阅读说明：本技术 一种同轴式大范围流量、混合比调节喷注器及其使用方法 (Coaxial injector capable of adjusting large-range flow and mixing ratio and using method thereof ) 是由 魏祥庚 赵志新 卞香港 朱韶华 李玲玉 左有幸 秦飞 于 2019-08-16 设计创作，主要内容包括：本发明公开了一种同轴式大范围流量、混合比调节喷注器及其使用方法,以填补现有技术中缺少一种同轴式大范围流量、混合比调节喷注器的空白。该喷注器包括：一空心腔体,其外壁为外壳,其内部从上至下设置有四个相互隔离的腔室,即推进剂收集腔A～D；四个推进剂入口,从上之下分别设置于每个腔室与外壳相临的外壁上,即推进剂入口A～D,作为将推进剂注入对应腔室的入口；四个控制阀门,分别设置于推进剂入口A～D的入口处,用于控制每个入口的开闭；至少一个复合喷嘴,竖直设置于外壳内,复合喷嘴内设有四条相互隔离的喷射通道,四条喷射通道的入口分别与推进剂收集腔A～D连通,四条喷射通道的出口设置于外壳的底部。(The invention discloses a coaxial injector for adjusting large-range flow and mixing ratio and a using method thereof, which are used for filling the blank that the prior art lacks a coaxial injector for adjusting large-range flow and mixing ratio. The injector comprises: the propellant collecting cavity A-D is a hollow cavity, the outer wall of the hollow cavity is a shell, and four mutually isolated cavities, namely propellant collecting cavities A-D, are arranged in the hollow cavity from top to bottom; the four propellant inlets are respectively arranged on the outer wall of each cavity adjacent to the shell from top to bottom, namely propellant inlets A-D, and are used as inlets for injecting the propellant into the corresponding cavity; the four control valves are respectively arranged at the inlets of the propellant inlets A-D and are used for controlling the opening and closing of each inlet; the composite nozzle is vertically arranged in the shell, four mutually isolated spraying channels are arranged in the composite nozzle, inlets of the four spraying channels are respectively communicated with the propellant collecting cavities A-D, and outlets of the four spraying channels are arranged at the bottom of the shell.)

1. A coaxial wide range flow, mixing ratio regulating injector, comprising:

the outer wall of the hollow cavity is a shell (6), and four mutually isolated cavities, namely propellant collecting cavities A-D (18, 19, 20 and 21), are arranged in the hollow cavity from top to bottom;

four propellant inlets, which are respectively arranged on the outer wall of each chamber adjacent to the shell (6) from top to bottom, namely propellant inlets A-D (14, 15, 16, 17), are used as inlets for injecting the propellant into the corresponding chambers;

the four control valves are respectively arranged at the inlets of the propellant inlets A-D (14, 15, 16 and 17) and are used for controlling the opening and closing of each inlet;

the composite spray nozzle comprises at least one composite spray nozzle (8) which is vertically arranged in the shell (6), four mutually isolated spray channels are arranged in the composite spray nozzle (8), inlets of the four spray channels are respectively communicated with the propellant collecting cavities A-D (18, 19, 20 and 21), and outlets of the four spray channels are arranged at the bottom of the shell (6).

2. An in-line wide flow and mixing ratio regulating injector as set forth in claim 1, wherein said propellant collecting chambers a-D (18, 19, 20, 21) are sequentially arranged in the order of oxidizer chamber, fuel chamber, oxidizer chamber and fuel chamber, or fuel chamber, oxidizer chamber, fuel chamber and oxidizer chamber from top to bottom.

3. A coaxial wide range flow, mixing ratio regulating injector according to claim 1 or 2, characterized in that it is located at the axis of said injector and/or that a plurality of said compound nozzles (8) are arranged uniformly around said axis.

4. A coaxial wide range flow, mixing ratio adjustment injector according to claim 3, characterized in that said compound nozzle (8) comprises:

the nozzle primary channel is a cylindrical channel A, the inlet of the nozzle primary channel is communicated with the propellant collecting cavity A (21), and the outlet of the nozzle primary channel is a nozzle outlet A (22);

the nozzle secondary channel is an annular channel B arranged around the cylindrical channel A, the inlet of the nozzle secondary channel is communicated with the propellant collecting cavity B (19), and the outlet of the nozzle secondary channel is a nozzle outlet B (23);

a nozzle tertiary channel which is an annular channel C arranged around the cylindrical channel B, the inlet of the nozzle tertiary channel is communicated with the propellant collecting cavity C (20), and the outlet of the nozzle tertiary channel is a nozzle outlet C (24);

and the nozzle four-stage channel is an annular channel D arranged around the cylindrical channel C, the inlet of the nozzle four-stage channel is communicated with the propellant collecting cavity D (21), and the outlet of the nozzle four-stage channel is a nozzle outlet D (25).

