Central swirl - dual coaxial shear injector

Abstract

The application relates to the field of aerospace technology, in particular to a center rotational flow-double coaxial shearing injector. The center rotational flow-double coaxial shearing injector comprises a shell; a first channel for conducting a first propellant and a first channel and a second channel for conducting a second propellant are formed in the shell; the leading-out part of the first channel is formed between the first channel and the second channel; the application has three outlets, the outlet for conducting the first propellant is located between the two outlets for conducting the second propellant, that is, the two sides of the leading-out first propellant will be in contact with the second propellant and participate in the reaction; compared with the injector structure with two outlets in the prior art, the combustion area of the application is obviously increased, the combustion efficiency can be obviously improved, the length required for complete combustion is shortened, and the design length of the gas-gas combustion chamber when working under the conditions of large flow and significant deviation from the equivalent mixture ratio is shortened.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a central vortex-dual coaxial shear injector. Background Technology

[0002] Currently, since gas-to-gas combustion does not require atomization or evaporation processes, gas-to-gas injectors often adopt the form of coaxial shear direct current injection, which has advantages such as simple structure and stable combustion.

[0003] However, when gas-gas combustion is applied to high-flow-rate conditions or conditions that deviate significantly from the equivalence mixture ratio (oxygen-rich conditions, fuel-rich conditions), the existing injectors only have a single contact surface for the reaction, resulting in poor mixing of fuel and oxidant. This leads to a significant increase in the length required for complete combustion, which in turn causes problems such as a large increase in combustion chamber volume and weight.

[0004] Therefore, there is an urgent need for a central vortex-dual coaxial shear injector to address, to some extent, the technical problems existing in the current technology. Summary of the Invention

[0005] The purpose of this application is to provide a central swirl-dual coaxial shear injector to solve, to some extent, the technical problem of existing injectors having only a single contact surface for reaction and poor mixing effect of fuel and oxidant.

[0006] This application provides a central vortex-dual coaxial shear injector, including a housing;

[0007] The housing has a first channel for conducting the first propellant and a second channel for conducting the second propellant.

[0008] The second channel has at least two channels;

[0009] The outlet portion of the first channel is formed between the outlet portions of adjacent second channels, so that both sides of the first propellant outletped by the outlet portion of the first channel can react with the second propellant outletped by the outlet portion of the second channel.

[0010] In the above technical solution, the inlet portion of the first channel is further formed in the radial direction of the housing;

[0011] The inlet portion, which is connected to a plurality of second channels, is formed in the axial direction of the housing.

[0012] In the above technical solution, the central vortex-dual coaxial shear injector further includes a vortex component, an inner shaft, a central shaft, and an inlet component disposed on the vortex component, which can serve as an inlet portion communicating with multiple second channels;

[0013] The swirl component, the inner shaft, and the central shaft are sequentially sleeved along the radial direction of the housing;

[0014] At least one second channel is formed in the swirl member along the axial direction of the housing, and at least another second channel includes a first section formed by the upper part of the housing and the central axis, a second section formed along the central axis along the axial direction, and a third section formed by the lower part of the housing and the central axis;

[0015] The first channel includes an inlet channel that extends radially through the housing and the central axis, serving as an inlet portion of the first channel, and a portion formed between the inner axis and the central axis.

[0016] In the above technical solution, the housing further includes a top cover and an outer shell that interlock and enclose an installation space;

[0017] The inlet component is connected to the top cover; the outlet portion of the second channel is connected to the end of the outer shell away from the top cover;

[0018] The inlet channel extends through the outer shell and the central axis in the radial direction of the outer shell, and the outlet portion of the first channel is connected to the end of the outer shell away from the top cover.

[0019] In the above technical solution, the inner shaft further includes a first receiving portion having a first receiving space and a preset distance from the top cover, and a first straight-through portion communicating with the first receiving portion and communicating with the end of the outer shell away from the top cover.

[0020] The swirling component is disposed in the first receiving portion, and the inlet component is disposed in the preset distance segment; one end of the swirling component is connected to the inlet component, and the other end is connected to the first straight portion, and the part connected to the first straight portion is the outlet portion of the second channel; so that the swirling component forms one of the second channels along the axial direction of the outer shell, so that the second propellant can pass through the top cover, the inlet component and the second channel in sequence.

