CN117605593A - Double-flow adjustable rotational flow pintle injector and liquid rocket engine - Google Patents
Double-flow adjustable rotational flow pintle injector and liquid rocket engine Download PDFInfo
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- CN117605593A CN117605593A CN202410001546.2A CN202410001546A CN117605593A CN 117605593 A CN117605593 A CN 117605593A CN 202410001546 A CN202410001546 A CN 202410001546A CN 117605593 A CN117605593 A CN 117605593A
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- 239000003380 propellant Substances 0.000 claims abstract description 156
- 238000002485 combustion reaction Methods 0.000 claims abstract description 42
- 238000005192 partition Methods 0.000 claims abstract description 11
- 239000000758 substrate Substances 0.000 claims abstract description 6
- 230000009977 dual effect Effects 0.000 claims description 18
- 230000005540 biological transmission Effects 0.000 claims description 10
- 238000006243 chemical reaction Methods 0.000 claims description 4
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- 238000009826 distribution Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000005507 spraying Methods 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 3
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- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- XTYUEDCPRIMJNG-UHFFFAOYSA-N copper zirconium Chemical compound [Cu].[Zr] XTYUEDCPRIMJNG-UHFFFAOYSA-N 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
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Classifications
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The application discloses two adjustable whirl pintle injectors of flow and liquid rocket engine relates to liquid rocket technical field, includes: the combustion chamber comprises a combustion chamber substrate, a first cavity, a second cavity and a third cavity; a partition plate for partition is arranged between the first cavity and the second cavity, a second propellant inlet is arranged on the second cavity, and a second propellant outlet is arranged between the second cavity and the third cavity; the pin column section is fixedly connected with the cover plate of the first cavity; a first propellant inlet is formed in one side of the pintle column section extending out of the combustion chamber base body, a plurality of spiral channels are formed in the pintle column section, a plurality of first propellant outlets a are formed in the outer wall of one side of the pintle column section extending into the third cavity in a circumferential direction, and the first propellant is radially sprayed out through the plurality of first propellant outlets a and is fully mixed with the first propellant sprayed out from the second propellant outlet in a straight line; and the adjusting assembly is used for controlling the opening degrees of the first propellant outlet a and the second propellant outlet.
Description
Technical Field
The application belongs to the technical field of liquid rockets, and particularly relates to a double-flow adjustable cyclone pintle injector and a liquid rocket engine.
Background
In a liquid rocket engine, an injector is a device for atomizing and mixing a tissue propellant, and the propellant is efficiently atomized and mixed to generate efficient and stable combustion in a combustion chamber, then the combustion is expanded and accelerated in a spray pipe, and then the spray pipe is ejected out by high-speed jet flow at an outlet of the spray pipe to form power for pushing the rocket to fly. Therefore, the structural quality of the injector directly determines the performance of the rocket engine. The traditional liquid rocket engine injector is generally composed of dozens of hundreds of nozzle units, and the nozzle units are usually centrifugal, direct-current or mutual-impact nozzles and the like, so that the defects of complex structure, high production cost, long manufacturing period and the like are often caused. The pintle injector has the characteristics of simple structure, high reliability, stable combustion, large thrust transformation ratio and the like, has low production cost and short manufacturing period, and avoids the defects of the traditional injector.
In the prior art, the needle bolt injector mainly has the following technical problems to be solved: 1. the inner flow channel propellant is sprayed out along the radial direction, the outer flow channel propellant is sprayed out along the axial direction, the propellant cannot be well diffused, and the spray distribution space range is smaller. Particularly when the flow rate of the outer flow path propellant is large, it is difficult to form a good radial mixing ratio distribution; 2. the traditional pintle only changes the flow of one of the oxidant or the fuel, when the injection areas of the two channels cannot be cooperatively changed, the momentum ratio of the inner propellant and the outer propellant of the engine is changed when the thrust is changed, so that the atomization mixing effect is affected, and the combustion efficiency of the engine is also affected; 3. because the pintle injector extends into the combustion chamber, a significant problem is that the pintle head is eroded by the high temperature gas, which is prone to ablation and thus affects the normal operation of the engine.
Disclosure of Invention
The application provides a double-flow adjustable rotational flow pintle injector and a liquid rocket engine, and aims to solve the technical problems that propellant in the existing pintle injector cannot be well diffused and the propellant flow is inconvenient to adjust to at least a certain extent.