5. A coaxial wide range flow, mixing ratio adjustment injector according to claim 3, characterized in that said compound nozzle (8) comprises:

the primary nozzle (9) is formed by connecting a primary upper cylinder (91) and a primary lower cylinder (92) up and down, a cylindrical channel A is arranged along the axis direction of the primary upper cylinder and the primary lower cylinder, the inlet of the cylindrical channel A is communicated with the propellant collecting cavity A, and the outlet of the cylindrical channel A is a nozzle outlet A (22);

the secondary nozzle (10) is formed by connecting a secondary upper hollow cylinder (101) and a secondary lower hollow cylinder (102) up and down, the secondary upper hollow cylinder (101) is detachably sleeved outside the primary upper cylinder (91), the secondary lower hollow cylinder (102) is sleeved outside the primary lower cylinder (92), an annular channel B is arranged in the outer wall of the secondary lower hollow cylinder (102), the inlet of the annular channel B is communicated with the propellant collecting cavity B, and the outlet of the annular channel B is a nozzle outlet B (23);

the three-stage nozzle (12) is formed by connecting a three-stage upper hollow cylinder (121) and a three-stage lower hollow cylinder (122) up and down, the three-stage upper hollow cylinder (121) is detachably sleeved outside the second-stage upper cylinder, the three-stage lower hollow cylinder (122) is sleeved outside the second-stage lower cylinder, an annular channel C is arranged in the outer wall of the three-stage lower hollow cylinder (122), the inlet of the annular channel C is communicated with the propellant collecting cavity C, and the outlet of the annular channel C is a nozzle outlet C (24);

the four-stage nozzle (13) is formed by connecting a four-stage upper hollow cylinder (131) and a four-stage lower hollow cylinder (132) from top to bottom, the four-stage upper hollow cylinder (131) can be detachably sleeved outside the three-stage upper cylinder, the four-stage lower hollow cylinder (132) is sleeved outside the three-stage lower cylinder, an annular channel D is arranged in the outer wall of the four-stage lower hollow cylinder (132), the inlet of the annular channel D is communicated with the propellant collecting cavity D, and the outlet of the annular channel D is a nozzle outlet D (25).

6. A use method of a coaxial injector with large-range flow and mixing ratio adjustment is characterized in that a strategy that fuel enters from a propellant inlet B (15) and a propellant inlet D (17), and oxidant enters from a propellant inlet A (14) and a propellant inlet C (16) is adopted, the initial working condition is assumed that the oxidant and the fuel are respectively sprayed out from a nozzle outlet, the pressure drop of two nozzles is moderate, and the working condition is marked as a working condition A;

under the working condition A, the valve A (1) is controlled to be opened, and at the moment, the oxidant and the fuel respectively flow out from the nozzle outlet C (24) and the nozzle outlet D (25); at the moment, the outlet of a single composite nozzle only has one mixing surface, and the mixing effect is similar to that of a common coaxial shearing nozzle;

wherein, the control valve A (1) and the control valve C (2) are equivalent in function, and the control valve C (2) can be closed; the control valve B (5) is functionally equivalent to the control valve D (4), and the control valve D (4) may be closed, with only the propellant inlet C (16) and the propellant inlet D (17).

7. The method of claim 6, wherein when the rocket operating condition needs to be adjusted up in a large range to ensure that the oxygen-fuel ratio is unchanged, namely the rocket operating condition is changed from the operating condition A to the operating condition B, the total flow of the operating condition B is at least 200% of the operating condition A, and the oxygen-fuel ratio is the same;

control valve a1 and control valve B (5) are open, with all four propellant inlets open, and with propellant flowing from nozzle outlet a (22), nozzle outlet B (23), nozzle outlet C (24), and nozzle outlet D (25).

8. The method of claim 6, wherein when the rocket operating condition requires a large-scale flow rate down-regulation to ensure that the oxygen-fuel ratio is unchanged, i.e. the rocket operating condition is changed from operating condition A to operating condition C, the total flow rate of the operating condition C is lower than 50% of the operating condition A, and the oxygen-fuel ratio is the same;

flow regulation is carried out by using a method for regulating the pressure of the inlet of the nozzle; oxidant and fuel are still flowing out of nozzle outlet C (24) and nozzle outlet D (25), respectively, and the nozzle pressure drop for condition B is about 0.5 MPa.

