CN114856863B - Injector for spirally nested type explosive column - Google Patents
Injector for spirally nested type explosive column Download PDFInfo
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- CN114856863B CN114856863B CN202210666492.2A CN202210666492A CN114856863B CN 114856863 B CN114856863 B CN 114856863B CN 202210666492 A CN202210666492 A CN 202210666492A CN 114856863 B CN114856863 B CN 114856863B
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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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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Abstract
The invention provides an injector for a spirally nested grain, which comprises an injection cylinder and an inner nozzle channel, wherein the inner nozzle channel is formed in the injection cylinder and injects an oxidant to a combustion channel; the two swirl injection channels form opposite swirl directions in the inner spout channel. The injector provided by the invention can be applied to a solid-liquid rocket engine, and the injection swirl direction of an oxidant is regulated and controlled by selecting an injection channel, so that the problem of complex regulation of the retreating speed in the combustion process of the spirally nested grain is solved.
Description
Technical Field
The invention relates to the field of solid-liquid rocket engines, in particular to an injector for a spirally nested grain, which is applied to the interior of a solid-liquid rocket engine.
Background
With the increasing demand of all countries in the world for space exploration, the solid-liquid hybrid rocket is one of the key points of the development and research of all aerospace big countries due to the advantages of high energy property, capability of starting and stopping for many times, simple structure, easy thrust adjustment and the like. The development and manufacture of the engine as the core of the solid-liquid rocket are also important.
The accurate combustion control of the solid-liquid rocket engine is one of the core scientific problems which must be solved by the development of the engine. The solid-liquid rocket engine usually adopts the combination of separating liquid oxidant and solid fuel, the traditional engine combustion control mainly depends on the regulation of oxidant flow, and when the oxidant flow is changed, the solid fuel retreating speed can be correspondingly changed, so that the combustion state and the thrust of the engine can be regulated. The adjusting mode has extremely high requirements on an oxidant conveying system and a flow control system, and greatly improves the complexity of the system and the difficulty of engineering application; and the combustion characteristics of the traditional direct-current injection and single-hole grain are limited, the thrust adjusting range is small, and the combustion control capability is weak. The thrust regulating capacity of the solid-liquid rocket engine is limited, and the development of the engine in the aspect of combustion control is restricted.
Disclosure of Invention
The invention provides an injector for a spirally nested grain, which can be applied to a solid-liquid rocket engine and solves the problem of complex modulation of retreating rate in the combustion process of the spirally nested grain.
An injector for a spirally nested grain comprises an injection cylinder body and an inner nozzle channel which is formed inside the injection cylinder body and injects an oxidant to a combustion channel, wherein a direct-current injection channel and two rotational-flow injection channels which are communicated with the inner nozzle channel are independently formed on the injection cylinder body, the oxidant enters the inner nozzle channel through the direct-current injection channel in a direct-current mode, and the oxidant is injected from the side part of the inner nozzle channel through the two rotational-flow injection channels and enters the inner nozzle channel to form rotational flow;
the two swirl injection channels form opposite swirl directions in the inner nozzle channel.
Further, the direct current injection channel is a through hole structure which is axially formed at one end part of the injection cylinder body, close to the oxidant inlet, and is communicated with the inner spout channel;
the direct current injection channel and the inner spout channel are coaxially arranged.
Further, the rotational flow injection channel comprises an annular cavity formed on the injection cylinder, an inlet channel and at least 2 shunt channels, the annular cavity is formed inside the injection cylinder in a surrounding mode, one end of the inlet channel is communicated with the oxidant, the other end of the inlet channel is communicated with the annular cavity, one end of the shunt channel is communicated with the annular cavity, and the other end of the shunt channel is communicated with the inner nozzle channel;
the outlet directions of all the branch channels of the two swirl injection channels are respectively in different swirl directions so as to form swirl in different directions corresponding to the swirl directions.
Further, the annular cavity is coaxially arranged with the inner spout channel.
Further, the annular cavities of the two swirl injection channels are arranged in parallel along the axial direction of the inner nozzle channel.
Furthermore, the flow dividing channels of the same swirl injection channel are distributed in central symmetry.
Further, the number of the flow dividing channels is 4.