In order to solve the technical problems, the application adopts the following technical scheme:
a first aspect of embodiments of the present application provides a dual flow adjustable swirl pintle injector for providing mixed propellant to a liquid rocket engine, the injector comprising: the combustion chamber comprises a combustion chamber substrate, wherein a first cavity, a second cavity and a third cavity are sequentially arranged in the combustion chamber substrate from one end to the other end; a partition plate for partition is arranged between the first cavity and the second cavity, a second propellant inlet is arranged on the second cavity, a third cavity is a reaction cavity, and a second propellant outlet is arranged between the second cavity and the third cavity; the needle tube is fastened and sequentially passes through the first cavity and the second cavity from the outside of the combustion chamber matrix to enter the third cavity, and the needle bolt column section is fixedly connected with a cover plate of the first cavity; a first propellant inlet is formed in one side of the pintle column section extending out of the combustion chamber base body, a plurality of spiral channels are formed in the pintle column section, a plurality of first propellant outlets a are formed in the outer wall of one side of the pintle column section extending into the third cavity in a circumferential direction, and the first propellant enters the spiral channels from the first propellant inlet, is radially sprayed out in the circumferential direction through the plurality of first propellant outlets a and is fully mixed with the first propellant sprayed out in a straight line from the second propellant outlet; the adjusting component is sleeved on the needle stud section and used for controlling the opening degrees of the first propellant outlet a and the second propellant outlet.
In some embodiments, the pintle column section further includes: the feeding channel is connected with the first propellant inlet, the section of the feeding channel is circular, one end of the feeding channel is communicated with one ends of a plurality of spiral channels through a plurality of radial holes, the other ends of the spiral channels are respectively communicated with the first propellant outlets a, and the first propellant is radially sprayed out from the first propellant outlets a in the circumferential direction after entering the spiral channels.
In some embodiments, the cross-section of the helical channel is rectangular or triangular or trapezoidal.
In some embodiments, the pintle column section further includes: the first propellant outlets b are annularly arranged at the end part of the pin column section extending into one side of the third cavity, the first propellant outlets b are communicated with the spiral channel, the central line of the first propellant outlets b and the central axis of the combustion chamber form a certain jet angle, and partial first propellant enters the jet formed by the first propellant outlets b to strike at a point at a certain distance from the pin column section to form a conical liquid film, so that the end part of the pin column section is cooled and protected.
In some embodiments, the adjustment assembly comprises: the sleeve is movably sleeved on the outer wall of the needle bolt column section, and the opening of the first propellant outlet a is controlled by adjusting the relative position of the sleeve and the needle column of the needle tube; the sleeve is positioned on the outer wall of the second cavity and provided with a bulge part capable of sealing the second propellant outlet, and the sleeve is driven to move on the pintle column section so as to control the opening of the second propellant outlet; and the driving unit is arranged in the first cavity and used for driving the sleeve to move.
In some embodiments, the driving unit includes: a driving motor; the transmission piece is connected with the power output end of the driving motor and used for converting the rotary motion of the driving motor into linear motion; one end of the connecting piece is connected with the transmission piece, and the other end of the connecting piece is connected with the sleeve.
In some embodiments, the second propellant outlet tapers from one side of the second cavity to one side of the third cavity, and when the boss does not completely close the second propellant outlet, the second propellant is ejected from the boss and the inner wall gap of the combustion chamber base, and is thoroughly mixed with the first propellant ejected by the circumferential emission.
In some embodiments, the injector further comprises: the first sealing groove is arranged between the outer wall of the sleeve and the partition plate; the second seal groove is arranged between the inner wall of the protruding part and the pintle column section.
In some embodiments, the vertical cross-section of the boss is circular arc.
A second aspect of the embodiments of the present application provides a liquid rocket engine, where the liquid rocket engine is provided with the dual-flow adjustable cyclone pintle injector.
According to the technical scheme, the application has at least the following advantages and positive effects:
according to the double-flow adjustable cyclone pintle injector, by utilizing the structural advantage of the injector, the spiral channel and the adjusting component are arranged on the pintle column section to form a special geometric flow channel, so that on one hand, the cyclone generated after entering the spiral channel by the first propellant effectively enlarges the spraying range, the cyclone is broken more easily when being impacted with the second propellant, the breaking time and the breaking distance are reduced, and the atomization, the mixing and the combustion are finished in advance, so that the combustion efficiency of an engine is improved.