9. The method of claim 6, wherein when the rocket operating condition requires to keep the total flow unchanged and only the oxygen-fuel ratio is adjusted upwards, i.e. the rocket operating condition is changed from the operating condition A to the operating condition D, the total flow of the operating condition D is the same as the operating condition A, and the oxygen-fuel ratio of the operating condition D is at least 280% of the operating condition A;

opening the control valve A (1) and the control valve B (5), and closing the control valve D (4), wherein at the moment, a propellant inlet A (14), a propellant inlet B (15) and a propellant inlet C (16) are opened, and at the moment, the propellant flows out from a nozzle outlet A (22), a nozzle outlet B (23) and a nozzle outlet C (24) respectively.

10. The method of claim 6, wherein when the rocket operating condition requires to keep the total flow unchanged and only the oxygen-fuel ratio is adjusted downward, i.e. the rocket operating condition is changed from operating condition A to operating condition E, the total flow of operating condition E is the same as operating condition A, and the oxygen-fuel ratio of operating condition E is at least 50% lower than that of operating condition A;

at this time, the propellant inlet B (15), the propellant inlet C (16), and the propellant inlet D (17) are opened, and the propellant flows out from the nozzle outlet B (23), the nozzle outlet C (24), and the nozzle outlet D (25).

[ technical field ] A method for producing a semiconductor device

The invention belongs to the technical field of liquid rocket engine propulsion, and particularly relates to a coaxial injector for adjusting large-range flow and mixing ratio and a using method thereof.

[ background of the invention ]

Under the background of the rapid development of reusable liquid Rocket engines and Rocket-based combined cycle (RBCC) propulsion technologies, the realization of large-range flow and mixing ratio adjustment becomes the key of the two propulsion technologies. For reusable liquid rocket engines, the thrust provided by the engine is also quite different in the two stages, considering the difference in loads during launch and recovery. The injector of the engine is required to realize large-scale flow regulation, and meanwhile, the injector is required to ensure that the propellant has a good atomization and mixing effect; the RBCC is a very advanced propulsion technology, and due to the technical requirement of wide-range operation, the injector of the primary rocket, one of the internal components, is required to be capable of realizing the change from large flow to small flow to large flow injection in the whole operation range, and the blending atomization effect of the propellant is required to be ensured in the change process. Therefore, designing an injector which gives consideration to large-range flow and mixing ratio adjustment, atomization under different flow and mixing ratios, good mixing effect and simple structure has very important significance for the working performance of the reusable liquid rocket engine and the RBCC engine.

At present, a pintle injector used in a reusable liquid rocket engine can achieve the purpose of flow regulation only by introducing an additional mechanical structure to regulate the position of a pintle; the RBCC primary rocket engine adopts a single-nozzle injector with a fixed geometric structure, and the variable working conditions are realized by adjusting the pressure drop of the nozzle, and the adjusting scheme has a simple structure but puts higher requirements on a supply system. The regulation ratio is about 1/3-1/2 limited by the inlet pressure of the propellant, and the requirement of a task with a large range of variable working conditions cannot be met.

[ summary of the invention ]

The invention aims to provide a coaxial type large-range flow and mixing ratio adjusting injector and a using method thereof, so as to fill the blank that the prior art lacks a coaxial type large-range flow and mixing ratio adjusting injector.

The invention adopts the following technical scheme: a coaxial wide range flow, mixing ratio regulating injector, comprising:

the propellant collecting cavity A-D is a hollow cavity, the outer wall of the hollow cavity is a shell, and four mutually isolated cavities, namely propellant collecting cavities A-D, are arranged in the hollow cavity from top to bottom;

the four propellant inlets are respectively arranged on the outer wall of each cavity adjacent to the shell from top to bottom, namely propellant inlets A-D, and are used as inlets for injecting the propellant into the corresponding cavity;

the four control valves are respectively arranged at the inlets of the propellant inlets A-D and are used for controlling the opening and closing of each inlet;

the composite nozzle is vertically arranged in the shell, four mutually isolated spraying channels are arranged in the composite nozzle, inlets of the four spraying channels are respectively communicated with the propellant collecting cavities A-D, and outlets of the four spraying channels are arranged at the bottom of the shell.

Furthermore, the propellant collecting cavities A-D are sequentially arranged into an oxidant cavity, a fuel cavity, an oxidant cavity and a fuel cavity or a fuel cavity, an oxidant cavity, a fuel cavity and an oxidant cavity from top to bottom.

Further, the composite nozzles are positioned at the axis of the injector and/or are uniformly arranged around the axis.

Further, a compound nozzle, comprising:

the nozzle primary channel is a cylindrical channel A, the inlet of the nozzle primary channel is communicated with the propellant collecting cavity A, and the outlet of the nozzle primary channel is a nozzle outlet A;

the nozzle secondary channel is an annular channel B arranged around the cylindrical channel A, the inlet of the nozzle secondary channel is communicated with the propellant collecting cavity B, and the outlet of the nozzle secondary channel is a nozzle outlet B;

the nozzle tertiary channel is an annular channel C arranged around the cylindrical channel B, the inlet of the nozzle tertiary channel is communicated with the propellant collecting cavity C, and the outlet of the nozzle tertiary channel is a nozzle outlet C;

the nozzle four-stage channel is an annular channel D arranged around the cylindrical channel C, the inlet of the nozzle four-stage channel is communicated with the propellant collecting cavity D, and the outlet of the nozzle four-stage channel is the nozzle outlet D.

