CN216714560U - Injector, engine and aircraft - Google Patents
Injector, engine and aircraft Download PDFInfo
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- CN216714560U CN216714560U CN202220442130.0U CN202220442130U CN216714560U CN 216714560 U CN216714560 U CN 216714560U CN 202220442130 U CN202220442130 U CN 202220442130U CN 216714560 U CN216714560 U CN 216714560U
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Abstract
The utility model relates to the technical field of space equipment, in particular to an injector, an engine and an aircraft. The injector comprises: one end of the oxidant channel is communicated with the oxidant inlet, and the other end of the oxidant channel is communicated with the oxidant injection hole, so that an oxidant path is formed; one end of the fuel flow passage is communicated with the fuel inlet, and the other end of the fuel flow passage is communicated with the fuel injection hole, so that a fuel path is formed; the fuel flow channel is circumferentially arranged relative to the oxidant flow channel; the oxidant injection holes and the fuel injection holes are arranged in a one-to-one correspondence manner. According to the injector provided by the utility model, the internal runner structures of the oxidant path and the fuel path are integrated into a whole through integral forming, so that the overall structure and the production and manufacturing process of the injector are greatly simplified, the influence on the production and manufacturing precision in the assembling and welding processes is avoided, the production cost is reduced, and the production efficiency of the injector is improved.
Description
Technical Field
The utility model relates to the technical field of space equipment, in particular to an injector, an engine and an aircraft.
Background
The injector is an important part for determining the performance of the rocket engine, and the impact injector can improve the atomization and mixing effects of the propellant, wherein the oxygen-combustion mutual-impact injector can realize the forced mixing of the oxidant and the fuel, is favorable for improving the combustion efficiency, and is widely applied to the rocket engine.
The conventional impact injector is complex in structure and mostly formed by combining different parts, and the different parts need to be matched and assembled, so that the whole production and manufacturing process of the injector is complicated, and the requirements on the matched size, tolerance and the like are high; meanwhile, means such as welding are needed for connection among different parts, part deformation is inevitably caused by heat input in the welding process, and assembly and critical dimension are affected.
SUMMERY OF THE UTILITY MODEL
Therefore, the technical problem to be solved by the present invention is to overcome the defects of complicated structure and difficult control of production and manufacturing precision of the injector in the prior art, thereby providing an injector with simple structure and easy control of production and manufacturing precision.
In order to solve the above technical problem, the present invention provides an injector, comprising:
one end of the oxidant channel is communicated with the oxidant inlet, and the other end of the oxidant channel is communicated with the oxidant injection hole;
one end of the fuel channel is communicated with the fuel inlet, and the other end of the fuel channel is communicated with the fuel injection hole;
the fuel flow channel is circumferentially arranged relative to the oxidant flow channel;
the oxidant injection holes and the fuel injection holes are arranged in a one-to-one correspondence mode.
Optionally, the fuel flow path comprises a first fuel flow section and a second fuel flow section; the second fuel flow segment is coincident with the axis of the oxidant flow channel, the first fuel flow segment and the second fuel flow segment forming a predetermined angle; said first fuel stream section adapted to communicate with said fuel inlet; the second fuel flow segment is adapted to communicate with the fuel injection orifice.
Optionally, the second fuel flow section comprises an upper fuel chamber and a lower fuel chamber, and the upper fuel chamber is communicated with the lower fuel chamber; the upper fuel cavity is adapted to communicate with the first fuel flow section and the lower fuel cavity is adapted to communicate with the fuel injection orifice.
Optionally, rounded corners and/or dome structures are provided inside the oxidant flow channels and the fuel flow channels.
Optionally, the injector further comprises a flow equalizing hole, and the upper fuel cavity and the lower fuel cavity are communicated through the flow equalizing hole.
Optionally, the fuel injection hole is disposed in an outer ring layer of the oxidant injection hole.
Optionally, the extending direction of the axis of the oxidant injection hole and the extending direction of the axis of the fuel injection hole intersect at the lower end of the injector and form a preset angle.