[0021] In the above technical solution, the inlet component further includes a cylinder; the circumferential sidewall of the cylinder is provided with first through holes spaced apart.

[0022] The swirling component includes a straight cylinder with one end connected to the cylindrical part and the other end connected to the first straight passage, and a limiting ring sleeved on the straight cylinder; the straight cylinder is engaged with the first receiving space by the limiting ring; swirling holes are spaced apart on the side wall of the straight cylinder;

[0023] The second propellant introduced into the cylinder through the top cover can be introduced into the first receiving space through the first through hole, and the second propellant in the first receiving space can be introduced into the interior of the straight cylinder and the first straight section in sequence.

[0024] In the above technical solution, the first receiving portion is truncated cone-shaped and tapers from the top cover to the bottom of the outer shell;

[0025] The axis of the swirling hole is at a preset angle to the radial direction of the straight cylinder.

[0026] In the above technical solution, the central axis further includes a second receiving portion having a second receiving space and a second straight-through portion communicating with the second receiving portion and communicating with the end of the outer shell away from the top cover;

[0027] The first receiving portion is disposed in the second receiving space and has a flow space with the second receiving space; the first straight portion is disposed in the second straight portion and a conductive gap is formed between the first straight portion and the second straight portion, which can serve as the outlet portion of the first channel.

[0028] The second receiving portion has a second through hole spaced apart on its side wall, which extends radially along the second receiving portion. The outer shell has a third through hole on its side wall. The path from the second through hole to the third through hole constitutes the inlet channel, so that the first propellant can pass through the third through hole, the second through hole, the flow space, and the through gap in sequence.

[0029] In the above technical solution, the outer shell further includes a third accommodating space, the second accommodating part is disposed in the third accommodating space, and there is a flow gap between the bottom of the second accommodating part and the outer shell that can serve as an outlet portion of the second channel;

[0030] The side wall of the second receiving part is provided with a fourth through hole that extends along the axial direction of the second receiving part and communicates with the preset distance segment;

[0031] The second propellant introduced into the cylinder through the top cover can be introduced into the preset distance segment through the first through hole to form the first segment, the second propellant is guided through the preset distance segment to the fourth through hole to form the second segment, and the second propellant is guided through the fourth through hole to the flow gap to form the third segment.

[0032] In the above technical solution, the central vortex-dual coaxial shear injector further includes an outer shaft;

[0033] The second receiving portion is engaged with the third receiving space via the outer shaft;

[0034] A sealing ring is provided between the outer shaft and the top cover, the outer shell, and the second receiving part, respectively.

[0035] Compared with the prior art, the beneficial effects of this application are as follows:

[0036] The central swirl-dual coaxial shear injector provided in this application includes a housing; a first channel for guiding a first propellant and a first second channel and a second second channel for guiding a second propellant are formed within the housing; specifically, the outlet of the first channel is formed between the first second channel and the second second channel; this can be understood as the present application having three outlets, with the outlet for guiding the first propellant located between the two outlets for guiding the second propellant, meaning that both sides of the exported first propellant will contact the second propellant and participate in the reaction; compared to the prior art central swirl-dual coaxial shear injector structure with two outlets (one outlet for guiding the first propellant and the other outlet for guiding the second propellant) (where the first propellant and the second propellant have only one contact surface), the combustion area of ​​the present application is significantly increased, which can significantly improve combustion efficiency, shorten the length required for complete combustion, and thus shorten the design length of the gas-gas combustion chamber when operating under conditions such as high flow rate and significant deviation from the equivalence mixture ratio. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0038] Figure 1 A schematic diagram of the central vortex-dual coaxial shear injector provided in an embodiment of this application from a first-view perspective;

[0039] Figure 2 A schematic diagram of the central vortex-dual coaxial shear injector provided in the embodiment of this application from a second perspective;

[0040] Figure 3 A cross-sectional view of the central vortex-dual coaxial shear injector provided in an embodiment of this application;

[0041] Figure 4 This is a schematic diagram of the hidden top cover of the center vortex-dual coaxial shear injector provided in an embodiment of this application;

[0042] Figure 5A schematic diagram of the structure of the central vortex-dual coaxial shear injector with a hidden housing provided in an embodiment of this application, viewed from a first perspective.

[0043] Figure 6 A schematic diagram of the structure of the central vortex-dual coaxial shear injector with a hidden housing provided in an embodiment of this application, viewed from a second perspective;

[0044] Figure 7 This is a schematic diagram of the hidden housing and outer shaft of the central vortex-dual coaxial shear injector provided in an embodiment of this application.