Further, the inner jet channel is located in the center of the injector barrel.
Further, the oxidant is respectively connected to the inlet end of the straight-flow injection channel and the inlet channels of the two swirl injection channels through three branch pipelines, and each branch pipeline is communicated with a separate valve control channel through one independent valve control channel.
Compared with the prior art, the invention has the following beneficial effects:
1. the injector provided by the invention is based on the influence characteristics of different injection modes of an oxidant on the spirally nested grain moving speed, and the injection direction of the oxidant is controlled by arranging the injection channel and the shunt channel, so that the combustion characteristic of the solid-liquid rocket engine is effectively regulated and controlled. Based on co-rotation injection and spiral nested grain coupling, the limit of combustion characteristics of direct-current injection and the traditional single-hole grain is broken through, the retreating speed is improved, and the thrust of the engine can be greatly improved.
2. In the invention, the injection mode is changed only by switching the valve instead of the traditional control method of adjusting the valve opening or changing the oxidant flow by the oxidant supply pressure, so that the engineering application is easier to realize and the system reliability is high.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
FIG. 1 is a schematic view of the structure of a solid-liquid rocket engine according to the present invention;
FIG. 2 is a schematic diagram of an injection mode and a spirally nested grain of the present invention;
FIG. 3 is a schematic diagram of the injector according to an embodiment of the present invention; wherein A-A isbase:Sub>A cross section of direct current injection, B-B isbase:Sub>A cross section of reverse rotation injection, and C-C isbase:Sub>A cross section of co-rotation injection;
FIG. 4 is a schematic structural diagram of a flow distribution channel according to an embodiment of the present invention;
FIG. 5 is a schematic view of the operation of the solid-liquid rocket engine according to the present invention;
FIG. 6 is a graph showing the variation of the retreating speed of the spirally nested grain coupled with different injection modes in the embodiment of the present invention;
notation of the reference numerals: 1-integrated valve, 2-injector, 3-spiral nested type grain, 4-high moving rate fuel, 5-spiral blade; 101-straight-flow injector control valve, 102-reverse-rotation injector control valve, 202-inner nozzle channel, 203-straight-flow injection channel, 204-rotational-flow injection channel, 205-annular cavity, 206-inlet channel, 207-shunt channel, 6-oxidant inlet, 7-combustion channel, 8-combustion chamber, 9-oxidant storage tank and 10-nozzle.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The spiral nested type explosive column is composed of two fuels with different retreating rates, low retreating rate fuels (such as ABS, aluminum powder and the like) are prepared into an explosive column base body with a plurality of groups of spiral blades, the number of the spiral blades can be selected from 6-12 groups and arranged at equal intervals, and the fuels with relatively high retreating rates (such as paraffin-based fuels, paraffin-doped HTPB fuels and the like) are filled into spiral channels between adjacent blades. When the spirally nested type explosive column burns, after the high-retreating-rate fuel in the spiral channel burns for any time length at first, the combustion of the spiral blade is finished, so that the spiral blade keeps a spiral channel structure in the combustion process of the high-retreating-rate fuel, and the retreating rate of the explosive column and the combustion efficiency are improved.
Aiming at the solid-liquid rocket engine adopting the spirally nested type grain which forms the spiral channel through the spiral blade, the spiral blade in the spirally nested type grain forms the spiral channel along with the combustion of the grain, the moving speed is different along with the different spiral angles from the combustion to the spiral blade in the combustion process, but the regulation and control thrust size needs to be further considered in the spirally nested type grain combustion process. In the prior art, thrust is mainly regulated and controlled by means of regulating the flow of an oxidant, but the regulation and control of the flow of the oxidant have extremely high requirements on an oxidant conveying system, particularly a variable flow control valve.
In contrast, the invention provides a combustion control method for a solid-liquid rocket engine, which specifically comprises the following steps: the solid-liquid rocket engine adopts the spirally nested grain (namely, the spirally nested grain of the spiral channel is formed on the inner wall of the combustion channel of the grain through the spiral blades), and controls the injection mode of the oxidant so that the oxidant is injected along the axial direction of the spirally nested grain in a direct current mode, in the same spiral direction as the spiral direction of the spiral channel or in a reverse spiral mode in the same spiral direction as the spiral direction of the spiral channel, and further the moving back rate of a combustion interface is changed.