Optionally, the injector is integrally formed or 3D printed.
The present invention also provides an engine comprising: the injector comprises an engine body and the injector.
The utility model also provides an aircraft comprising: an aircraft body, and the engine described above.
The technical scheme of the utility model has the following advantages:
1. the present invention provides an injector comprising: one end of the oxidant channel is communicated with the oxidant inlet, and the other end of the oxidant channel is communicated with the oxidant injection hole, so that an oxidant path is formed; one end of the fuel channel is communicated with the fuel inlet, and the other end of the fuel channel is communicated with the fuel injection hole, so that a fuel path is formed; the fuel flow channel is circumferentially arranged relative to the oxidant flow channel; the oxidant injection holes and the fuel injection holes are arranged in a one-to-one correspondence manner; the injector integrates the internal flow passage structures of the oxidant path and the fuel path into a whole through integral forming, so that the overall structure and the production and manufacturing process of the injector are greatly simplified, the influence on the production and manufacturing precision in the assembling and welding processes is avoided, the production cost is reduced, and the production efficiency of the injector is improved.
2. The injector provided by the utility model is provided with a fuel flow channel, wherein the fuel flow channel comprises a first fuel flow section and a second fuel flow section; the second fuel flow section is coincident with the axis of the oxidant flow channel, and the first fuel flow section forms a preset angle with the second fuel flow section; the second fuel flow section comprises an upper fuel cavity and a lower fuel cavity; in the design and production process, the preset angle is adjusted, so that the injector can meet different actual space structure requirements, and the applicability of the injector is improved.
3. According to the injector provided by the utility model, the fuel upper cavity and the fuel lower cavity are arranged to convert the lateral incoming flow in the first fuel flow section into the axial incoming flow parallel to the direction of the axis L1, so that the propellant sprayed by the fuel injection holes and the propellant sprayed by the oxidant injection holes are fully collided and mixed near the spraying port of the injector along the axis direction, the mixing effect of the propellant is enhanced, and efficient and stable combustion is realized.
4. The injector provided by the utility model also comprises a flow equalizing hole, wherein the fuel upper cavity is communicated with the fuel lower cavity through the flow equalizing hole; the number of the flow equalizing holes is multiple, and the flow equalizing holes are circumferentially and uniformly distributed relative to the axis of the oxidant flow channel; through setting up the flow equalizing hole the side direction comes to flow and converts into the in-process that the axial came for the propellant in the fuel upper chamber passes through the flow equalizing hole evenly shunts and lets in the fuel intracavity down, has improved the homogeneity of the structure of insufflator has guaranteed the high-efficient stable burning of propellant.
5. According to the injector provided by the utility model, the fuel flow channel is arranged around the peripheral wall of the oxidant flow channel, and the fuel flow channel and the oxidant flow channel are separated by the integrally formed wall surface; the oxidant injection hole is communicated with the oxidant runner; the fuel injection hole is communicated with the fuel flow channel; by disposing the fuel injection hole to an outer ring layer of the oxidant injection hole; the inner ring is the oxidant injection hole, and the outer ring is the injection structure of the fuel injection hole, so that an internal oxygen external combustion environment is formed in the combustion process, a certain film cooling effect can be achieved in rich combustion, and thermal protection of the wall surface of the combustion chamber is facilitated.
6. According to the injector provided by the utility model, the oxidant injection holes and the fuel injection holes are arranged in a one-to-one correspondence manner, each oxidant injection hole and the corresponding fuel injection hole form a pair of mutual-impacting holes at the injection port of the injector, and the pairs of mutual-impacting holes are circumferentially and uniformly distributed on the lower end surface of the injector relative to the axis of the oxidant runner; the extension direction of each oxidant injection hole axis and the extension direction of the fuel injection hole axis corresponding to the oxidant injection hole axis form the preset angle, so that the propellants can sufficiently collide, collide and mix near the injection hole of the injector, the efficient and stable combustion of the propellants in the combustion chamber is realized, and the combustion efficiency of the injector is improved.