[0045] Figure 8 A schematic diagram of the inner shaft, swirling fluid, and inlet component in the central vortex-dual coaxial shear injector provided in the embodiments of this application, viewed from a first perspective.

[0046] Figure 9 A schematic diagram of the inner shaft, swirling fluid, and inlet component in the central vortex-dual coaxial shear injector provided in the embodiments of this application, viewed from a second perspective.

[0047] Figure 10 A cross-sectional view of the inner shaft, swirling fluid, and inlet component in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0048] Figure 11 A cross-sectional view of the swirling fluid and the inlet component in the central swirling-dual coaxial shear injector provided in an embodiment of this application;

[0049] Figure 12 This is a schematic diagram of the top cover structure in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0050] Figure 13 This is a schematic diagram of the outer shell of the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0051] Figure 14 A cross-sectional view of the housing in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0052] Figure 15 A schematic diagram of the central axis in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0053] Figure 16 A cross-sectional view of the central axis in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0054] Figure 17 This is a schematic diagram of the inner shaft structure in the central vortex-dual coaxial shear injector provided in the embodiments of this application;

[0055] Figure 18This is a cross-sectional view of the inner shaft in the central vortex-dual coaxial shear injector provided in an embodiment of this application.

[0056] Figure 19 This is a schematic diagram of the swirling fluid in the central swirling-dual coaxial shear injector provided in the embodiments of this application;

[0057] Figure 20 This is a wiring diagram of the channels in the central vortex-dual coaxial shear injector provided in the embodiments of this application.

[0058] Figure label:

[0059] 2-Top cover; 3-Outer shell; 4-First channel; 5-Second channel No. 1; 6-Second channel No. 2; 7-Swirl component; 8-Inner shaft; 9-Central shaft; 10-Introducing component; 11-First accommodating space; 12-Preset distance section; 13-First accommodating part; 14-First straight through part; 15-Cylinder; 16-First guide hole; 17-Straight cylinder; 18-Limiting ring; 19-Swirl hole; 20-Second accommodating space; 21-Second accommodating part; 22-Second straight through part; 23-Flow space; 24-Guiding gap; 25-Second guiding hole; 26-Third guiding hole; 27-Third accommodating space; 28-Flow gap; 29-Fourth guiding hole; 30-Outer shaft; 31-Sealing ring; 32-Introducing gap. Detailed Implementation

[0060] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of this application, but not all embodiments.

[0061] The components of the embodiments of this application described and shown in the accompanying drawings can be arranged and designed in a variety of different configurations. Therefore, the following detailed description of the embodiments of this application provided in the drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application.

[0062] Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0063] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0064] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0065] The following reference Figures 1 to 20 This application describes a center vortex-dual coaxial shear injector according to an embodiment of the present application.

[0066] The central vortex-dual coaxial shear injector provided in this application includes a housing; a first channel 4 for guiding a first propellant and a first second channel 5 and a second second channel 6 for guiding a second propellant are formed inside the housing; specifically, the outlet of the first channel 4 is formed between the first second channel 5 and the second second channel 6.

[0067] In summary, this application can be understood as having three outlets. The outlet for guiding the first propellant is located between the two outlets for guiding the second propellant. In other words, both sides of the first propellant can contact the second propellant and participate in the reaction. Compared with the injector structure in the prior art that has two outlets (one outlet for guiding the first propellant and the other outlet for guiding the second propellant) (the first propellant and the second propellant have only one contact surface), the combustion area of ​​this application is significantly increased, which can significantly improve the combustion efficiency, shorten the length required for complete combustion, and thus shorten the design length of the gas-gas combustion chamber when operating under conditions such as high flow rate and significant deviation from the equivalence mixture ratio.

[0068] In this embodiment, the inlet portion of the first channel 4 is formed in the radial direction of the housing; the inlet portion shared by the first second channel 5 and the second second channel 6 is formed in the axial direction of the housing.

[0069] In this embodiment, the central vortex-dual coaxial shear injector includes a vortex member 7, an inner shaft 8, a central shaft 9, and an inlet member 10 disposed on the vortex member 7, which can serve as an inlet portion shared with the first second channel 5 and the second second channel 6.