Further, a compound nozzle, comprising:

the primary nozzle is formed by connecting a primary upper cylinder and a primary lower cylinder up and down, a cylindrical channel A is arranged along the axis direction of the primary upper cylinder and the primary lower cylinder, the inlet of the cylindrical channel A is communicated with the propellant collecting cavity A, and the outlet of the cylindrical channel A is the nozzle outlet A;

the second-stage nozzle is formed by connecting a second-stage upper hollow cylinder and a second-stage lower hollow cylinder up and down, the second-stage upper hollow cylinder is detachably sleeved outside the first-stage upper cylinder, the second-stage lower hollow cylinder is sleeved outside the first-stage lower cylinder, an annular channel B is arranged in the outer wall of the second-stage lower hollow cylinder, the inlet of the annular channel B is communicated with the propellant collecting cavity B, and the outlet of the annular channel B is a nozzle outlet B;

the three-stage nozzle is formed by connecting a three-stage upper hollow cylinder and a three-stage lower hollow cylinder up and down, the three-stage upper hollow cylinder is detachably sleeved outside the second-stage upper cylinder, the three-stage lower hollow cylinder is sleeved outside the second-stage lower cylinder, an annular channel C is arranged in the outer wall of the three-stage lower hollow cylinder, the inlet of the annular channel C is communicated with the propellant collecting cavity C, and the outlet of the annular channel C is a nozzle outlet C;

the four-stage nozzle is formed by connecting a four-stage upper hollow cylinder and a four-stage lower hollow cylinder up and down, the four-stage upper hollow cylinder can be detachably sleeved outside the three-stage upper cylinder, the four-stage lower hollow cylinder is sleeved outside the three-stage lower cylinder, an annular channel D is arranged in the outer wall of the four-stage lower hollow cylinder, an inlet of the annular channel D is communicated with a propellant collecting cavity D, and an outlet of the annular channel D is a nozzle outlet D.

The second technical scheme adopted by the invention is a using method of a coaxial type large-range flow and mixing ratio adjusting injector, a strategy that fuel enters from a propellant inlet B and a propellant inlet D and oxidant enters from a propellant inlet A and a propellant inlet C is adopted, the initial working condition is assumed to be that the oxidant and the fuel are respectively sprayed out from a nozzle outlet, the pressure drop of two nozzles is moderate, and the working condition is marked as the working condition A;

under the working condition A, the valve A is controlled to be opened, and at the moment, the oxidant and the fuel respectively flow out from the nozzle outlet C and the nozzle outlet D; at the moment, the outlet of a single composite nozzle only has one mixing surface, and the mixing effect is similar to that of a common coaxial shearing nozzle;

wherein, the control valve A and the control valve C are equivalent in function, and C can be closed; the control valve B and the control valve D are equivalent in function, and the control valve D can be closed, and only the propellant inlet C and the propellant inlet D are provided.

Furthermore, when the working condition of the rocket needs to be adjusted up in a large range to ensure that the oxygen-fuel ratio is unchanged, namely the working condition A is changed into the working condition B, the total flow of the working condition B is at least 200% of the working condition A, and the oxygen-fuel ratio is the same;

control valve a and control valve B are opened, at which time the four propellant inlets are all open, at which time propellant flows out of nozzle outlet a, nozzle outlet B, nozzle outlet C and nozzle outlet D.

Furthermore, when the rocket working condition needs to be subjected to large-range flow rate down regulation to ensure that the oxygen-fuel ratio is unchanged, namely the working condition A is changed into the working condition C, the total flow rate of the working condition C is lower than 50% of the working condition A, and the oxygen-fuel ratio is the same;

flow regulation is carried out by using a method for regulating the pressure of the inlet of the nozzle; oxidant and fuel still flow out of nozzle outlet C and nozzle outlet D, respectively, and the nozzle pressure drop for condition B is about 0.5 MPa.

Furthermore, when the working condition of the rocket needs to keep the total flow unchanged and only the oxygen-fuel ratio is adjusted upwards, namely the working condition A is changed into a working condition D, the total flow of the working condition D is the same as that of the working condition A, and the oxygen-fuel ratio of the working condition D is at least 280% of that of the working condition A;

and opening the control valve A and the control valve B, and closing the control valve D at the same time, wherein at the moment, a propellant inlet A, a propellant inlet B and a propellant inlet C are opened, and at the moment, the propellant flows out from the nozzle outlet A, the nozzle outlet B and the nozzle outlet C respectively.