According to the double-flow adjustable cyclone pintle injector, the opening of the first propellant outlet a and the opening of the second propellant outlet are controlled through the sleeve, when the sleeve axially reciprocates along the combustion chamber, the sleeve shields the spiral channel on the pintle column section to a certain extent, meanwhile, the flow area of a slit formed by the outer molded surface of the sleeve and the inner wall of the combustion chamber also synchronously changes, and the flow of the two propellants is continuously and accurately adjusted.
According to the double-flow adjustable cyclone pintle injector, the first propellant enters jet flow formed by a plurality of first propellant outlets b to strike a point at a certain distance from a pintle section to form a conical liquid film, and the end part of the pintle section is cooled and protected, so that the head part of the pintle section can be effectively protected from being ablated; in addition, the liquid film can be gradually broken, atomized and evaporated to participate in combustion reaction, so that propellant is not wasted and engine performance loss is not caused.
According to the liquid rocket engine, the spiral channel and the adjusting component are arranged on the pintle column section to form a special geometric flow channel, the swirling flow generated by the first propellant after entering the spiral channel effectively enlarges the spraying range, so that the penetrating power of jet flow is enhanced when the second propellant collides with the first propellant, the diffusion mixing process of the two propellants is effectively improved, different flow intensity and mixing ratio distribution in space are formed, and the combustion efficiency is effectively improved; the self structural advantage is utilized to set the adjusting component, and the flow area of the two propellants can be changed simultaneously, so that the thrust is continuously adjustable, and the working range of the liquid rocket engine is widened.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a dual flow adjustable swirl pintle injector in accordance with an embodiment of the present application;
FIG. 2 is a schematic illustration of the configuration of the helical channel of a dual flow adjustable swirl pintle injector in accordance with an embodiment of the present application;
FIG. 3 is a schematic view of a partial construction of a pintle column section of a dual flow adjustable swirl pintle injector in accordance with an embodiment of the present application.
The reference numerals are explained as follows: 100. a combustion chamber base; 110. a first cavity; 111. a cover plate; 120. a second cavity; 121. a second propellant inlet; 122. a second propellant outlet; 130. a third cavity; 200. a pin post section; 210. a first propellant inlet; 220. a spiral channel; 230. a first propellant outlet a; 240. a mounting plate; 250. a buffer area; 260. a feed channel; 261. a radial hole; 270. a first propellant outlet b; 310. a sleeve; 320. a driving motor; 331. a drive cover plate; 332. a traction rod; 410. a first seal groove; 420. and a second seal groove.
Detailed Description
In order to make the present application more clearly understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
Please refer to fig. 1 and 2;
fig. 1 is a schematic structural view of a dual flow rate adjustable swirl pintle injector according to an embodiment of the present application, and fig. 2 is a schematic structural view of a spiral channel of a dual flow rate adjustable swirl pintle injector according to an embodiment of the present application, as shown in fig. 1 and 2, for providing mixed propellant to a liquid rocket engine, the injector comprising: a combustion chamber base body 100, wherein a first cavity 110, a second cavity 120 and a third cavity 130 are sequentially arranged in the combustion chamber base body 100 from one end to the other end; a partition board for partition is arranged between the first cavity 110 and the second cavity 120, a second propellant inlet 121 for injecting a second propellant is arranged on the second cavity 120, a third cavity 130 is a reaction cavity, and a second propellant outlet 122 is arranged between the second cavity 120 and the third cavity 130; a needle bolt column section 200, the needle tube is fastened and sequentially passes through the first cavity 110 and the second cavity 120 from the outside of the combustion chamber base body 100 to enter the third cavity 130, and the needle bolt column section 200 is fixedly connected with the cover plate 111 of the first cavity 110; a first propellant inlet 210 is formed in one side of the pintle column section 200 extending out of the combustion chamber substrate 100, a plurality of spiral channels 220 are formed in the pintle column section 200, a plurality of first propellant outlets a230 are formed in the outer wall of one side of the pintle column section 200 extending into the third cavity 130 in a circumferential direction, and the first propellant enters the spiral channel from the first propellant inlet 210 and is radially sprayed out through the plurality of first propellant outlets a230 in a circumferential direction and is fully mixed with the first propellant sprayed out from the second propellant outlet 122 in a straight line; and the adjusting component is sleeved on the needle bolt column section 200 and is used for controlling the opening degrees of the first propellant outlet a230 and the second propellant outlet 122. By arranging the spiral channel 220 and the adjusting component in the pintle column section 200 to form a special geometric flow channel, the rotational flow generated by the first propellant after entering the spiral channel 220 effectively enlarges the spraying range, so that the penetrating power of jet flow is enhanced when the second propellant collides with the first propellant, the diffusion mixing process of the two propellants is effectively improved, different flow strengths and mixing ratio distribution in space are formed, and the combustion efficiency is effectively improved; the self structural advantage is utilized to set the adjusting component, and the flow area of the two propellants can be changed simultaneously, so that the thrust is continuously adjustable, and the working range of the liquid rocket engine is widened.