The combustion control method provided by the invention combines the characteristics of the spiral channel in the spirally nested grain, and realizes thrust regulation and control by controlling the injection direction of the oxidant in the combustion channel.
Based on the solid-liquid rocket engine combustion control method, the solid-liquid rocket engine capable of implementing the combustion control method further comprises an injector 2, a spirally nested grain 3, an oxidant inlet 6 and a combustion chamber 8, wherein the combustion chamber 8 is used for mounting the spirally nested grain 3, the oxidant inlet 6 is communicated to the injector 2, and the injector 2 is used for injecting oxidant into a combustion channel 7 in the spirally nested grain.
As shown in fig. 2 and 3, the injector 2 includes an injector cylinder 201, and an inner nozzle channel 202 formed inside the injector cylinder 201 and injecting oxidant into the combustion channel 7, wherein the inner nozzle channel 202 is located at the center of the injector cylinder 201, a direct-flow injector channel 203 and two swirl injector channels 204 are independently formed on the injector cylinder 201, the oxidant enters the inner nozzle channel 202 through the direct-flow injector channel 203 in a direct-flow manner, and the oxidant is injected from the side of the inner nozzle channel 202 through the two swirl injector channels 203 and enters the inner nozzle channel 202 to form a swirl flow;
the direct-current injection channel 203 axially and directly injects oxidant to the inner nozzle channel 202, and the two swirl injection channels 204 inject oxidant from the side of the inner nozzle channel 202 to form swirl inside the inner nozzle channel 202; wherein the two swirl injection channels 204 form swirl inside the inner nozzle channel 202 in opposite directions.
In other words, the present embodiment integrates three injection modes on one injection cylinder 201, and enters the combustion channel through one inner nozzle channel 202, that is, the selection of the three injection modes can be controlled only by controlling the supply of the oxidant, so as to realize the regulation of the retreating rate. The solid-liquid rocket engine provided by the invention controls the injection mode in the injector to further regulate and control the rotational flow direction of the oxidant, thereby realizing the control of the thrust of the engine.
In the present embodiment, the formation of the direct current injection passage 203 and the two swirl injection passages 204 is not particularly limited, and it is only necessary to form oxidant flows of direct current, normal swirl, and reverse swirl in the inner jet passage 202.
To simplify the injector system construction, ease of implementation and control, this embodiment further provides a preferred embodiment of direct, positive and reverse swirl, as shown in fig. 3, as follows:
as shown inbase:Sub>A-base:Sub>A sectional view of fig. 3, the straight injection channel 203 isbase:Sub>A through hole structure axially formed at an end of the injection cylinder 201 near the oxidant inlet (i.e., oxidant inlet 6) and communicating with the inner nozzle channel 202; the direct injection channel 203 is arranged coaxially with the inner jet channel 202. In a straight-flow injection channel 203 in the injector 2, oxidant is injected into a combustion channel from an oxidant inlet 6 through the straight-flow injection channel 203 and from an inner nozzle channel 202 along the axial direction of a spirally nested grain.
The swirl injection channel 204 comprises an annular cavity 205, an inlet channel 206 and at least 2 flow dividing channels 207, which are formed on the injection cylinder 201, wherein the annular cavity 205 is formed inside the injection cylinder 201 in a circumferential surrounding manner and is coaxially arranged with the inner nozzle channel 202, one end of the inlet channel 206 is communicated with the oxidant inlet 6, the other end of the inlet channel is communicated with the annular cavity 205, one end of the flow dividing channel 207 is communicated with the annular cavity 205, the other end of the flow dividing channel is communicated with the inner nozzle channel 202, and the outlet directions of all the flow dividing channels 207 of the two swirl injection channels 204 are respectively in different swirling directions so as to form swirling flows in different corresponding swirling directions.
In this embodiment, the swirling flow is mainly formed by first making the oxidant form a circumferentially moving gas flow in the annular cavity 205, and then making the gas flow enter the inner nozzle channel 202 through the branch channel 207 at different positions of the annular cavity 205 in different injection directions, but it is required that the injection directions (the outlet directions of the branch channels 207) are distributed along a swirling direction, and then a plurality of gas flows entering the inner nozzle channel 202 in different directions form a forward swirling flow or a reverse swirling flow, as shown in the sectional views B-B and C-C in fig. 3.