[0070] Specifically, the swirl component 7, the inner shaft 8, and the central shaft 9 are sequentially fitted from the inside to the outside along the radial direction of the shell.

[0071] Specifically, the first second channel 5 is formed on the swirl member 7 along the axial direction of the shell, and the second second channel 6 includes a first section formed by the upper part of the shell and the central axis 9, a second section formed along the central axis 9 along the axial direction, and a third section formed by the lower part of the shell and the central axis 9.

[0072] Specifically, the first channel 4 includes an inlet channel that extends radially through the housing and the central shaft 9, which can serve as an inlet portion of the first channel 4, and a portion formed between the inner shaft 8 and the central shaft 9.

[0073] In summary, for the first propellant, it is first introduced into the shell along the radial direction of the shell. The first propellant passes through the central axis 9 and exits from the portion formed between the inner axis 8 and the central axis 9. For the second propellant, it is introduced into the shell through the introduction member 10. Then, a portion of the second propellant exits the shell through the swirl member 7. This portion of the second propellant will contact and burn with the side of the first propellant near the centerline of the shell. Another portion of the second propellant exits the shell sequentially through the first section, the second section, and the third section. This portion of the second propellant will contact and burn with the side of the first propellant away from the centerline.

[0074] In addition, the swirl component in this application can further shorten the complete combustion length, thereby shortening the design length of the gas-gas combustion chamber when operating under conditions such as high flow rate and significant deviation from equivalence mixture ratio.

[0075] In this embodiment, the housing includes a top cover 2 and an outer shell 3 that interlock and enclose an installation space.

[0076] Specifically, the inlet component 10 is connected to the top cover 2, meaning that the second propellant can be introduced into the inlet component 10 through the top cover 2; the outlet of the second channel is connected to the end of the outer shell 3 away from the top cover 2, meaning that the second propellant will eventually be exported through the bottom of the outer shell 3.

[0077] Specifically, the inlet channel runs through the outer shell 3 and the central shaft 9 in the radial direction of the outer shell 3, and the outlet part of the first channel 4 is connected to the end of the outer shell 3 away from the top cover 2.

[0078] In this embodiment, the inner shaft 8 includes a first receiving portion 13 having a first receiving space 11 and a preset distance segment 12 between it and the top cover 2 (as will be known below, this preset distance segment 12 is formed because the middle shaft 9 is a certain distance from the top cover 2 when the outer shaft 30 is engaged with the middle shaft 9 inside the outer shell 3), and a first straight-through portion 14 communicating with the first receiving portion 13 and communicating with the end of the outer shell 3 away from the top cover 2;

[0079] Specifically, the first receiving portion 13 is frustum-shaped and tapers from the top cover 2 to the bottom of the outer shell 3; or the central axis 9 having the first receiving portion 13 and the first through portion 14 can be understood as a funnel-like structure.

[0080] Specifically, the swirling member 7 is disposed in the first receiving portion 13 and has an inlet gap 32 between it and the first receiving portion 13; the inlet member 10 is disposed in the preset distance segment 12; one end of the swirling member 7 is connected to the inlet member 10, and the other end is connected to the first straight through portion 14 and the part connected to the first straight through portion 14 is the outlet portion of the second channel.

[0081] Furthermore, the inlet component 10 includes a cylinder 15; a first through hole 16 is provided at intervals on the circumferential sidewall of the cylinder 15, that is, the second propellant guided to the cylinder 15 through the top cover 2 will diffuse within the preset distance section 12 and the inlet gap 32 through the first through hole 16, and the second propellant diffused into the inlet gap 32 will enter the first channel 4. As will be understood below, the setting of this preset distance section 12 provides the possibility for the second propellant introduced into the outer shell 3 through the inlet component 10 to be divided into two paths.

[0082] Furthermore, the swirl component 7 includes a straight cylinder 17 with one end connected to the cylinder 15 and the other end connected to the first through part 14, and a limiting ring 18 sleeved on the straight cylinder 17; the straight cylinder 17 is engaged with the first receiving space 11 by the limiting ring 18; swirl holes 19 are spaced apart on the side wall of the straight cylinder 17.

[0083] Furthermore, the axis of the swirl orifice 19 forms a predetermined angle with the radial direction of the straight cylinder 17; preferably, the predetermined angle is 60°. This arrangement of the swirl orifice 19, compared to the conventional direct-flow propellant which has a very high axial velocity but almost no radial velocity, allows the gas to have a large radial velocity during ejection, promoting mixing between the gas phases and facilitating more complete combustion.