In some embodiments, the second propellant inlet 121 is disposed at an upper end of the second chamber 120.
In some embodiments, the end of the pintle column section 200 that extends out of the combustion chamber base 100 is provided with a removable mounting plate 240, and the other end of the pintle column section 200 is a spherical head machined from zirconium copper or other high thermal conductivity material.
In some embodiments, pintle column section 200 further includes: a feed channel 260 in communication with the first propellant inlet 210; the cross section of the feeding channel 260 is circular, the feeding channel 260 is communicated with one ends of a plurality of spiral channels 220 through a plurality of radial holes 261, the other ends of the plurality of spiral channels 220 are respectively communicated with the first propellant outlets a230, after the first propellant enters the spiral channels 220, most of the first propellant is radially sprayed out from the circumference of the first propellant outlet a230, on the other hand, a plurality of cylindrical small holes leading to the spherical head of the pintle at the bottom end of the spiral channels 220 are communicated with the first propellant outlet b270, and a small part of the first propellant is sprayed out from the first propellant outlet b 270.
In this embodiment, a buffer 250 is further disposed between the first propellant inlet 210 and the feed channel 260, and the first propellant enters the feed channel 260 through the buffer.
In some embodiments, the feed channel 260 is provided with a radial hole 261 at its end, and the feed channel 260 communicates with the spiral channel 220 through the radial hole 261.
In some embodiments, the cross-section of the helical channel 220 is rectangular or triangular or trapezoidal.
Specifically, the diameter of the pintle post section 200, the number of radial holes 261, the diameter of the radial holes 261, the number of channels, the pitch, the aspect ratio, and other structural parameters may be set as desired. The aspect ratio and the pitch of the cross section of the channel influence the tangential velocity of the fluid, and the larger the tangential velocity is, the stronger the centrifugal effect is, and the optimization is pending through calculation.
Referring to FIG. 3, FIG. 3 is a schematic view of a portion of a pintle column section 200 of a dual flow adjustable swirl pintle injector according to an embodiment of the present application;
in some embodiments, pintle column section 200 further includes: the first propellant outlets b270 are annularly arranged at the end part of the needle pillar section 200 extending into one side of the third cavity 130, the first propellant outlets b270 are communicated with the spiral channel 220, the central line of the first propellant outlets b270 and the central line of the combustion chamber form a certain jet angle, and partial first propellant enters the jet formed by the first propellant outlets b270 to strike a point at a certain distance from the needle pillar section 200 to form a conical liquid film so as to cool and protect the end part of the needle pillar section 200.
Specifically, the first propellant outlet b270 is arranged on the spherical head, so that high-temperature fuel gas can be prevented from flowing to the spherical head to a certain extent, and the spherical head can be effectively protected from being ablated; on the other hand, the liquid film can be gradually broken, atomized and evaporated to participate in the combustion reaction, so that the propellant is not wasted and the performance loss of the engine is not caused.
Specifically, the number of cooling holes and the jet angle of the first propellant outlet b270 can be optimally designed by test or simulation means.
Referring to fig. 1, in some embodiments, the adjustment assembly includes: the sleeve 310 is movably sleeved on the outer wall of the needle stud section 200, and the opening of the first propellant outlet a230 is controlled by adjusting the relative position of the sleeve 310 and the needle stud of the needle tube; the sleeve 310 is provided with a protruding part on the outer wall of the second cavity 120, which can seal the second propellant outlet 122, and the protruding part can be driven to open or close the second propellant outlet 122 by driving the sleeve 310; the driving unit is installed in the first cavity 110 and is used for driving the sleeve 310 to move.