As shown in fig. 4, two diversion channels are taken as an example and distributed randomly, and the injection directions thereof face the same rotation direction, so that a rotation flow can be formed.
In fact, the outlet direction distribution and number of the diversion channel 207, and the position of the diversion channel entering the inner nozzle channel 202, etc. form different sizes or characteristics of the rotational flows, and the rotational flows are selected through testing according to the regulation and control requirements of the actual retreating speed. The following provides a preferred scheme for the number, distribution and location of the diversion channels 207:
as shown in fig. 3, the number of the branch channels 207 is 4, and the branch channels 207 are arranged in a central symmetrical distribution (i.e. the straight line where two adjacent branch channels 207 are located is perpendicular), and the ends of the branch channels 207 communicate close to the direction tangential to the inner nozzle channel 202, so that the rotational flow formed by the solution provided by this embodiment is relatively large and stable.
In a preferred embodiment, the annular cavities 205 of the two swirl injection channels 204 are arranged in parallel in the axial direction of the inner jet channel 202. The relative positions of the two swirling jet passages 204 (near or far from the oxidant inlet) are not limiting.
Wherein the inner jet channel 202 is located in the centre of the injector cylinder 201.
In the embodiment, preferably, the oxidant inlet 6 is connected to the inlet end of the straight injection channel 203 and the inlet channels 206 of the two swirl injection channels 204 through three branch lines, and each branch line controls the passage through a separate valve 101. Specifically, as shown in fig. 3, the oxidant inlet 6 is connected to three branch pipelines through 1 main pipeline, and the three branch pipelines respectively control the straight injection channel 203 and the two swirl injection channels 204 through one valve 101.
According to the invention, the number and distribution of the shunt channels in the two swirl injection channels can be determined according to design requirements, the swirl injection channels of the direct-current injection channels or different injection modes are selected, and the injection direction and size of the oxidant are further determined, so that the thrust regulation and control of the solid-liquid rocket engine are realized, and the engineering application is easier to realize.
In a possible embodiment, the injection direction of the branch channels 207 can also be confirmed by testing the included angle between the adjacent branch channels 207, that is, at least two branch channels 207 in the same swirl injection channel are installed between the annular cavity 205 and the inner nozzle channel 202 at an angle to each other, which is the angle between the straight intersection points of the two adjacent branch channels 207. And at least two flow dividing channels 207 which are mutually angled enable the oxidant to be injected into the inner nozzle channel 202 in a certain injection direction, and the oxidant is enabled to rotate to the combustion channel 7 of the spirally nested grain 3 in a rotational flow direction under the injection pressure. Taking fig. 4 as an example, two branch channels 207 are counterclockwise communicated between the annular cavity 205 and the inner nozzle channel 202, the included angle is a, the injection swirl direction of the oxidant is the same as the spiral direction of the spiral channel, and the oxidant is injected into the spirally nested grain in the same rotation.
In a preferred embodiment, the angle between adjacent flow distribution channels 207 is 90 °, any two adjacent flow distribution channels 207 are connected between the annular cavity 205 and the inner nozzle channel 202 in a 90-degree relationship, and the swirling direction of the oxidant is more stable than that generated by other angles.
The working process of the solid-liquid rocket engine is shown in figure 5, after an oxidant in an oxidant storage tank 9 enters a pipeline through an oxidant inlet 6, an injection mode is determined by an integrated valve 1, the oxidant is injected through a selected injection channel and is combusted with a spirally nested grain 3, high-temperature and high-pressure gas fills the whole combustion channel 7, the high-temperature and high-pressure gas is injected through a nozzle 10 to generate thrust, the injection mode of the oxidant is changed, and the thrust is adjustable. Fig. 6 shows a change rule of the retreating speed of the spirally nested type fuel grain coupled with different injection modes, and it can be seen that the retreating speed of the combustion surface of the spirally nested type fuel grain is greatly influenced by the different injection modes, and particularly, the retreating speed of the combustion surface of the spirally nested type fuel grain is remarkably improved by adopting co-rotation injection, which is already remarkably higher than the retreating speed of the paraffin-based fuel grain at the international highest level, so that the thrust regulation range of the engine can be greatly improved.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made to the disclosure by those skilled in the art within the spirit and scope of the disclosure, and such modifications and equivalents should also be considered as falling within the scope of the disclosure.
