CN114576038B - Anti-channeling plug type injector for horizontal ground test run engine and anti-channeling method thereof - Google Patents
Anti-channeling plug type injector for horizontal ground test run engine and anti-channeling method thereof Download PDFInfo
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- CN114576038B CN114576038B CN202210478670.9A CN202210478670A CN114576038B CN 114576038 B CN114576038 B CN 114576038B CN 202210478670 A CN202210478670 A CN 202210478670A CN 114576038 B CN114576038 B CN 114576038B
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- 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
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- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention provides a anti-channeling plug injector for a horizontal ground test engine and an anti-channeling method thereof, which solve the problems that residues of oxidant and fuel are easy to generate a dripping channeling cavity when a plug injector is used for horizontal test, and the channeling cavity is detonated to cause a pressure peak when the plug injector is restarted. The injector comprises a central cylinder, a central rod, an outer shell and a circumferential groove, wherein the central rod is arranged in the central cylinder and forms a plurality of radial injection channels with the front end surface of the central cylinder; the annular groove arranged on the central cylinder collects the propellant and leaves the bolt type injector under the action of gravity, so that the problem of pressure peak caused by cavity channeling deflagration existing in the horizontal test run for multiple starting is effectively solved.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engine injectors, and particularly relates to a anti-channeling plug injector for a horizontal ground test run engine and an anti-channeling method thereof.
Background
The typical bolt injector used in liquid rocket engines has unique geometric and flow field characteristics and is widely used compared with the conventional injector using typical impact or coaxial nozzles. The central injection component of the bolt type injector protrudes out of the end face of the injector outer shell and is arranged in the return flow field of the combustion chamber. Currently, the central injector assembly of most of the pin injectors uses central channel flow and slotted injection of oxidant, while the outer channel formed between the central injector assembly and the outer casing surrounds the injected fuel.
During ground test, most engines are horizontally arranged, when the engines are started, in order to create a good working environment of a central injection assembly, the starting time sequence requires that an oxidant leads a fuel path to complete filling, and the gas-liquid combustion state in the starting process is weakened, so that on one hand, the flame front is far away from an injector, and the heat load is reduced; on the other hand, the liquid oxidant flows in advance to carry out active cooling, so that the structural heat load of the central injection assembly is further reduced. However, the time difference is too long, and the initial oxidant is attached to the outer surface of the central cylinder after passing through the central channel (oxidant cavity) and the slotted hole of the central cylinder and is easy to drip into the fuel cavity (outer ring channel cavity).
When the fuel injector is shut down, the oxidant is higher in saturated vapor pressure, smaller in the containing cavity and fast in emptying of the oxidant cavity, so that a little residue exists in the fuel cavity and is discharged out of order, combustion occurs near the center, the flame surface of the residual fire adheres to or is close to the central injection assembly, and the thermal environment of the central injection assembly is deteriorated. In addition, fuel may blow into the oxidizer cavity, causing a pressure spike caused by the oxidizer cavity knocking at restart. And when the oxidant is later than the fuel shutdown, the residual oxidant attached to the surface of the central cylinder can also drip into the fuel cavity, so that the fuel cavity is detonated to cause a pressure peak when the fuel is restarted.
Disclosure of Invention
The invention provides a cross-flow prevention bolt injector for a horizontal ground test engine and a cross-flow prevention method thereof, aiming at solving the technical problems that residues of oxidant and fuel are easy to generate a dripping cross-flow cavity during horizontal test of the existing bolt injector, and the cross-flow cavity is detonated during restarting to cause a pressure peak.
In order to realize the purpose, the technical scheme provided by the invention is as follows:
the utility model provides a level ground is anti-channeling plug formula insufflator for test run engine, includes a center section of thick bamboo, sets up in a center section of thick bamboo and center section of thick bamboo front end face between form a plurality of radial central poles of spouting passageway to and the cover is established in a center section of thick bamboo outside and front end face and center section of thick bamboo between form the shell body of outer lane passageway circumferential weld, its characterized in that:
the outer diameter of the central cylinder positioned at the rear side of the circumferential groove is larger than that of the central cylinder positioned at the front side of the circumferential groove.