Furthermore, when the total flow needs to be kept unchanged under the working condition of the rocket and only the oxygen-fuel ratio is adjusted downwards, namely the working condition A is changed into the working condition E, the total flow of the working condition E is the same as that of the working condition A, and the oxygen-fuel ratio of the working condition E is at least 50% lower than that of the working condition A;

at this time, the propellant inlet B, the propellant inlet C, and the propellant inlet D are opened, and the propellant flows out from the nozzle outlet B, the nozzle outlet C, and the nozzle outlet D.

The invention has the beneficial effects that: the characteristics of stable and reliable work and good mixing effect of the coaxial nozzles are combined, the mixing characteristic of the coaxial nozzles is kept, and the large-range adjustment of the oxygen-fuel ratio is completed under the condition that the output pressure of a supply system is not changed by introducing a nested four-stage nozzle structure; and can ensure that the performance analysis studied for the coaxial shear nozzle can be fully applied to the design of the nozzle; in addition, due to the introduction of the four-stage nested structure, the mixing area of the propellant sprayed out of the nozzle is increased, and the mixing effect is increased.

[ description of the drawings ]

FIG. 1 is a schematic diagram of an engine with a coaxial wide-range flow and mixing ratio control injector according to the present invention;

FIG. 2 is a schematic structural diagram of an injector of a coaxial wide-range flow and mixing ratio adjusting injector according to the present invention;

FIG. 3 is a schematic diagram of the positional arrangement of the nozzles of a coaxial wide range flow, mix ratio adjustment injector of the present invention;

FIG. 4 is a schematic view of a nozzle structure of a coaxial wide-range flow and mixing ratio adjusting injector according to the present invention;

FIG. 5 is a schematic diagram of a primary nozzle structure of a coaxial wide-range flow and mixing ratio adjusting injector according to the present invention;

FIG. 6 is a schematic diagram of a secondary nozzle structure of a coaxial wide-range flow and mixing ratio adjusting injector according to the present invention;

FIG. 7 is a schematic diagram of a three-stage nozzle structure of a coaxial wide-range flow and mixing ratio adjusting injector according to the present invention;

fig. 8 is a schematic diagram of a four-stage nozzle structure of a coaxial wide-range flow and mixing ratio adjusting injector.

Wherein, 1, controlling a valve A; 2. a control valve C; 3. an engine; 4. controlling a valve D; 5. a control valve B; 6. an injector housing; 7. an injector baffle; 8. a compound nozzle; 9. a primary nozzle; 10. a secondary nozzle; 11. sealing gaskets; 12. a tertiary nozzle; 13. a four-stage nozzle; 14. a propellant inlet A; 15. A propellant inlet B; 16. a propellant inlet C; 17. a propellant inlet D; 18. a propellant collection chamber A; 19. a propellant collection chamber B; 20. a propellant collection chamber C; 21. a propellant collection chamber D; 22. a nozzle outlet A; 23. a nozzle outlet B; 24. a nozzle outlet C; 25. a nozzle outlet D;

91. the cylinder comprises a first-stage upper cylinder, a first-stage lower cylinder, a second-stage upper hollow cylinder, a second-stage lower hollow cylinder, a first-stage upper hollow cylinder, a second-stage lower hollow cylinder, a third-stage upper hollow cylinder, a third-stage lower hollow cylinder.

[ detailed description ] embodiments

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

The invention provides a coaxial type injector with wide flow and mixing ratio regulation, which is shown in figures 1 and 2 and comprises a control valve positioned in an oxidant/fuel supply path, wherein the control valve is connected with a head injector through a welding pipeline or by adopting a standard connector; the injector is divided into four cavities and is positioned at the top of the rocket engine; the injector is internally sleeved with a plurality of nozzles, and each outlet of each nozzle is connected with one cavity in the injector but not communicated with other cavities.

The structure specifically comprises the following:

1. the outer wall of the hollow cavity is a shell 6, and four mutually isolated cavities, namely propellant collecting cavities A-D (18, 19, 20 and 21), are arranged in the hollow cavity from top to bottom. As shown in fig. 2, the injector chamber is separated by a partition, and the partition is connected to the housing by welding, and the injector base plate is also connected to the housing by welding. And after the inlets of the channels of all stages are connected with the cavities of all stages, the nozzles and the partition plates are fixed by using a welding method.

The propellant collecting cavities A-D (18, 19, 20, 21) are sequentially arranged into an oxidant cavity, a fuel cavity, an oxidant cavity and a fuel cavity or a fuel cavity, an oxidant cavity, a fuel cavity and an oxidant cavity from top to bottom. For the combination of liquid phase in the propellant, the liquid propellant is ensured to be in the cavity at the bottommost layer as far as possible, so that a good thermal protection effect of the injector is achieved, four cavities of the injector are respectively connected with four pipelines, and each pipeline is provided with a valve capable of controlling the opening and closing of the pipeline.