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, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic cross-sectional view of an injector according to the present invention;
FIG. 2 is a schematic view showing the structure of an oxidant injection hole and a fuel injection hole of the injector according to the present invention;
fig. 3 is a schematic structural diagram of a flow equalizing hole of the injector of the present invention.
Description of reference numerals:
10. an oxidant inlet; 20. a fuel inlet; 31. a first oxidant flow section; 32. a second oxidant flow section; 41. a first fuel stream section; 42. a second fuel flow section; 421. a fuel upper chamber; 422. a lower fuel cavity; 50. an oxidant injection hole; 60. a fuel injection hole; 70. and (6) flow equalizing holes.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The present embodiment provides an injector, comprising:
one end of the oxidant channel is communicated with the oxidant inlet 10, and the other end of the oxidant channel is communicated with the oxidant injection hole 50;
a fuel flow passage having one end communicated with the fuel inlet 20 and the other end communicated with the fuel injection hole 60;
the fuel flow channel is circumferentially arranged relative to the oxidant flow channel;
the oxidant injection holes 50 are provided in one-to-one correspondence with the fuel injection holes 60.
Note that, the upper end face refers to an end face indicated by a in fig. 1; the lower end face refers to an end face indicated by B in fig. 1; the axis L1 of the oxidant flow passage passes through the center of the upper end surface A and is perpendicular to the upper end surface A; the first fuel flow section 41 and the second fuel flow section 42 form a preset angle, the preset angle is in the range of 0-180 degrees, and the preset angle can be adjusted according to actual use conditions, and is not limited to the conditions shown in the figures.
Optionally, an oxidant channel is arranged in the injector, one end of the oxidant channel is communicated with the oxidant inlet 10, and the other end of the oxidant channel is communicated with the oxidant injection hole 50; the oxidant inlet 10 is arranged on the upper end surface of the injector; the oxidant injection hole 50 is provided in a lower end surface of the injector.
Optionally, the injector is further provided with a fuel channel, one end of the fuel channel is communicated with the fuel inlet 20, and the other end of the fuel channel is communicated with the fuel injection hole 60; the fuel inlet 20 is arranged on one side end face of the injector; the fuel injection hole 60 is provided in a lower end surface of the injector.
Optionally, the oxidant injection holes 50 and the fuel injection holes 60 are arranged in a one-to-one correspondence manner, and each oxidant injection hole 50 and the fuel injection hole 60 corresponding to the oxidant injection hole form a pair of mutual injection holes at an injection port of the injector; the pairs of the mutual striking holes are circumferentially and uniformly distributed on the lower end face of the injector relative to the axis L1 of the oxidant flow passage.
Optionally, the oxidant inlet 10 and the fuel inlet 20 have the same structure, which is beneficial to the uniform matching of the upstream interface.
Referring to fig. 1, in the present embodiment, the injector includes: an oxidant passage, one end of which is communicated with the oxidant inlet 10 and the other end of which is communicated with the oxidant injection hole 50, thereby forming an oxidant path; a fuel flow passage having one end communicated with the fuel inlet 20 and the other end communicated with the fuel injection hole 60, thereby forming a fuel path; the fuel flow channel is circumferentially arranged relative to the oxidant flow channel; the oxidant injection holes 50 and the fuel injection holes 60 are arranged in a one-to-one correspondence; the injector integrates the internal flow passage structures of the oxidant path and the fuel path into a whole through integral forming, so that the overall structure and the production and manufacturing process of the injector are greatly simplified, the influence on the production and manufacturing precision in the assembling and welding processes is avoided, the production cost is reduced, and the production efficiency of the injector is improved.
Optionally, the oxidant flow path comprises a first oxidant flow section 31 and a second oxidant flow section 32; one end of the first oxidant flow section 31 is communicated with the oxidant inlet 10, the other end is communicated with one end of the second oxidant flow section 32, and the other end of the second oxidant flow section 32 is communicated with the oxidant injection hole 50.