Claims (8)
1. An injector for a spirally nested grain of medicine, which is characterized in that,
the burner comprises a jetting cylinder (201), and an inner jet channel (202) which is formed inside the jetting cylinder (201) and jets oxidant to a combustion channel (7), wherein a direct current jetting channel (203) and two swirl jetting channels (204) which are communicated with the inner jet channel (202) are independently formed on the jetting cylinder (201), the oxidant enters the inner jet channel (202) through the direct current jetting channel (203) in a direct current manner, and the oxidant is jetted from the side part of the inner jet channel (202) through the two swirl jetting channels (204) to enter the inner jet channel (202) to form swirl;
wherein the two swirl injection channels (204) form a swirl inside the inner jet channel (202) with opposite directions of swirl;
the oxidant is connected to the inlet end of the straight jet channel (203) and the inlet channels (206) of the two swirl jet channels (204) by three branch lines, each of which controls the passage by an independent valve (101).
2. An injector for a spirally nested cartridge according to claim 1, wherein said straight jet channel (203) is a through hole structure axially formed at an end of said jet cylinder (201) near an inlet of said oxidizer and communicating with said inner jet channel (202);
the direct current injection channel (203) is arranged coaxially with the inner jet channel (202).
3. The injector for the spirally nested grain according to claim 1, wherein the swirl injection channel (204) comprises an annular cavity (205) formed on the injection cylinder (201), an inlet channel (206) and at least 2 shunt channels (207), the annular cavity (205) is circumferentially formed around the inside of the injection cylinder (201), one end of the inlet channel (206) is communicated with the oxidant, the other end of the inlet channel is communicated with the annular cavity (205), one end of the shunt channel (207) is communicated with the annular cavity (205), and the other end of the shunt channel is communicated with the inner nozzle channel (202);
the outlet directions of all the branch channels (207) of the two swirl injection channels (204) are respectively in different directions of rotation, so that swirl in different directions in the corresponding directions of rotation is formed.
4. An injector for a spirally nested cartridge as claimed in claim 3, wherein said annular cavity (205) is arranged coaxially with said inner nozzle channel (202).
5. An injector for helically nested grains according to claim 4, wherein the annular cavities (205) of two of the swirl injection channels (204) are arranged in parallel in the axial direction of the inner nozzle channel (202).
6. An injector for a spirally nested column according to claim 3, wherein said diverging channels (207) of the same swirl injection channel (204) are centrosymmetrically distributed.
7. An injector for a spirally nested column according to any one of claims 3 or 6, wherein the number of said dividing channels is 4.
8. An injector for helically nested grains according to claim 1, wherein the inner nozzle channel (202) is located in the centre of the injector barrel (201).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210666492.2A CN114856863B (en) | 2022-06-14 | 2022-06-14 | Injector for spirally nested type explosive column |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210666492.2A CN114856863B (en) | 2022-06-14 | 2022-06-14 | Injector for spirally nested type explosive column |
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| CN114856863A CN114856863A (en) | 2022-08-05 |
| CN114856863B true CN114856863B (en) | 2022-12-23 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| TWI504538B (en) * | 2013-05-31 | 2015-10-21 | Nat Applied Res Laboratories | Dual-vortical-flow hybrid rocket engine |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN109372656B (en) * | 2018-12-24 | 2020-07-07 | 中国人民解放军战略支援部队航天工程大学 | Rocket engine injection panel with adjustable nozzle liquid mist distribution and design method |
| CN109989850B (en) * | 2019-04-12 | 2020-06-05 | 中国科学院力学研究所 | Grain for solid-liquid rocket engine |
| CN113294265B (en) * | 2021-07-21 | 2021-10-15 | 北京星际荣耀空间科技股份有限公司 | Pintle injector for liquid rocket engine |
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