[0084] In summary, the first second channel 5 is formed by the inlet member 10, the swirl member 7, and the first straight section 14; the second propellant is introduced into the inlet member 10 through the top cover 2, and the inlet member 10 will introduce a part of the second propellant into the inlet gap 32, and then through the swirl member 7 into the first straight section 14, thereby realizing the export of a part of the second propellant.

[0085] In this embodiment, the central shaft 9 includes a second receiving portion 21 having a second receiving space 20 and a second through portion 22 communicating with the second receiving portion 21 and communicating with the end of the outer casing 3 away from the top cover 2.

[0086] Specifically, the first receiving part 13 is disposed in the second receiving space 20 and has a flow space 23 with the second receiving space 20, and the first straight part 14 is disposed in the second straight part 22 and has a connecting gap 24 between it and the second straight part 22 that can serve as the outlet part of the first channel 4.

[0087] Specifically, the sidewall of the second receiving portion 21 is provided with a second through hole 25 extending in the radial direction of the second receiving portion 21, and the sidewall of the outer casing 3 is provided with a third through hole 26. The path from the second through hole 25 to the third through hole 26 forms an inlet channel.

[0088] In summary, the first propellant can pass sequentially through the first channel 4, which is composed of the third through hole 26, the second through hole 25, the flow space 23, and the through gap 24.

[0089] In this embodiment, the outer casing 3 has a third receiving space 27, a second receiving portion 21 is disposed in the third receiving space 27, and there is a flow gap 28 between the bottom of the second receiving portion 21 and the outer casing 3, which can serve as a discharge portion for a second channel.

[0090] Specifically, the side wall of the second receiving portion 21 is provided with a fourth through hole 29 that extends along the axial direction of the second receiving portion 21 and communicates with the preset distance segment 12.

[0091] It is worth noting that the second through hole 25 and the fourth through hole 29 are arranged alternately and do not have any specific purpose, thus preventing the first propellant passing through the second through hole from contacting and burning with the second propellant passing through the fourth through hole.

[0092] In summary, the second propellant introduced into the cylinder 15 through the top cover 2 can be introduced into the preset distance segment 12 through the first through hole 16 to form the first segment. The second propellant is guided through the preset distance segment 12 to the fourth through hole 29 to form the second segment. The second propellant is guided through the fourth through hole 29 to the flow gap 28 to form the third segment. That is, the second propellant introduced into the cylinder 15 through the top cover 2 is guided to the preset distance segment 12 through the first through hole 16, diffuses within the preset distance segment 12, then is guided through the fourth through hole within the central axis 9, and finally is discharged through the flow gap 28.

[0093] In this embodiment, the central vortex-dual coaxial shear injector further includes an outer shaft 30; the second receiving portion 21 is engaged with the third receiving space 27 via the outer shaft 30.

[0094] Specifically, sealing rings 31 are provided between the outer shaft 30 and the top cover 2, the outer shell 3 and the second receiving part, respectively.

[0095] In addition, sealing rings 31 are also provided between the central shaft 9 and the outer shell 3, and between the central shaft 9 and the inner shaft 8.

[0096] In summary, the sealing ring 31 is used to seal the first and second propellants inside the shell, preventing them from coming into contact and burning inside the shell.

[0097] In addition, the outer shaft, middle shaft, inner shaft, swirl component and inlet component in this application are all detachable structures, and the size of each component can be determined according to the actual working conditions to change the diameter of the first channel and the second channel, thereby changing the fuel blending ratio.

[0098] In addition, the swirl component of this application is provided with swirl holes. To meet the requirements of certain working conditions, the direct current holes can be used instead of the swirl holes.