Specifically, the fuel flow path includes a first fuel flow section 41 and a second fuel flow section 42; the second fuel flow section 42 coincides with the axis of the oxidant flow channel, and the first fuel flow section 41 and the second fuel flow section 42 form a preset angle; said first fuel flow section 41 is adapted to communicate with said fuel inlet 20; the second fuel flow section 42 is adapted to communicate with the fuel injection holes 60.
Optionally, the fuel injection holes 60 are circumferentially and uniformly distributed on the lower end surface of the injector with respect to the axis L1 of the oxidant flow passage.
Optionally, the fuel flow path includes a first fuel flow section 41 and a second fuel flow section 42; the second fuel flow segments 42 are disposed around the fuel flow channel peripheral wall with the axis of the second fuel flow segments 42 coincident with the axis L1 of the oxidant flow channels; the first fuel flow section 41 forms a preset angle with the second fuel flow section 42, and the first fuel flow section 41 communicates with the second fuel flow section 42;
during the operation of the injector, the fuel inlet 20 leads the propellant into the first fuel flow section 41, and the propellant is converted from a side incoming flow into an axial incoming flow in a direction parallel to the axis L1 of the oxidizer flow channel through the second fuel flow section 42, and then enters the combustion chamber through the fuel injection holes 60 which are uniformly distributed in the circumferential direction.
In the present embodiment, as shown in fig. 1, the injector is provided with a fuel flow passage including a first fuel flow section 41 and a second fuel flow section 42; the second fuel flow segments 42 are disposed around the fuel flow channel peripheral wall, the second fuel flow segments 42 are coincident with the axis of the oxidant flow channels, and the first fuel flow segments 41 form a predetermined angle with the second fuel flow segments 42; in the design and production process, the preset angle is adjusted, so that the injector can meet different actual space structure requirements, and the applicability of the injector is improved.
Specifically, the second fuel flow section 42 includes an upper fuel chamber 421 and a lower fuel chamber 422, and the upper fuel chamber 421 and the lower fuel chamber 422 are communicated with each other; the upper fuel cavity 421 is adapted to communicate with the first fuel flow section 41 and the lower fuel cavity 422 is adapted to communicate with the fuel injection holes 60.
Optionally, the second fuel flow section 42 comprises a fuel upper chamber 421 and a fuel lower chamber 422; the upper fuel chamber 421 is adapted to communicate the side-to-side flow in the first fuel flow section 41 into the lower fuel chamber 422 and into an axial flow parallel to the axis L1 of the oxidant flow path.
Referring to fig. 1, in this embodiment, the fuel upper cavity 421 and the fuel lower cavity 422 are arranged to convert the side incoming flow in the first fuel flow section 41 into an axial incoming flow parallel to the direction of the axis L1, so that the propellant ejected from the fuel injection holes 60 and the propellant ejected from the oxidant injection holes 50 are fully collided and blended in the vicinity of the ejection ports of the injector along the direction of the axis L1, thereby enhancing the blending effect of the propellant and realizing efficient and stable combustion.
Specifically, the oxidant flow channels and the fuel flow channels are internally provided with rounded corners and/or dome structures.
Optionally, fillets and/or dome structures are arranged inside the oxidant flow channel and the fuel flow channel, so that the process requirement of 3D printing is met, the process difficulty is reduced, the surface quality of the corresponding position of the inner wall of the flow channel is improved, and the flow resistance at a non-throttling hole in the flow channel is reduced.
Specifically, the injector further comprises a flow equalizing hole 70, and the fuel upper chamber 421 and the fuel lower chamber 422 are communicated through the flow equalizing hole 70.
Optionally, a plurality of flow equalizing holes 70 are provided between the fuel upper chamber 421 and the fuel lower chamber 422, and the plurality of flow equalizing holes 70 are circumferentially and uniformly distributed relative to the axis L1 of the oxidant flow channel, so as to ensure that the fuel sprayed from the injector outlet is circumferentially and uniformly distributed relative to the axis L1 of the oxidant flow channel.