Furthermore, the outer diameter of the central cylinder positioned at the rear side of the circumferential groove is D1, the height difference of two ends of the circumferential groove is H, the groove depth of one end, close to the circumferential seam of the outer ring channel, of the circumferential groove is H, the width of the circumferential groove is B, the distance between one end, close to the circumferential seam of the outer ring channel, of the circumferential groove and the circumferential seam nozzle of the outer ring channel is L, and the distance between the circumferential seam nozzle of the outer ring channel and the nozzle of the radial injection channel is L1; d1, H, H, B, L and L1 satisfy the following conditional expressions:
h=（1%~4%）D1，H=（2%~4%）D1，B=(1.4～1.8）H；
L=（1/2~4/5）L1。
further, H =2% D1, H =3.4% D1, B = (1.5 ~ 1.6) H;
l is 7 mm-12 mm.
Further, if D1 ≦ 35 mm, H =0.7 mm, H =1.2mm, B =2 mm;
if D1 is more than 35 mm and less than or equal to 60 mm, H =1.2mm, H =2mm, B =3.2 mm;
if 60 mm < D1 ≦ 100 mm, H =2mm, H =3 mm, B =4.5 mm.
Furthermore, the central rod comprises a connecting rod and an end cover, the connecting rod is coaxially arranged in the central cylinder, and the end cover is arranged at the front end of the connecting rod and is abutted against the front end face of the central cylinder;
the radial injection channel is a radial through hole formed in the front end of the central cylinder.
Meanwhile, the invention also provides a flow channeling preventing method based on the flow channeling preventing bolt type injector for the horizontal ground test run engine, which is characterized by comprising the following steps of:
before the engine is started, when the first propellant filled into the central cylinder in advance flows out of the radial jetting channel and flows towards the annular seam of the outer ring channel, the first propellant is collected by the annular groove arranged on the central cylinder and leaves the bolt type injector under the action of gravity, so that the first propellant is prevented from flowing into the cavity of the outer ring channel;
after the engine is shut down, when the residual second propellant in the outer ring channel cavity flows out of the outer ring channel circumferential seam and flows towards the radial jetting channel, the residual second propellant is collected by the circumferential groove arranged on the central cylinder and leaves the bolt type injector under the action of gravity, and the residual second propellant is prevented from entering the central cylinder.
Compared with the prior art, the invention has the advantages that:
1. according to the bolt type injector, the annular groove located between the annular seam of the outer ring channel and the radial injection channel is formed in the outer wall of the central cylinder, when a first propellant in the central cylinder flows out of the radial injection channel and flows out of the annular seam of the outer ring channel, and when a second propellant remaining in the cavity of the outer ring channel flows out of the annular seam of the outer ring channel and flows out of the annular seam of the radial injection channel, the annular groove formed in the central cylinder collects the propellant and leaves the bolt type injector under the action of gravity, the problem of pressure peaks caused by cavity channeling explosion when the bolt type injector is started for multiple times in horizontal test run is effectively solved, the use risk is reduced, and the structural reliability is improved.
2. Compared with the existing blow-off and anti-channeling mode, the bolt type injector does not need to be provided with a blow-off air source and a blow-off program, and an engine system and a starting and shutdown mode are simpler.
Drawings
FIG. 1 is a schematic structural diagram of a first embodiment of a cross-flow prevention bolt injector for a horizontal ground test run engine according to the present invention;
FIG. 2 is a schematic structural diagram of a central cylinder according to a first embodiment of the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at I;
FIG. 4 is a schematic structural diagram of a radial injection channel in a second embodiment of the anti-channeling plug injector for a horizontal ground test run engine according to the present invention (without an outer casing, a part of a central cylinder and a central rod are shown);
FIG. 5 is a schematic view of a first configuration of an injector block set according to a second embodiment of the present invention;
FIG. 6 is a schematic representation of a second configuration of an injector block set according to a second embodiment of the present invention;
FIG. 7 is a schematic diagram illustrating a second embodiment of the invention showing the deployment of the spray beam after impact of a propellant in the form of a second set of injection channels;
wherein the reference numbers are as follows:
1-central cylinder, 11-circumferential groove, 12-injection groove group, 121-injection groove, 13-supporting bump, 14-injection circumferential seam, 141-seam one, 142-seam two;
2-center rod, 21-connecting rod, 22-end cap;
3-an outer shell;
41-central channel, 42-radial injection channel, 43-outer ring channel cavity and 44-outer ring channel circumferential seam.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
Example one
As shown in fig. 1 to 3, the anti-channeling plug injector for the horizontal ground test engine comprises a central barrel 1, a central rod 2 and an outer shell 3, wherein one end of the central rod 2 is coaxially arranged in the central barrel 1, the other end of the central rod is arranged on the front end surface of the central barrel 1, a central propellant flow channel is formed between the central rod 2 and the central barrel 1, and the central propellant (first propellant) flow channel comprises a central channel 41 positioned in the inner cavity of the central barrel 1 and a plurality of radial injection channels 42 communicated with the central channel 41; the outer shell 3 is sleeved on the outer side of the central cylinder 1, an outer ring propellant flow channel is formed between the outer shell 3 and the central cylinder 1, and the outer ring propellant (second propellant) flow channel comprises an outer ring channel cavity 43 located in the middle of the outer shell 3 and the central cylinder 1 and an outer ring channel annular seam 44 located between the inner wall of the front end part of the outer shell 3 and the outer wall of the central cylinder 1 and communicated with the outer ring channel cavity 43. Aiming at the problem that the safety of the bolt type injector is outstanding when the existing horizontal test run state is started for multiple times, and mainly aiming at the problem of propellant channeling deflagration, on the basis of the existing bolt type injector, the circumferential groove 11 positioned between the outer ring channel circumferential seam 44 and the radial injection channel 42 is arranged on the outer wall of the central cylinder 1, and the circumferential groove 11 is arranged on the central cylinder 1, so that the problems of channeling deflagration and pressure peaks existing when the bolt type injector is started for multiple times are effectively solved, the use risk is reduced, and the structural reliability is improved.
In the embodiment, the central rod 2 comprises a connecting rod 21 and an end cover 22, the connecting rod 21 is coaxially arranged in the central cylinder 1, and the end cover 22 is arranged at the front end of the connecting rod 21 and is abutted against the front end surface of the central cylinder 1; the radial injection channel 42 is a radial through hole opened at the front end of the central barrel 1.
The circumferential groove 11 is dimensioned as follows:
the circumferential groove 11 is designed to have a radial step, that is, the outer diameter of the central cylinder 1 positioned at the rear side (close to the circumferential seam 44 of the outer ring channel) of the circumferential groove 11 is larger than the outer diameter of the central cylinder 1 positioned at the front side (close to the radial injection channel 42) of the circumferential groove 11, and the height difference of two ends of the circumferential groove 11 is h, that is, the height of the radial step of the circumferential groove 11 is h; the outer diameter of the central cylinder 1 positioned at the rear side of the circumferential groove 11 is D1, the groove depth of one end, close to the outer ring channel circumferential seam 44, of the circumferential groove 11 is H, the width of the circumferential groove 11 is B, the distance between one end, close to the outer ring channel circumferential seam 44, of the circumferential groove 11 and the nozzle of the outer ring channel circumferential seam 44 is L, and the distance between the nozzle of the outer ring channel circumferential seam 44 and the nozzle of the radial injection channel 42 is L1;
when the step height h is designed, the trickle propellants are not suitable to be contacted, and the two propellants impact in a space area impacting the step during working, so that the jet flow is broken and atomized, a good three-dimensional space distribution spray field is formed, and the combustion efficiency is improved by 2 percent. When no step exists, the impact occurs on the jet orifice of the radial jetting channel 42, the phenomenon of streaming of the propellant at the outer ring can exist, and the contact mixing of the two propellants is reduced;
the distance L between one end of the circumferential groove 11 close to the outer ring channel circumferential seam 44 and the nozzle of the outer ring channel circumferential seam 44 is moderate, and is not suitable to be too small or too large, the too small end can not effectively retain the residual propellant of the outer ring, and is not beneficial to the heat transfer and evaporation of the liquid film in work, and the too large end can lead the heat transfer and evaporation of the liquid film of the outer ring to be too strong, and the uniformity and the stability are poor;
d1, H, B, L and L1 satisfy the following conditional expressions:
h = (1% -4%) D1, H = (2% -4%) D1, B = (1.4% -1.8) H; preferably, H =2% D1, H =3.4% D1, B = (1.5-1.6) H;
l = (1/2-4/5) L1, preferably, L is 7-12 mm, L1 is 12-15 mm.
Generally, if D1 ≦ 35 mm, H is 0.5 to 0.7mm, preferably H =0.7 mm, H =1.2mm, B =2 mm;
if 35 mm < D1 ≦ 60 mm, preferably H =1.2mm, H =2mm, B =3.2 mm;
if 60 mm < D1 ≦ 100 mm, it is preferred that H =2mm, H =3 mm, B =4.5 mm.
Preferably, two ends of the circumferential groove 11 are in arc transition connection with the outer wall of the central cylinder 1, as shown in a position a in fig. 3, so that the outer ring flow is ensured to keep a complete liquid film form during operation.
In the multiple starting method of the anti-channeling plug type injector, a groove with certain depth and width is processed on the outer wall of the central cylinder 1 at the position between the spout of the outer ring channel annular seam 44 and the spout of the radial injection channel 42; before the engine is started, when the first propellant (oxidizer) filled into the central barrel 1 in advance flows out of the radial injection channel 42 and flows towards the annular seam 44 of the outer ring channel, the first propellant (oxidizer) is collected by the annular groove 11 arranged on the central barrel 1 and leaves the bolt type injector under the action of gravity to avoid flowing into the outer ring channel cavity 43, so that the annular groove 11 prevents a little oxidizer in the first propellant (oxidizer) filling in advance from attaching to the outer edge and flowing into the outer ring channel cavity 43;
after the engine is shut down, a little residual second propellant (fuel cavity) in the outer ring channel 43 flows out of the outer ring channel annular seam 44 and flows towards the radial injection channel 42, and is collected by the annular groove 11 arranged on the central barrel 1 and leaves the bolt injector under the action of gravity to avoid entering the central barrel 1, so that the annular groove 11 prevents a little residual propellant (fuel cavity) in the outer ring channel annular seam 44 from flowing into the radial injection channel 42 close to the central barrel 1.
Regarding the anti-channeling method of the injector, considering the direction of the structural schematic diagram shown in fig. 1, the first propellant and the second propellant flow adherently on the outer wall of the central barrel 1, the doses of the first propellant and the second propellant are both small, and are collected when flowing adherently to the circumferential groove 11, and when the doses of the first propellant or the second propellant are collected to a certain amount, they will fall under the action of gravity to avoid entering the outer ring channel cavity 43 or the central channel 41.
In addition, when the central channel 41 of the central cylinder 1 is excessively remained, the first propellant (oxidizer) is discharged through the radial injection channel 42 and then attached to the outer surface of the central cylinder 1, and drops to the circumferential groove 11 under the action of gravity, so that the first propellant (oxidizer) is prevented from flowing into the outer ring channel cavity 43; the problem of pressure peak caused by deflagration occurring in the inner cavity (oxidant cavity) of the central cylinder 1 or the outer ring channel cavity 43 (fuel cavity) is effectively solved.
The bolt type injector eliminates the problem of detonation pressure peak caused by propellant channeling during starting or after shutdown, is suitable for a horizontal ground trial run bolt type injector engine, and can realize a reliable target of repeated starting; compared with the existing blow-off anti-channeling cavity mode, the blow-off air source and the blow-off program are not needed to be arranged, and the engine system and the starting and shutdown process are simpler.
Example two
The difference from the first embodiment is that: as shown in fig. 4, the front end surface of the central barrel 1 of the present embodiment is provided with a plurality of circumferentially arranged supporting protrusions 13 and a plurality of circumferentially arranged injection groove sets 12; the supporting projections 13 and the injection groove groups 12 are arranged in a staggered manner along the circumferential direction, preferably, the supporting projections 13 are uniformly distributed along the circumferential direction of the central cylinder 1, and the injection groove groups 12 are also uniformly distributed along the circumferential direction of the central cylinder 1. The central rod 2 comprises a connecting rod 21 and an end cover 22, the connecting rod 21 is coaxially arranged in the central cylinder 1, a distance exists between the connecting rod 21 and the end cover 22 to form a central channel 41, the end cover 22 is arranged at the front end of the connecting rod 21, the supporting lugs 13 are in contact with the end cover 22, and an injection annular seam 14 is formed between the front end surface of the central cylinder 1, the end cover 22 and every two adjacent supporting lugs 13; the injection groove group 12 comprises at least one injection groove 121 which radially penetrates through the side wall of the front end surface of the central cylinder 1 and is communicated with the injection annular seam 14; the injection annular slot 14 and the injection slots 121 running through it serve as radial injection channels 42 communicating with the central channel 41.
The machining process of the center tube 1 in the embodiment is as follows: firstly, designing and processing a discontinuous circumferential seam structure on the front end surface of the central cylinder 1 along the circumferential direction, then designing and processing an injection groove 121 on the bottom surface of the circumferential seam structure, and forming the supporting bump 13 between the circumferential seam structure and the circumferential seam structure at the end of the central cylinder 1; the end surface of the end cover 22 is attached to the end surface of the supporting bump 13 of the central barrel 1 to form an injection structure of the injection groove 121 and the injection circular seam 14; the number of the supporting protrusions 13 and the number of the injection slots 121 of each injection slot group 12 are designed according to specific requirements. The section of the injection groove 121 in the embodiment is half of a track shape; in other embodiments, the cross-sectional shape of the injection groove 121 may be designed to be circular or triangular according to actual needs.
The present embodiment shows two structural forms of the injection groove set 12:
first, as shown in FIG. 5, the set of injection slots 12 includes 2 injection slots 121, all of the injection circumferential slots 14 being of equal height.
Secondly, as shown in fig. 6, the injection groove group 12 comprises 2 injection grooves 121, and preferably, the injection annular gap 14 between the 2 injection grooves 121 is greater than the injection annular gaps 14 at the rest positions, and in the embodiment, two kinds of gaps with different heights are designed, that is, the injection annular gap 14 between the 2 injection grooves 121 is a first gap 141, the injection annular gap 14 at the rest positions is a second gap 142, and the height of the first gap 141 is greater than that of the second gap 142, so that, due to the large area of the first gap 141, when the central rod 2 is slightly deformed during operation, the injection area is not sufficiently affected, and therefore, the height of the first gap 141 is designed to be relatively high, and injection stability can be ensured under the condition of meeting a large flow rate; in addition, after the first propellant jetted by the jetting structure formed by combining the jetting grooves 121 and the jetting circumferential seams 14 collides with the second propellant on the outer ring (outside the circumference of the central barrel 1), a mist beam spreading mode shown in fig. 7 is formed, wherein in the drawing, a, b, c and d are mist beams at the supporting bumps, a gap two 142 collides mist beams, a gap one 141 collides mist beams and a jetting groove 121 collides mist beams, and it can be seen that the jetting structure of the embodiment enriches the distribution gradient of the mist beams and is beneficial to improving the combustion performance.
The above description is only for the purpose of describing preferred embodiments of the present invention and is not intended to limit the technical solutions of the present invention, and any modifications made by those skilled in the art based on the main technical idea of the present invention are within the technical scope of the present invention.
Claims (4)
1. The utility model provides a level ground test run engine is with preventing scurrying stream bolt formula insufflator, includes a center section of thick bamboo (1), a plurality of radial spouting passageway (42), well core rod (2) to and the cover establish shell body (3) that form outer lane passageway circumferential weld (44) between a center section of thick bamboo (1) outside and front end and a center section of thick bamboo (1), its characterized in that:
the central rod (2) comprises a connecting rod (21) and an end cover (22), the connecting rod (21) is coaxially arranged in the central cylinder (1), and the end cover (22) is arranged at the front end of the connecting rod (21) and is abutted against the front end face of the central cylinder (1);
the radial injection channel (42) is a radial through hole formed in the front end of the central cylinder (1);
the outer diameter of the central cylinder (1) positioned at the rear side of the circumferential groove (11) is larger than that of the central cylinder (1) positioned at the front side of the circumferential groove (11);
the outer diameter of a central cylinder (1) positioned at the rear side of a circumferential groove (11) is D1, the height difference of two ends of the circumferential groove (11) is H, the groove depth of one end, close to an outer ring channel circumferential seam (44), of the circumferential groove (11) is H, the width of the circumferential groove (11) is B, the distance between one end, close to the outer ring channel circumferential seam (44), of the circumferential groove (11) and a nozzle of the outer ring channel circumferential seam (44) is L, and the distance between the nozzle of the outer ring channel circumferential seam (44) and a nozzle of a radial injection channel (42) is L1; d1, H, H, B, L and L1 satisfy the following conditional expressions:
h=（1%~4%）D1，H=（2%~4%）D1，B=(1.4～1.8）H；
L=（1/2~4/5）L1。
2. the anti-channeling plug-type injector for the horizontal ground test engine according to claim 1, characterized in that: h =2% D1, H =3.4% D1, B = (1.5 ~ 1.6) H;
l is 7 mm-12 mm.
3. The anti-channeling bolt injector for the horizontal ground test engine according to claim 1, characterized in that:
if D1 is less than or equal to 35 mm, H =0.7 mm, H =1.2mm, B =2 mm;
if D1 is more than 35 mm and less than or equal to 60 mm, H =1.2mm, H =2mm, B =3.2 mm;
if 60 mm < D1 ≦ 100 mm, H =2mm, H =3 mm, B =4.5 mm.
4. A method for preventing a cross flow of a cross flow prevention bolt type injector for a horizontal ground test run engine according to any one of claims 1 to 3, comprising:
before the engine is started, when a first propellant filled into the central cylinder (1) in advance flows out of the radial jetting channel (42) and flows towards an outer ring channel annular seam (44), the first propellant is collected by an annular groove (11) arranged on the central cylinder (1) and leaves the bolt type jetting device under the action of gravity, and the first propellant is prevented from flowing into an outer ring channel cavity (43);
after the engine is shut down, when the residual second propellant in the outer ring channel cavity (43) flows out of the outer ring channel annular seam (44) and flows towards the radial injection channel (42), the residual second propellant is collected by the annular groove (11) arranged on the central cylinder (1) and leaves the bolt type injector under the action of gravity, so that the residual second propellant is prevented from entering the central cylinder (1).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210478670.9A CN114576038B (en) | 2022-05-05 | 2022-05-05 | Anti-channeling plug type injector for horizontal ground test run engine and anti-channeling method thereof |
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| CN202210478670.9A CN114576038B (en) | 2022-05-05 | 2022-05-05 | Anti-channeling plug type injector for horizontal ground test run engine and anti-channeling method thereof |
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| CN114576038B true CN114576038B (en) | 2022-08-16 |
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|---|---|---|---|---|
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| CN114427505A (en) * | 2022-04-07 | 2022-05-03 | 西安航天动力研究所 | Pintle injector and thrust chamber |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3508712A (en) * | 1966-10-04 | 1970-04-28 | North American Rockwell | Fluid injector with manifold-forming sealing ring |
| DE102006004265A1 (en) * | 2006-01-31 | 2007-08-09 | Incoe International, Inc. | Heavy-duty seals for injection molding machines |
| EP2757243B1 (en) * | 2013-01-18 | 2015-08-12 | Airbus DS GmbH | Injector element |
| CN104234870B (en) * | 2014-06-13 | 2016-05-18 | 中国航天科技集团公司第六研究院第十一研究所 | The coaxial pintle formula ejector filler thrust chamber of a kind of fluting |
| KR101958278B1 (en) * | 2017-11-21 | 2019-03-14 | 한국항공우주연구원 | Pintle injector for oxidizer rich preburner |
| CN108286478B (en) * | 2017-12-20 | 2019-07-12 | 北京控制工程研究所 | A kind of pre- rotating pintle ejector filler applied to double elements liquid-propellant rocket engine |
| CN112253332B (en) * | 2020-12-22 | 2021-04-06 | 西安空天引擎科技有限公司 | Single variable-push large-ratio pintle type injector |
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2022
- 2022-05-05 CN CN202210478670.9A patent/CN114576038B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| CN114427505A (en) * | 2022-04-07 | 2022-05-03 | 西安航天动力研究所 | Pintle injector and thrust chamber |
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