Specifically, the sleeve 310 can realize axial reciprocating motion by arranging the driving unit, and the flow of the internal and external propellant can be continuously regulated, so that the thrust can be continuously regulated, and the working range of the liquid rocket engine is improved. The invention is mainly suitable for a liquid rocket engine with a double-component propellant, if the liquid rocket engine is a non-spontaneous combustion propellant, an igniter is also required to be arranged at the position of a combustion chamber matrix close to the head of a pintle, and under the action of the igniter, the two propellants are subjected to chemical reaction to generate high-temperature high-pressure fuel gas. Since the atomization effect is also greatly related to the momentum ratio of the propellants ejected from the inner and outer channels, the flow areas of the two propellants are synchronously changed when the sleeve 310 moves, i.e., the momentums of the two propellants are synchronously changed, so that the momentum ratio can be always kept in the optimal state during the thrust change.
In some embodiments, the driving unit includes: a driving motor 320; the transmission piece is connected with the power output end of the driving motor 320 and is used for converting the rotary motion of the driving motor 320 into linear motion; and one end of the connecting piece is connected with the transmission piece, and the other end of the connecting piece is connected with the sleeve 310.
In some embodiments, the transmission may be a worm drive or a ball screw drive or a gear drive or a crank link mechanism or a compression spring mechanism.
In other embodiments, the driving unit may also be a driving cylinder or a driving hydraulic cylinder.
In some embodiments, the connector comprises: the transmission cover plate 331 is connected with the transmission piece; at least 2 traction rods 332, one end of the sleeve 310, which is close to the first cavity 110, is provided with an annular driving part, and the transmission cover plate 331 is connected with the driving part through the traction rods 332.
In some embodiments, the second propellant outlet 122 tapers from one side of the second cavity 120 to one side of the third cavity 130, and when the boss does not completely close the second propellant outlet 122, the second propellant is ejected from the gap between the boss and the inner wall of the second propellant outlet 122, and is thoroughly mixed with the circumferentially emitted first propellant.
In some embodiments, the vertical cross-section of the boss is circular arc shaped to better fit the second propellant outlet 122.
Referring to fig. 1, in some embodiments, the injector further comprises: a first seal groove 410 disposed between the outer wall of the sleeve 310 and the partition; a second seal groove 420 is disposed between the boss inner wall and pintle column section 200.
Specifically, the first seal groove 410 and the second seal groove 420 are used to prevent propellant media from flowing through the cavity. The first seal groove 410 is provided with a sliding seal ring to prevent the first propellant from leaking to the outside of the sleeve 310, and the first propellant can only enter the spiral channel 220 from the radial hole 261 and then be ejected; a sliding seal ring is also installed in the second seal groove 420 to prevent the second propellant from leaking to the inside of the first chamber 110 or the sleeve 310, and the second propellant can only be ejected from the slit to the combustion chamber along the outside of the sleeve 310.
A second aspect of embodiments of the present application provides a liquid rocket engine on which a dual flow adjustable swirl pintle injector is disposed. By arranging the spiral channel 220 and the adjusting component in the pintle column section 200 to form a special geometric flow channel, the rotational flow generated by the first propellant after entering the spiral channel 220 effectively enlarges the spraying range, so that the penetrating power of jet flow is enhanced when the second propellant collides with the first propellant, the diffusion mixing process of the two propellants is effectively improved, different flow strengths and mixing ratio distribution in space are formed, and the combustion efficiency is effectively improved; the self structural advantage is utilized to set the adjusting component, and the flow area of the two propellants can be changed simultaneously, so that the thrust is continuously adjustable, and the working range of the liquid rocket engine is widened.
In this application, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, and may also include the first and second features not being in direct contact but being in contact with each other by way of additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise" indicate or positional relationships are based on the positional relationships shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present application.