[0099] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A central vortex-dual coaxial shear injector, characterized in that, Includes the casing; The housing has a first channel for conducting the first propellant and a second channel for conducting the second propellant. The second channel has at least two channels; The outlet portion of the first channel is formed between the outlet portions of adjacent second channels, so that both sides of the first propellant outletped from the outlet portion of the first channel can react with the second propellant outletped from the outlet portion of the second channel; The inlet portion of the first channel is formed in the radial direction of the housing; The inlet portion, which is connected to multiple second channels, is formed in the axial direction of the housing; The central vortex-dual coaxial shear injector includes a vortex component, an inner shaft, a central shaft, and an inlet component disposed on the vortex component, which can serve as an inlet portion communicating with multiple second channels. The swirl component, the inner shaft, and the central shaft are sequentially sleeved along the radial direction of the housing; At least one second channel is formed in the swirl member along the axial direction of the housing, and at least another second channel includes a first section formed by the upper part of the housing and the central axis, a second section formed along the central axis along the axial direction, and a third section formed by the lower part of the housing and the central axis; The first channel includes an inlet channel that extends radially through the housing and the central axis, serving as an inlet portion of the first channel, and a portion formed between the inner axis and the central axis.

2. The central vortex-dual coaxial shear injector according to claim 1, characterized in that, The housing includes a top cover and an outer shell that interlock and enclose an installation space; The inlet component is connected to the top cover; the outlet portion of the second channel is connected to the end of the outer shell away from the top cover; The inlet channel extends through the outer shell and the central axis in the radial direction of the outer shell, and the outlet portion of the first channel is connected to the end of the outer shell away from the top cover.

3. The central vortex-dual coaxial shear injector according to claim 2, characterized in that, The inner shaft includes a first receiving portion having a first receiving space and a predetermined distance from the top cover, and a first straight-through portion communicating with the first receiving portion and connected to the end of the outer shell away from the top cover. The swirling component is disposed in the first receiving portion, and the inlet component is disposed in the preset distance segment; one end of the swirling component is connected to the inlet component, and the other end is connected to the first straight portion, and the part connected to the first straight portion is the outlet portion of the second channel; so that the swirling component forms one of the second channels along the axial direction of the outer shell, so that the second propellant can pass through the top cover, the inlet component and the second channel in sequence.

4. The central vortex-dual coaxial shear injector according to claim 3, characterized in that, The inlet component includes a cylinder; a first through hole is provided at intervals on the circumferential sidewall of the cylinder; The swirling component includes a straight cylinder with one end connected to the cylindrical part and the other end connected to the first straight section, and a limiting ring sleeved on the straight cylinder; the straight cylinder is engaged with the first receiving space by the limiting ring; The sidewall of the straight cylinder is provided with swirling holes spaced apart; The second propellant introduced into the cylinder through the top cover can be introduced into the first receiving space through the first through hole, and the second propellant in the first receiving space can be introduced into the interior of the straight cylinder and the first straight section in sequence.

5. The central vortex-dual coaxial shear injector according to claim 4, characterized in that, The first receiving portion is frustum-shaped and tapers from the top cover to the bottom of the outer shell; The axis of the swirling hole is at a preset angle to the radial direction of the straight cylinder.

6. The central vortex-dual coaxial shear injector according to claim 5, characterized in that, The central axis includes a second receiving portion having a second receiving space and a second straight portion communicating with the second receiving portion and connected to one end of the outer shell away from the top cover; The first receiving portion is disposed in the second receiving space and has a flow space with the second receiving space; the first straight portion is disposed in the second straight portion and a conductive gap is formed between the first straight portion and the second straight portion, which can serve as the outlet portion of the first channel. The second receiving portion has a second through hole spaced apart on its side wall, which extends radially along the second receiving portion. The outer shell has a third through hole on its side wall. The path from the second through hole to the third through hole constitutes the inlet channel, so that the first propellant can pass through the third through hole, the second through hole, the flow space, and the through gap in sequence.

7. The central vortex-dual coaxial shear injector according to claim 6, characterized in that, The outer casing has a third receiving space, the second receiving part is disposed in the third receiving space and there is a flow gap between the bottom of the second receiving part and the outer casing that can serve as the outlet of the second channel; The side wall of the second receiving part is provided with a fourth through hole that extends along the axial direction of the second receiving part and communicates with the preset distance segment; The second propellant introduced into the cylinder through the top cover can be introduced into the preset distance segment through the first through hole to form the first segment, the second propellant is guided through the preset distance segment to the fourth through hole to form the second segment, and the second propellant is guided through the fourth through hole to the flow gap to form the third segment.

8. The central vortex-dual coaxial shear injector according to claim 7, characterized in that, The central vortex-dual coaxial shear injector also includes an outer shaft; The second receiving portion is engaged with the third receiving space via the outer shaft; A sealing ring is provided between the outer shaft and the top cover, the outer shell, and the second receiving part, respectively.

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