2. Four propellant inlets, which are respectively arranged on the outer wall of each chamber adjacent to the housing 6 from top to bottom, namely propellant inlets A-D (14, 15, 16, 17), are used as inlets for injecting propellant into the corresponding chambers.

3. And the four control valves are respectively arranged at the inlets of the propellant inlets A-D (14, 15, 16 and 17) and are used for controlling the opening and closing of each inlet.

4. The composite nozzle is vertically arranged in the shell 6, four mutually isolated spraying channels are arranged in the composite nozzle (8), inlets of the four spraying channels are respectively communicated with propellant collecting cavities A-D (18, 19, 20 and 21), outlets of the four spraying channels are arranged at the bottom of the shell 6, the connection sequence of the nozzle and the injector is that after a primary partition plate is welded to form a primary cavity, the nozzle is placed in a reserved mounting hole of the primary partition plate of the injector, after the inlet of the primary channel of the nozzle is adjusted to be connected with the primary cavity, the lower surface of the primary partition plate is welded, a secondary partition plate is welded to form a secondary cavity, the inlet of the secondary channel of the nozzle is ensured to be connected with the secondary cavity, and then the welding of the four-stage partition plate is sequentially completed.

As shown in fig. 3, a plurality of composite nozzles 8 may be located at the axial center of the injector and/or may be arranged evenly around the axial center. The nozzle comprises a circular channel and three annular channels, four channel outlets are all located in the circular channel, the first-level channel is a circular channel, an inlet is formed in the top end of the first-level channel, inlets are formed in the lateral directions of the second-level channel, the third-level channel and the fourth-level channel respectively, the inlets are all annular outlets, the outlets of the four channels are all located in the bottom end of the first-level channel, and the four channels are communicated with one-layer cavity to four-layer cavity of the injector respectively.

The composite spout 8 comprises: the nozzle primary channel is a cylindrical channel A, the inlet of the nozzle primary channel is communicated with the propellant collecting cavity A21, and the outlet of the nozzle primary channel is a nozzle outlet A22; the nozzle secondary channel is an annular channel B arranged around the cylindrical channel A, the inlet of the nozzle secondary channel is communicated with the propellant collecting cavity B19, and the outlet of the nozzle secondary channel is a nozzle outlet B23; the nozzle tertiary channel is an annular channel C arranged around the cylindrical channel B, the inlet of the nozzle tertiary channel is communicated with the propellant collecting cavity C20, and the outlet of the nozzle tertiary channel is a nozzle outlet C24; the nozzle four-stage channel is an annular channel D arranged around the cylindrical channel C, the inlet of the nozzle four-stage channel is communicated with the propellant collecting cavity D21, and the outlet of the nozzle four-stage channel is a nozzle outlet D25.

As shown in fig. 4, the compound nozzle 8 includes a first-stage nozzle 9, a second-stage nozzle 10, a third-stage nozzle 12, and a fourth-stage nozzle 13, which are sequentially nested from top to bottom, i.e., form four nozzle outlets 22-25 in the form of annular channels.

The composite nozzle 8 can be specifically arranged according to the following structure:

the primary nozzle 9, as shown in fig. 6, is formed by connecting a primary upper cylinder 91 and a primary lower cylinder 92 up and down, and is provided with a cylindrical channel a along the axial direction, the inlet of the cylindrical channel a is communicated with the propellant collecting cavity a, and the outlet of the cylindrical channel a is the nozzle outlet a 22; the secondary nozzle 10 is formed by connecting a secondary upper hollow cylinder 101 and a secondary lower hollow cylinder 102 up and down as shown in fig. 7, the secondary upper hollow cylinder 101 is detachably sleeved outside the primary upper cylinder 91, the secondary lower hollow cylinder 102 is sleeved outside the primary lower cylinder 92, an annular channel B is arranged in the outer wall of the secondary lower hollow cylinder 102, the inlet of the annular channel B is communicated with the propellant collecting cavity B, and the outlet of the annular channel B is a nozzle outlet B23; the three-stage nozzle 12 is formed by connecting a three-stage upper hollow cylinder 121 and a three-stage lower hollow cylinder 122 up and down as shown in fig. 8, the three-stage upper hollow cylinder 121 is detachably sleeved outside the two-stage upper cylinder, the three-stage lower hollow cylinder 122 is sleeved outside the two-stage lower cylinder, an annular channel C is arranged in the outer wall of the three-stage lower hollow cylinder 122, the inlet of the annular channel C is communicated with the propellant collecting cavity C, and the outlet of the annular channel C is a nozzle outlet C24; the four-stage nozzle 13, as shown in fig. 8, is formed by connecting a four-stage upper hollow cylinder 131 and a four-stage lower hollow cylinder 132 from top to bottom, the four-stage upper hollow cylinder 131 is detachably sleeved outside the three-stage upper cylinder, the four-stage lower hollow cylinder 132 is sleeved outside the three-stage lower cylinder, an annular channel D is arranged in the outer wall of the four-stage lower hollow cylinder 132, the inlet of the annular channel D is communicated with the propellant collecting cavity D, and the outlet of the annular channel D is a nozzle outlet D25.

The composite nozzle 8 has a four-stage channel, and consists of a four-stage nozzle shell and three red copper gaskets. The center of the first-level nozzle shell is a round hole, and the outside from top to bottom is as follows: the top end is a hexagonal prism structure which is convenient to hold and install, the lower part of the hexagonal prism structure is a thread structure which is convenient to be connected with the shell of the secondary nozzle, the lower part of the hexagonal prism structure is a cylindrical shell with a thinner thickness, and the thickness of the cylindrical wall is about 1 mm. The structure of the second-level nozzle is basically the same as that of the third-level nozzle, the inside of the second-level nozzle is of a threaded structure from top to bottom in sequence, the second-level nozzle is convenient to be connected with the upper-level nozzle, a straight cylindrical hole is arranged below the second-level nozzle, the diameter of the hole is slightly larger than the outer diameter of a cylindrical shell on the lower layer of the first-level nozzle, the outside of the second-level nozzle is of a hexagonal prism structure from top to bottom in sequence, the cylindrical structure is convenient to be welded with a clapboard of an injector, the inlet of the second-level three-level channel is provided with a threaded structure, the threaded structure is convenient to be connected with the lower-level nozzle.

The external structure of the four-stage nozzle structure is only cylindrical, the internal structure of the four-stage nozzle structure is the same as the shape of the shells of the two-stage nozzle and the three-stage nozzle, but the size of the internal channel is only reserved in the thin-wall cylindrical section. The inlets of the two, three and four stages of nozzle channels are arranged at the lower end of the internal thread structure and the upper end of the external thread structure of each stage of nozzle shell. The nozzles at all levels are isolated among different channels by the aid of the red copper gaskets between the extrusion parts, and during production, the threaded connection structure and the red copper gaskets can be omitted, and the nozzles at all levels are isolated by welding. In the working process, the design of the oxygen-fuel ratio of 1: 2 to 2: 1 and can adjust the nozzle to spray 1/2 and 3/4 of the maximum flow.

The invention also provides an engine, and the top of the engine is provided with the coaxial wide-range flow and mixing ratio adjusting injector.

Secondly, the invention discloses an installation method of a coaxial type large-range flow and mixing ratio adjusting injector, which comprises the following steps:

firstly, the connection of the injector shell 6 with the pipeline and the valve can use a welding method, and the installation sequence does not exist, and only the welding strength is required to meet the requirement; the main points to be emphasized are the connection of the composite nozzle 8, the ejector partition plates 7 of all stages and the ejector shell 6 and the installation process of the composite nozzle 8;

the composite nozzle 8 is installed in stages, firstly, a sealing gasket 11 is placed between a first-stage nozzle 9 and a second-stage nozzle 10, then, an external thread of the first-stage nozzle 9 and an internal thread of the second-stage nozzle 10 are screwed, and the connection and the sealing of the two-stage nozzle are completed; subsequently, according to the mounting method, the tertiary nozzles 12 and the quaternary nozzles 13 are sequentially mounted.

Alternatively, the external thread of the upper nozzle and the internal thread of the lower nozzle can be replaced by an optical axis and a unthreaded hole structure which are in clearance fit, and the connection can be completed by using a welding method after installation.

The injector was installed as follows:

firstly, taking an injector clapboard 7 to be arranged in an injector shell 6, and connecting the injector clapboard and the injector shell by using a welding method after a propellant collecting cavity A18 is formed;

the composite nozzle 8 is placed in a hole reserved in the partition plate 7 of the injector, and when the position is adjusted to ensure that the propellant collecting cavity A18 is only connected with the nozzle outlet A22, the propellant collecting cavity A18 and the nozzle outlet A22 are connected by a welding method, and the good sealing of a welding seam is ensured;

then placing an injector clapboard 7 into an injector shell 6, wherein holes with the same positions are formed in the injector clapboard 7 and can be sleeved with a composite nozzle 8, at the moment, moving the injector clapboard 7 to form a propellant collecting cavity B19 and ensuring that the propellant collecting cavity B19 is only connected with a nozzle outlet B23, and at the moment, completing connection by welding and ensuring sealing;

repeating the above process to complete the welding of the other two injector clapboards 7;

at this point, the injector assembly is complete.

