Regeneration type gas turbine | |
| CN114592989A (en) | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof | |
| CN114214586A (en) | Supersonic flame spray gun for preparing amorphous alloy coating and spraying method thereof | |
| CN110005558A (en) | A kind of anti-carbon deposition fuel injection equipment (FIE) | |
| CN112253333A (en) | Collector inlet flow guide structure with flow equalizing function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |