CN114151234B - Regenerated cooling liquid oxygen methane torch igniter - Google Patents
Regenerated cooling liquid oxygen methane torch igniter Download PDFInfo
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- CN114151234B CN114151234B CN202210014767.4A CN202210014767A CN114151234B CN 114151234 B CN114151234 B CN 114151234B CN 202210014767 A CN202210014767 A CN 202210014767A CN 114151234 B CN114151234 B CN 114151234B
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- methane
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- oxygen
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- squib
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 317
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 title claims abstract description 39
- 239000000110 cooling liquid Substances 0.000 title claims abstract description 28
- 238000001816 cooling Methods 0.000 claims abstract description 96
- 230000001172 regenerating effect Effects 0.000 claims abstract description 91
- 239000007788 liquid Substances 0.000 claims abstract description 47
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- 230000002093 peripheral effect Effects 0.000 claims abstract description 9
- 239000001301 oxygen Substances 0.000 claims description 51
- 229910052760 oxygen Inorganic materials 0.000 claims description 51
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 48
- 230000001154 acute effect Effects 0.000 claims description 8
- 230000008929 regeneration Effects 0.000 abstract description 11
- 238000011069 regeneration method Methods 0.000 abstract description 11
- 239000000446 fuel Substances 0.000 abstract description 8
- 238000002679 ablation Methods 0.000 abstract description 7
- 230000008676 import Effects 0.000 abstract description 3
- 239000003380 propellant Substances 0.000 description 12
- 238000002156 mixing Methods 0.000 description 7
- 230000009286 beneficial effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 239000007800 oxidant agent Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000001590 oxidative effect Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000004075 alteration Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- NLOAOXIUYAGBGO-UHFFFAOYSA-N C.[O] Chemical compound C.[O] NLOAOXIUYAGBGO-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Bags (AREA)
Abstract
The invention discloses a regenerated cooling liquid oxygen methane torch igniter, relates to the technical field of ignition devices, and solves the technical problems of ablation and poor heat protection performance of severe combustion in the igniter in the related art. The methane shell is arranged outside the ignition tube and is enclosed with the ignition tube to form a methane cavity, and the methane cavity is communicated with the ignition chamber through the methane nozzle; the regenerative cooling assembly is arranged in the methane cavity and is arranged at the peripheral wall of the ignition tube, and a regenerative cooling channel is formed in the regenerative cooling assembly. Through this scheme, during operation liquid methane flows into from the liquid methane import of methane shell, gets into the ignition room of ignition tube through methane nozzle through methane chamber and regeneration cooling module, and on the one hand high temperature ignition tube wall is cooled off, and on the other hand liquid fuel gets into the ignition room with higher temperature, has realized the regeneration of energy, and this scheme has improved the easy ablation of torch igniter, the difficult problem of thermal protection.
Description
Technical Field
The invention relates to the technical field of ignition devices, in particular to a regenerated cooling liquid oxygen methane torch igniter.
Background
Regarding the torch igniter, from the research experience of the ignition technology of the liquid oxygen methane and the oxyhydrogen engine, the ignition of methane is more difficult than other low-temperature propellants, the ignition delay time is longer, and the ignition energy requirement is higher. The inner wall of the torch igniter can be heated to a higher temperature by violent combustion in a limited space, and the problems that the inner wall of the igniter is easy to ablate, the heat protection performance is poor and the like exist.
Disclosure of Invention
The application provides a regenerated cooling liquid oxygen methane torch igniter, which solves the technical problems of easy ablation and poor heat protection performance caused by severe combustion in the igniter in the related art.
The application provides a regenerated cooling liquid oxygen methane torch igniter which comprises a squib, a methane shell and a regenerated cooling component, wherein an ignition chamber is arranged in the squib, a methane nozzle is arranged in the squib, the squib is arranged outside the methane shell, a liquid methane inlet is formed in the methane shell, the methane shell and the squib are enclosed to form a methane cavity, the liquid methane inlet is communicated with the methane cavity, the methane cavity is communicated with the ignition chamber through the methane nozzle, the regenerated cooling component is arranged in the methane cavity, the regenerated cooling component is arranged at the peripheral wall of the squib, a regenerated cooling channel is formed in the regenerated cooling component, and the regenerated cooling component and the methane nozzle are arranged at intervals.
Optionally, the regenerative cooling assembly is arranged along a circumferential direction of the squib, and the regenerative cooling channels are arranged along an axial direction of the squib.
Optionally, the regenerative cooling assembly is a regenerative cooling rib or a regenerative cooling fin, the regenerative cooling rib or the regenerative cooling fin is arranged along the axial direction of the ignitron, a plurality of regenerative cooling ribs or regenerative cooling fins are arranged at intervals along the circumferential direction of the ignitron, and two adjacent regenerative cooling ribs or regenerative cooling fins are enclosed to form a regenerative cooling channel.
Optionally, the regenerative cooling channels are arranged in a linear or spiral manner, and the cross sections of the regenerative cooling channels are arranged in a rectangular, triangular or trapezoidal manner.
Optionally, the regenerative cooling assembly comprises a first assembly and a second assembly, the first assembly and the second assembly are arranged at the outer peripheral wall of the ignitron at intervals, the first assembly, the second assembly and the ignitron are enclosed to form a first annular zone, and the methane nozzle is arranged in the area of the ignitron opposite to the first annular zone.
Optionally, the regenerative cooling assembly further comprises a third assembly, the first assembly, the second assembly and the third assembly are sequentially arranged at intervals, the second assembly, the third assembly and the ignitron are enclosed to form a second annular belt, and the second annular belt is arranged between the liquid methane inlet and the first annular belt.
Optionally, the squib is provided with at least one row of methane tangential holes in a region opposite to the second endless belt, each row of methane tangential holes comprises at least two methane tangential holes which are arranged at intervals along the circumferential direction of the squib, and the methane tangential holes are arranged along the tangential direction of the inner edge of the squib so as to form a rotating liquid film on the inner wall of the squib.
Optionally, the ignition tube is further provided with an oxygen nozzle, and the regenerated cooling liquid oxygen methane torch igniter further comprises:
The oxygen shell is provided with an ignition tube, the oxygen shell is provided with a liquid oxygen inlet, the oxygen shell and the ignition tube are enclosed to form an oxygen cavity, the liquid oxygen inlet is communicated with the oxygen cavity, and the oxygen cavity is communicated with the ignition chamber through an oxygen nozzle.
Optionally, the regenerated cooling liquid oxygen methane torch igniter further comprises a spark plug and a downstream combustion device, wherein the spark plug and the downstream combustion device are respectively and spirally arranged at two ends of the ignition tube.
Optionally, the ignition tube is provided with n oxygen nozzles uniformly distributed along the circumferential direction at intervals, n is a positive integer not less than 2, the included angle between the axes of the oxygen nozzles and the axis of the ignition tube is an acute angle, and the axes of the n oxygen nozzles and the axis of the ignition tube intersect at a first point;
the ignition tube is provided with m methane nozzles which are uniformly distributed along the circumferential direction at intervals, m is a positive integer which is not less than 2, the included angle between the axis of the methane nozzle and the axis of the ignition tube is an acute angle, and the m methane nozzles and the axis of the ignition tube are intersected at a second point;
The end face of the spark plug rod of the spark plug is separated from a first point by a first distance, the first point is separated from a second point by a second distance, the axis of the oxygen nozzle forms a first included angle with the axis of the spark plug, and the methane nozzle forms a second included angle with the axis of the spark plug.
The application has the following beneficial effects: the application provides a regenerated cooling liquid oxygen methane torch igniter, which relates to liquid methane propellant and can be expanded to other non-spontaneous combustion propellant, and particularly comprises a regenerated cooling component which is arranged outside an ignition tube, is arranged in a methane cavity formed by a methane shell and the ignition tube, and is limited at the peripheral wall of the regenerated cooling component, when the liquid methane works, the liquid methane flows in from a liquid methane inlet of the methane shell, and enters an ignition chamber of the ignition tube through a methane nozzle via the methane cavity and a regenerated cooling channel of the regenerated cooling component; in the process, the wall surface and liquid methane generate convective heat exchange, on one hand, the wall surface of the high-temperature ignition tube is cooled, and on the other hand, the liquid fuel enters the ignition chamber at a higher temperature, so that the regeneration of energy is realized, and the problems of easiness in ablation and difficulty in heat protection of the torch igniter are solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present invention.
FIG. 1 is a schematic cross-sectional view of a regenerative coolant oxygen methane flare igniter provided by the application;
fig. 2 is a schematic diagram of a squib of a regenerative cooling liquid oxygen methane torch igniter provided by the application.
The drawings are marked: 100-ignitron, 110-ignition chamber, 120-methane nozzle, 130-oxygen nozzle, 200-methane shell, 210-liquid methane inlet, 220-methane cavity, 300-regenerative cooling assembly, 310-regenerative cooling channel, 320-first assembly, 330-first annulus, 340-second assembly, 350-second annulus, 360-third assembly, 400-oxygen shell, 410-liquid oxygen inlet, 420-oxygen cavity, 500-spark plug, a-first distance, b-second distance, c-first included angle, d-second included angle.
Detailed Description
The embodiment of the application solves the technical problems of easy ablation and poor heat protection performance caused by severe combustion in the igniter in the related art by providing the regenerated cooling liquid oxygen methane torch igniter.
The technical scheme in the embodiment of the application aims to solve the technical problems, and the overall thought is as follows:
The utility model provides a regeneration cooling liquid oxygen methane torch igniter, including the ignition tube, methane shell and regeneration cooling subassembly, be provided with the ignition chamber in the ignition tube, the ignition tube is equipped with the methane nozzle, the methane shell is equipped with the ignition tube outward, the methane shell has been seted up liquid methane import, methane shell encloses with the ignition tube and closes and form the methane chamber, liquid methane import and methane chamber intercommunication, the methane chamber switches on with the ignition chamber through the methane nozzle, regeneration cooling subassembly sets up in the methane intracavity, regeneration cooling subassembly sets up in the peripheral wall department of ignition tube, regeneration cooling subassembly is formed with regeneration cooling channel, regeneration cooling subassembly and methane nozzle interval set up.
In order to better understand the above technical solutions, the following detailed description will refer to the accompanying drawings and specific embodiments.
Referring to fig. 1, the present embodiment discloses a regenerative cooling liquid oxygen methane torch igniter, which comprises a squib 100, a spark plug 500, a path for inputting liquid methane into an ignition chamber 110 in the squib 100, and a path for inputting liquid oxygen. It should be noted that this embodiment is applicable not only to liquid methane, but also to other non-pyrophoric propellants, in the form of a non-pyrophoric propellant torch igniter. The following description will be given in terms of specific forms of liquid methane.
As shown in fig. 1, an ignition chamber 110 is provided in the squib 100, a spark plug 500 (the reference numeral 500 of fig. 1 may also be understood as a spark plug rod) is mounted at one end of the ignition chamber 110, and a downstream combustion device such as a gas generator or a thrust chamber is mounted at the other end of the ignition chamber 110. The spark plug 500 may employ a laser or spark plug 500 to ignite the propellant entering the ignition chamber 110, creating a steady flow of high temperature combustion gases to ignite the downstream combustion apparatus. In one embodiment, the spark plug 500, the downstream combustion device are each threadably mounted to the squib 100; the downstream burner may also be flanged to the squib 100. The ignition device adopts the scheme that the ignition plug rod is in threaded connection with the ignition tube 100, and the whole ignition device is connected with a downstream combustion device through threads or flanges, so that the ignition device is convenient for detecting and maintaining faults of the ignition plug or the ignition plug 500.
Regarding the path of feeding liquid methane into the ignition chamber 110 in the squib 100, as shown in fig. 1, the regenerated cooling liquid oxygen methane torch igniter further comprises a methane shell 200, the squib 100 is arranged outside the methane shell 200, the methane shell 200 and the squib 100 are enclosed to form a methane cavity 220, a liquid methane inlet 210 is formed in the methane shell 200, and the liquid methane inlet 210 is communicated with the methane cavity 220; the squib 100 is provided with a methane nozzle 120, and a methane chamber 220 is in communication with the ignition chamber 110 through the methane nozzle 120. Liquid methane enters methane chamber 220 from liquid methane inlet 210 and then enters ignition chamber 110 through methane nozzle 120.
Regarding the path of inputting liquid oxygen into the ignition chamber 110 in the squib 100, the regenerated cooling liquid oxygen methane torch igniter further comprises an oxygen shell 400, wherein the oxygen shell 400 is arranged outside the squib 100, the oxygen shell 400 and the squib 100 are enclosed to form an oxygen cavity 420, the oxygen shell 400 is provided with a liquid oxygen inlet 410, and the liquid oxygen inlet 410 is communicated with the oxygen cavity 420; the squib 100 is further provided with an oxygen nozzle 130, and the oxygen chamber 420 is in communication with the ignition chamber 110 through the oxygen nozzle 130. Liquid oxygen enters the oxygen chamber 420 from the liquid oxygen inlet 410 and then enters the ignition chamber 110 through the oxygen nozzle 130.
Regarding methane chamber 220 and oxygen chamber 420, it may also be described that methane housing 200 encloses methane chamber 220 with the lower portion of squib 100 and oxygen housing 400 encloses oxygen chamber 420 with the upper portion of squib 100.
The regenerative cooling liquid oxygen methane torch igniter of the present embodiment is also provided with a regenerative cooling assembly 300 within methane chamber 220. Specifically, referring to fig. 1, a regenerative cooling assembly 300 is disposed in the methane chamber 220, the regenerative cooling assembly 300 is disposed at the outer peripheral wall of the squib 100, a regenerative cooling channel 310 is formed in the regenerative cooling assembly 300, and the regenerative cooling assembly 300 is disposed at a distance from the methane nozzle 120.
Liquid methane flows in from liquid methane inlet 210 of methane housing 200, through methane chamber 220 and regenerative cooling channel 310 of regenerative cooling assembly 300, and into ignition chamber 110 of squib 100 through methane nozzle 120 when in operation; in this process, the wall surface of the regenerative cooling assembly 300 performs convective heat exchange with the liquid methane, so that, on one hand, the wall surface of the high-temperature squib 100 can be cooled by the liquid methane, and on the other hand, the liquid fuel enters the ignition chamber 110 at a higher temperature, thereby realizing energy regeneration. In conclusion, the technical scheme improves the difficult problem of ablation and heat protection caused by severe combustion in the limited space of the torch igniter.
Optionally, the first assembly 320, the second assembly 340 and the third assembly 360 shown in fig. 2 belong to a specific arrangement of the regenerative cooling assembly 300, and as shown in fig. 2, the regenerative cooling assembly 300 is arranged along the circumference of the squib 100, and the regenerative cooling channels 310 are arranged along the axial direction of the squib 100. Through 360 arrangement in the circumferential direction, the heat exchange effect is improved.
It is to be understood that the definition herein of the regenerative cooling channel 310 being disposed axially of the squib 100 is to be understood in a broad sense as meaning that the regenerative cooling channel 310 is disposed generally axially of the squib 100 and need not be defined as a percentage of being disposed axially straight. For example, to enhance the heat transfer effect, the regenerative cooling channels 310 may be arranged in a spiral configuration, which may increase the flow rate of the liquid fuel. In one embodiment, the regenerative cooling channels 310 are disposed in a linear configuration. In other aspects, the number, profile, pitch, aspect ratio, etc. of regenerative cooling channels 310 may also be designed and optimized using experimentation or numerical simulation. In one embodiment, the regenerative cooling channel 310 is rectangular, triangular, or trapezoidal in cross-section.
Alternatively, as shown in fig. 1 and 2, the regenerative cooling assembly 300 may be further defined as a specific form of ribs or fins. When the regenerative cooling assembly 300 is provided with regenerative cooling ribs, the regenerative cooling ribs are arranged along the axial direction of the squib 100, a plurality of regenerative cooling ribs are arranged at intervals along the circumferential direction of the squib 100, and two adjacent regenerative cooling ribs enclose to form a regenerative cooling channel 310; when the regenerative cooling assembly 300 is provided with regenerative cooling fins, the regenerative cooling fins are arranged along the axial direction of the squib 100, a plurality of regenerative cooling fins are arranged at intervals along the circumferential direction of the squib 100, and two adjacent regenerative cooling fins enclose to form a regenerative cooling channel 310. The scheme also plays a role in equalizing flow when liquid methane flows through.
The regenerative cooling assembly 300 is further provided based on the fact that the squib 100 is provided with the methane nozzle 120. Alternatively, as shown in fig. 1 and 2, the regenerative cooling assembly 300 includes a first assembly 320 and a second assembly 340, the first assembly 320 and the second assembly 340 are spaced apart at the outer peripheral wall of the squib 100, the first assembly 320, the second assembly 340 and the squib 100 are enclosed to form a first annulus 330, and the methane nozzle 120 is disposed in the squib 100 at a region opposite to the first annulus 330. Liquid methane entering through liquid methane inlet 210 enters ignition chamber 110 from methane nozzle 120 sequentially through second assembly 340, first annulus 330; in this process, liquid methane enters the first annulus 330 from the second assembly 340, and the arrangement of the first annulus 330 improves the disadvantage that if the methane nozzle 120 is opened directly at the bottom of the regenerative cooling channel 310, methane will not flow smoothly into the ignition chamber 110 at low pressure, and on the other hand improves the convection and heat transfer effects.
Optionally, as shown in fig. 1 and 2, the regenerative cooling assembly 300 further includes a third assembly 360, where the first assembly 320, the second assembly 340, and the third assembly 360 are sequentially spaced apart, and the second assembly 340, the third assembly 360, and the squib 100 enclose a second annulus 350, and the second annulus 350 is disposed between the liquid methane inlet 210 and the first annulus 330. Liquid methane enters an open area of the second zone 350 through the third component 360 (compared with the regenerative cooling component 300), and the liquid methane of the second zone 350 passes through the second component 340, and the solution has the beneficial effect of flow equalization by adding the third component 360 to form the second zone 350, which is beneficial for the liquid methane to enter the ignition chamber 110 from the methane nozzle 120.
Optionally, the squib 100 is provided with at least one row of methane tangential holes (not shown in fig. 2) in a region opposite to the second endless belt 350, each row of methane tangential holes comprising at least two methane tangential holes arranged at intervals along the circumference of the squib 100, the methane tangential holes being arranged tangentially along the inner edge of the squib 100 to form a rotating liquid film on the inner wall of the squib 100. It should be noted that the provision of tangential holes to form a rotating liquid film belongs to the prior art, and is not described in detail in this embodiment. In this scheme, through the methane tangential hole of seting up in the second clitellum 350 region between third subassembly 360 and the second subassembly 340, liquid methane along methane tangential Kong Penru in the ignition room 110 and under the effect of gas pneumatic shearing force, form the rotatory liquid film of adherence at the ignition room 110 inner wall, the rotatory liquid film of formation separates the ignition room 110 inner wall face with high temperature gas, realizes the cooling down of ignition room 110 wall face better, improves the problem that ablation, thermal protection performance are poor.
The methane tangential holes are arranged in a row, specifically at least two methane tangential holes are circumferentially spaced apart from each other in the squib 100; and multiple rows of methane tangential holes exist graphically in the form of multiple turns.
In one embodiment, the squib 100 of the present example may be manufactured integrally with the rod material by milling the regenerative cooling channel 310 into the outer wall of the body of the squib 100, thereby forming the desired regenerative cooling assembly 300 and achieving the associated functions.
In an embodiment, the regenerated cooling liquid oxygen methane torch igniter of this embodiment, the ignitron 100 and the methane shell 200, and the ignitron 100 and the oxygen shell 400 are all connected by adopting a welding mode, and compared with a 3D printing structure and a brazing structure, the all-welded structure reduces the production cost of the torch igniter.
Regarding the oxygen nozzle 130 and the methane nozzle 120, the oxidant and the fuel enter the ignition chamber 110 in a self-striking or mutual striking manner for atomization and mixing, the ignition plug 500 is ignited to burn the liquid oxygen methane mixture in the ignition chamber 110, and the combustion generates high-temperature fuel gas to enter a downstream combustion device for completing the ignition process.
Alternatively, referring to fig. 1, the squib 100 (specifically, at the upper portion of the squib 100) is provided with n oxygen nozzles 130 uniformly distributed at intervals along the circumferential direction, n is a positive integer not less than 2, the axis of the oxygen nozzle 130 and the axis of the squib 100 are disposed at an acute angle, and the axes of the n oxygen nozzles 130 intersect with the axis of the squib 100 at a first point; the squib 100 (specifically, at the lower part of the squib 100) is provided with m methane nozzles 120 uniformly distributed along the circumferential direction at intervals, m is a positive integer not less than 2, the included angle between the axis of the methane nozzle 120 and the axis of the squib 100 is an acute angle, and the m methane nozzles 120 intersect with the axis of the squib 100 at a second point.
Note that n and m are not necessarily the same. The two propellants are rapidly collided for atomization, mixing, combustion, atomization resulting from the impact dynamics, mixing being between the oxidizer and the fuel spray fan. In this scheme, the axis of the oxygen nozzle 130 and the axis of the squib 100 are disposed at an acute angle, and the axis of the methane nozzle 120 and the axis of the squib 100 are disposed at an acute angle, as shown in fig. 1, the oxygen nozzle 130 and the methane nozzle 120 can be understood as inclined straight flow holes, and compared with radial holes and tangential holes, the inclined straight flow holes are adopted to enable the propellant to be sprayed into the igniter to have a certain penetration depth, so that the propellant is beneficial to accelerating the mixing combustion.
Further, as shown in fig. 1, the first distance a, the second distance b, the first angle c and the second angle d are formed, wherein the first distance a is the distance between the end face of the plug rod of the spark plug 500 and the first point, the second distance b is the distance between the first point and the second point, the first angle c is the angle (injection angle) formed between the axis of the oxygen nozzle 130 and the axis of the spark plug 500, and the second angle d is the angle (injection angle) formed between the methane nozzle 120 and the axis of the spark plug 500. The parameters are key design parameters for ensuring that the torch igniter is reliably and effectively ignited, the spark plug 500 is not ablated, the propellant is well atomized and mixed, and the combustion efficiency is high, and the optimal design can be carried out through test or simulation means.
For example, the first distance a and the second distance b are chosen to ensure both reliable ignition of the propellant without ablating the spark plug 500 and atomized mixing of the oxidant and fuel between the conical spray fans. A suitable first distance a ensures reliable ignition of the propellant without the spark plug 500 being ablated; at a smaller second distance b, the mixing effect of the oxidant and the fuel will be better.
On the other hand, the n oxygen nozzles 130, the m methane nozzles 120, the oxygen chamber 420 and the methane chamber 220 are arranged in the embodiment, and the diameter, the number, the inlet pressure and the like of the nozzles can be further designed to realize reliable work in a wider mixing ratio, which is beneficial to improving the working condition adaptability of the torch igniter.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (10)
1. A regenerative cooling liquid oxymethane flare igniter, comprising:
An ignition chamber is arranged in the ignition tube, and a methane nozzle is arranged in the ignition tube;
the methane shell is arranged outside the ignition tube, is provided with a liquid methane inlet, and is enclosed with the ignition tube to form a methane cavity, the liquid methane inlet is communicated with the methane cavity, and the methane cavity is communicated with the ignition chamber through the methane nozzle; and
And the regenerative cooling assembly is arranged in the methane cavity and is arranged at the peripheral wall of the ignition tube, a regenerative cooling channel is formed, and the regenerative cooling assembly and the methane nozzle are arranged at intervals.
2. The regenerative cooling liquid oxygen methane torch igniter of claim 1 wherein the regenerative cooling assembly is disposed circumferentially of the squib and the regenerative cooling channel is disposed axially of the squib.
3. A regenerative cooling liquid oxygen methane torch igniter as defined in claim 2 wherein said regenerative cooling assembly is provided in the form of regenerative cooling ribs or regenerative cooling fins, said regenerative cooling ribs or said regenerative cooling fins being provided along the axial direction of said squib, a plurality of said regenerative cooling ribs or said regenerative cooling fins being arranged at intervals along the circumferential direction of said squib, adjacent two of said regenerative cooling ribs or said regenerative cooling fins enclosing said regenerative cooling channel.
4. The regenerative cooling liquid oxygen methane torch igniter of claim 2 wherein the regenerative cooling channels are arranged in a linear or spiral configuration and the regenerative cooling channels are arranged in a rectangular, triangular or trapezoidal configuration in cross section.
5. A regenerative cooling liquid oxygen methane torch igniter as defined in any one of claims 2-4 wherein said regenerative cooling assembly comprises a first assembly and a second assembly, said first assembly and said second assembly being spaced apart at an outer peripheral wall of said squib, said first assembly, said second assembly and said squib enclosing to form a first annulus, said methane nozzle being disposed in said squib in a region opposite said first annulus.
6. The regenerative cooling liquid oxygen methane torch igniter of claim 5 wherein the regenerative cooling assembly further comprises a third assembly, the first assembly, the second assembly, and the third assembly being sequentially spaced apart, the second assembly, the third assembly, and the squib enclosing to form a second annulus, the second annulus being disposed between the liquid methane inlet and the first annulus.
7. The regenerative cooling liquid oxygen methane torch igniter of claim 6 wherein the squib is provided with at least one row of methane tangential holes in a region opposite the second annulus, each row of methane tangential holes comprising at least two methane tangential holes arranged at intervals along the circumference of the squib, the methane tangential holes being arranged tangentially along the inner edge of the squib to form a rotating liquid film on the inner wall of the squib.
8. The regenerative cooling liquid oxygen methane torch igniter of claim 1 wherein the squib is further provided with an oxygen nozzle, the regenerative cooling liquid oxygen methane torch igniter further comprising:
The oxygen shell is arranged outside the ignition tube, a liquid oxygen inlet is formed in the oxygen shell, the oxygen shell and the ignition tube are enclosed to form an oxygen cavity, the liquid oxygen inlet is communicated with the oxygen cavity, and the oxygen cavity is communicated with the ignition chamber through the oxygen nozzle.
9. The regenerative cooling liquid oxygen methane torch igniter of claim 8 further comprising a spark plug and a downstream combustion device, the spark plug and the downstream combustion device being threadably mounted at each end of the squib.
10. The regenerative cooling liquid oxygen methane torch igniter of claim 9, wherein the ignitron is provided with n oxygen nozzles which are uniformly distributed along the circumferential direction at intervals, n is a positive integer not less than 2, the included angle between the axis of the oxygen nozzle and the axis of the ignitron is set at an acute angle, and the axes of the n oxygen nozzles and the axis of the ignitron intersect at a first point;
The ignition tube is provided with m methane nozzles which are uniformly distributed along the circumferential direction at intervals, m is a positive integer which is not less than 2, the included angle between the axis of the methane nozzle and the axis of the ignition tube is an acute angle, and the m methane nozzles and the axis of the ignition tube intersect at a second point;
The end face of the spark plug rod of the spark plug is separated from the first point by a first distance, the first point is separated from the second point by a second distance, the axis of the oxygen nozzle forms a first included angle with the axis of the spark plug, and the methane nozzle forms a second included angle with the axis of the spark plug.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210014767.4A CN114151234B (en) | 2022-01-07 | 2022-01-07 | Regenerated cooling liquid oxygen methane torch igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210014767.4A CN114151234B (en) | 2022-01-07 | 2022-01-07 | Regenerated cooling liquid oxygen methane torch igniter |
Publications (2)
| Publication Number | Publication Date |
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| CN114151234A CN114151234A (en) | 2022-03-08 |
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| CN115289497A (en) * | 2022-09-22 | 2022-11-04 | 中国空气动力研究与发展中心空天技术研究所 | Pneumatic resonance ignition device for combustion heater |
| CN119267037A (en) * | 2024-09-02 | 2025-01-07 | 九州云箭(北京)空间科技有限公司 | Open cycle liquid rocket engine thrust chamber torch low pressure ignition device and method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109386400A (en) * | 2018-12-07 | 2019-02-26 | 上海空间推进研究所 | A kind of laser torch lighter for liquid oxygen/methane engine |
| CN110513719A (en) * | 2019-08-12 | 2019-11-29 | 西安航天动力研究所 | A gas oxygen/gas methane torch igniter |
| CN110552815A (en) * | 2019-08-20 | 2019-12-10 | 西安航天动力研究所 | torch type electric igniter for oxygen/kerosene rich combustion |
| CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN112240570A (en) * | 2020-10-20 | 2021-01-19 | 西安航天动力研究所 | Swirl torch igniter based on 3D printing forming |
| CN216518321U (en) * | 2022-01-07 | 2022-05-13 | 航天科工火箭技术有限公司 | Regenerative cooling liquid oxygen-methane torch igniter |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8161725B2 (en) * | 2008-09-22 | 2012-04-24 | Pratt & Whitney Rocketdyne, Inc. | Compact cyclone combustion torch igniter |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109386400A (en) * | 2018-12-07 | 2019-02-26 | 上海空间推进研究所 | A kind of laser torch lighter for liquid oxygen/methane engine |
| CN110513719A (en) * | 2019-08-12 | 2019-11-29 | 西安航天动力研究所 | A gas oxygen/gas methane torch igniter |
| CN110552815A (en) * | 2019-08-20 | 2019-12-10 | 西安航天动力研究所 | torch type electric igniter for oxygen/kerosene rich combustion |
| CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN112240570A (en) * | 2020-10-20 | 2021-01-19 | 西安航天动力研究所 | Swirl torch igniter based on 3D printing forming |
| CN216518321U (en) * | 2022-01-07 | 2022-05-13 | 航天科工火箭技术有限公司 | Regenerative cooling liquid oxygen-methane torch igniter |
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