The invention discloses another installation method of a coaxial injector for adjusting large-range flow and mixing ratio, which comprises the following steps:

firstly, welding the first injector partition 7 by using the same method as the method 1, and connecting the primary nozzle 9 and the secondary nozzle 10 in the composite nozzle 8 without using a welding method; then, welding of the injector partition 7 and the first two stages of nozzles is completed;

sleeving a sealing gasket 11 on the secondary nozzle 10, and completing the connection of the tertiary nozzle 12 and the secondary nozzle 10;

the installation of the secondary injector baffle 7 is completed according to the method mentioned in the installation method 1;

sleeving a sealing gasket 11 on the third-stage nozzle 12, and connecting the fourth-stage nozzle 13 with the second-stage nozzle 12;

according to the method mentioned in the installation method 1, the installation of the three-stage and four-stage injector partition plates 7 is completed;

at this point, the injector assembly is complete.

The injector may be attached to the engine using a more conventional flange connection or welding.

The use method of the coaxial injector for adjusting the large-range flow and the mixing ratio comprises the following steps:

the strategy of fuel entering from propellant inlet B15 and propellant inlet D17 and oxidizer entering from propellant inlet A14 and propellant inlet C16 is adopted, assuming that the initial working condition is that oxidizer and fuel are sprayed out from one nozzle outlet respectively, and the pressure drop of the two nozzles is moderate, namely preferably about 1 MPa. This condition is denoted as condition A.

Under condition a, valve a1 is controlled to open, and oxidant and fuel flow out of nozzle outlet C24 and nozzle outlet D25, respectively; in this case, the outlet of the single composite nozzle only has one mixing surface, and the mixing effect is similar to that of a common coaxial shearing nozzle.

The control valve A1 and the control valve C2 are functionally equivalent, and C2 can be closed. Control valve B5 is functionally equivalent to control valve D4, and control valve D4 may be closed, with only propellant inlet C16 and propellant inlet D17.

When the working condition of the rocket needs to be adjusted up in a large range to ensure that the oxygen-fuel ratio is unchanged, the working condition A is changed into the working condition B. The total flow of the working condition B is several times of that of the working condition A, can be higher than the working condition A by 200 percent, and has the same oxygen-fuel ratio. Control valve a1 and control valve B5 were opened, at which time the four propellant inlets were open, at which time propellant flowed from nozzle outlet a22, nozzle outlet B23, nozzle outlet C24 and nozzle outlet D25; at the moment, three blending surfaces appear, and the blending effect is more prominent.

When the working condition of the rocket needs to be adjusted downwards in a large range to ensure that the oxygen-fuel ratio is unchanged, the working condition A is changed into the working condition C. The total flow of the working condition C is a part of the working condition A, can be lower than 50 percent of the working condition A, and has the same oxygen-fuel ratio. At this time, the flow rate is adjusted by adjusting the nozzle inlet pressure. At the moment, the oxidant and the fuel still respectively flow out from the nozzle outlet C24 and the nozzle outlet D25, but the mixing effect is lower than that of the working condition A due to the fact that the pressure drop of the nozzle outlet is reduced, and the pressure drop of the nozzle under the working condition B is about 0.5MPa considering that the design requirement of the working condition A reaches more than 1MPa, and the mixing atomization effect can also be guaranteed.

When the working condition of the rocket needs to keep the total flow unchanged and only the oxygen-fuel ratio is adjusted upwards, the working condition A is changed into the working condition D. The total flow of the working condition D is the same as that of the working condition A, and the oxygen-fuel ratio of the working condition D is multiple times of that of the working condition A, so that the total flow of the working condition D can reach 280% of that of the working condition A, and is even higher. Opening control valve A1 and control valve B5, and closing control valve D4, wherein propellant inlet A14, propellant inlet B15 and propellant inlet C16 are opened, and propellant flows out from nozzle outlet A22, nozzle outlet B23 and nozzle outlet C24; at the moment, two mixing surfaces appear at the outlet of a single composite nozzle, and the mixing effect is higher than that of a common coaxial nozzle.

When the working condition of the rocket needs to keep the total flow unchanged and only the oxygen-fuel ratio is adjusted downwards, the working condition A is changed into the working condition E. The total flow of the working condition E is the same as that of the working condition A, and the oxygen-fuel ratio of the working condition E is 50% or even lower than that of the working condition A. At this point, propellant inlet B15, propellant inlet C16, propellant inlet D17 are open, and propellant flows from nozzle outlet B23, nozzle outlet C24 and nozzle outlet D25; and at the moment, two mixing surfaces still appear at the outlet of the single composite nozzle, and the mixing effect is higher than that of the common coaxial nozzle.