In the present application, unless explicitly specified and limited otherwise, the terms "coupled," "secured," and the like are to be construed broadly, and for example, "secured" may be either permanently attached or removably attached, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
In addition, descriptions such as those related to "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated in this application. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more features. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
While embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the application, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. A dual flow adjustable swirl pintle injector for providing mixed propellant to a liquid rocket engine, the dual flow adjustable swirl pintle injector comprising:
the combustion chamber comprises a combustion chamber substrate, wherein a first cavity, a second cavity and a third cavity are sequentially arranged in the combustion chamber substrate from one end to the other end; a partition plate for partition is arranged between the first cavity and the second cavity, a second propellant inlet is arranged on the second cavity, a third cavity is a reaction cavity, and a second propellant outlet is arranged between the second cavity and the third cavity;
the needle bolt column section sequentially passes through the first cavity and the second cavity from the outside of the combustion chamber matrix and enters the third cavity, and the needle bolt column section is fixedly connected with a cover plate of the first cavity;
a first propellant inlet is formed in one side of the pintle column section extending out of the combustion chamber base body, a plurality of spiral channels are formed in the pintle column section, a plurality of first propellant outlets a are formed in the outer wall of one side of the pintle column section extending into the third cavity in a circumferential direction, and the first propellant is radially sprayed out of the first propellant outlets a in a circumferential direction and is fully mixed with the first propellant sprayed out of the second propellant outlets in a straight line;
the adjusting component is sleeved on the needle stud section and is used for controlling the opening degrees of the first propellant outlet a and the second propellant outlet.
2. The dual flow adjustable swirl pintle injector of claim 1, wherein the pintle column section further comprises:
the feeding channel is connected with the first propellant inlet, the section of the feeding channel is circular, the circular channel is communicated with one ends of a plurality of spiral channels through a plurality of radial holes, the other ends of the plurality of spiral channels are respectively communicated with each first propellant outlet a, and the first propellant is radially sprayed out from the first propellant outlet a in the circumferential direction after entering the spiral channels.
3. The dual flow adjustable swirl pintle injector of claim 1 wherein the cross section of the helical channel is rectangular or triangular or trapezoidal.
4. The dual flow adjustable swirl pintle injector of claim 2, wherein the pintle column section further comprises:
the multiple first propellant outlets b are annularly arranged at the end part of the pintle column section extending into one side of the third cavity, the first propellant outlets b are communicated with the spiral channel, the central line of each first propellant outlet b is at a certain jet angle with the central axis of the combustion chamber, part of the first propellant enters the multiple first propellant outlets b to form jet flow which is impacted at a certain distance from the pintle column section to form a conical liquid film, and the end part of the pintle column section is cooled and protected.
5. The dual flow adjustable swirl pintle injector of claim 1, wherein the adjustment assembly comprises:
the sleeve is movably sleeved on the outer wall of the needle bolt column section, and the opening of the first propellant outlet a is controlled by adjusting the relative position of the sleeve and the needle bolt column section; the sleeve is positioned on the outer wall of the second cavity, and is provided with a bulge part capable of sealing the second propellant outlet, and the sleeve is driven to move on the pintle column section so as to control the opening of the second propellant outlet;
and the driving unit is arranged in the first cavity and used for driving the sleeve to move.
6. The dual flow adjustable swirl pintle injector of claim 5, wherein the drive unit comprises:
a driving motor;
the transmission piece is connected with the power output end of the driving motor and used for converting the rotary motion of the driving motor into linear motion;
and one end of the connecting piece is connected with the transmission piece, and the other end of the connecting piece is connected with the sleeve.
7. The dual flow adjustable swirl pintle injector of claim 5 wherein the second propellant outlet has an inner diameter that tapers from one side of the second chamber to one side of the third chamber, the second propellant being expelled from the boss into the inner wall gap of the combustion chamber base when the boss does not fully close the second propellant outlet to substantially mix with the circumferentially radially expelled first propellant.
8. The dual flow adjustable swirl pintle injector of claim 5, further comprising:
the first sealing groove is arranged between the outer wall of the sleeve and the partition plate;
the second seal groove is arranged between the inner wall of the protruding part and the pintle column section.
9. The dual flow adjustable swirl pintle injector of claim 5, wherein the raised portion has a vertically arcuate cross-section.
10. A liquid rocket engine, characterized in that the liquid rocket engine is provided with the double-flow adjustable cyclone pintle injector as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410001546.2A CN117605593A (en) | 2024-01-02 | 2024-01-02 | Double-flow adjustable rotational flow pintle injector and liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410001546.2A CN117605593A (en) | 2024-01-02 | 2024-01-02 | Double-flow adjustable rotational flow pintle injector and liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117605593A true CN117605593A (en) | 2024-02-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410001546.2A Pending CN117605593A (en) | 2024-01-02 | 2024-01-02 | Double-flow adjustable rotational flow pintle injector and liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117605593A (en) |
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2024
- 2024-01-02 CN CN202410001546.2A patent/CN117605593A/en active Pending
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