In the present embodiment, as shown in fig. 1 and 3, the injector further includes a flow equalizing hole 70, and the upper fuel chamber 421 and the lower fuel chamber 422 are communicated with each other through the flow equalizing hole 70; the number of the flow equalizing holes 70 is multiple, and the flow equalizing holes 70 are circumferentially and uniformly distributed relative to the axis L1 of the oxidant flow passage; through setting up flow hole 70 is uniformized the side direction comes to flow and converts into the in-process that the axial came makes propellant in the fuel epicoele 421 passes through flow hole 70 evenly shunts and lets in the fuel cavity 422, improved the homogeneity of the structure of insufflator has guaranteed the high-efficient stable burning of propellant.
Specifically, the fuel injection hole 60 is provided at an outer ring layer of the oxidant injection hole 50.
Optionally, the oxidant injection hole 50 is correspondingly communicated with the second oxidant flow section 32, the fuel injection hole 60 is correspondingly communicated with the fuel lower cavity 422, and the fuel injection hole 60 is disposed in an outer ring layer of the oxidant injection hole 50.
Referring to fig. 1 and 2, in the present embodiment, the fuel flow channel is disposed around the oxidant flow channel outer peripheral wall, and the fuel flow channel and the oxidant flow channel are separated by an integrally formed wall surface; the oxidant injection hole 50 is communicated with the oxidant runner; the fuel injection holes 60 are communicated with the fuel flow passage; by disposing the fuel injection hole 60 to the outer ring layer of the oxidizer injection hole 50; the inner ring is provided with the oxidant injection hole 50, and the outer ring is provided with the injection structure of the fuel injection hole 60, so that an internal oxygen external combustion environment is formed in the combustion process, a certain film cooling effect can be achieved in rich combustion, and thermal protection of the wall surface of the combustion chamber is facilitated.
Specifically, the extension direction of the axis of the oxidant injection hole 50 and the extension direction of the axis of the fuel injection hole 60 intersect at the lower end of the injector and form a predetermined angle.
It should be noted that the number and distribution of the oxidant injection holes 50 and the fuel injection holes 60 may be adjusted according to actual use conditions, and are not limited to the conditions shown in the figures; the distribution and the number of the flow equalizing holes 70 can be adjusted according to actual use conditions, and are not limited to the conditions shown in the drawing; the preset angle formed by the extension direction of the axis of the oxidant injection hole 50 and the extension direction of the axis of the fuel injection hole 60 can be adjusted according to actual use conditions, and is not limited to the condition shown in the figure.
Optionally, the extending direction of the axis of the oxidant injection hole 50 and the extending direction of the axis of the fuel injection hole 60 intersect near the injection port of the injector and form a preset angle, and the preset angle is in the range of 30 ° to 90 °.
Referring to fig. 1 and 2, in this embodiment, the oxidant injection holes 50 and the fuel injection holes 60 are arranged in a one-to-one correspondence manner, each oxidant injection hole 50 and the corresponding fuel injection hole 60 form a pair of impinging holes at an injection port of the injector, and the pairs of impinging holes are circumferentially and uniformly distributed on a lower end surface of the injector relative to an axis L1 of the oxidant flow passage; the extension direction of the axis of each oxidant injection hole 50 and the extension direction of the axis of the corresponding fuel injection hole 60 form the preset angle, so that the propellants can sufficiently collide, collide and mix near the injection port of the injector, the efficient and stable combustion of the propellants in the combustion chamber is realized, and the combustion efficiency of the injector is improved.
In particular, the injector is integrally formed or 3D printed.
Optionally, the injector is integrally formed or 3D printed, the fuel flow channel is circumferentially arranged relative to the oxidant flow channel, and the fuel flow channel and the oxidant flow channel are separated by an integrally formed wall surface, so that interfaces and/or welding seams are effectively reduced, and the problem of propellant serial cavities is avoided; the injector integrates the structures of the oxidant path and the fuel path internal flow channel of the propellant component into a whole through 3D printing and forming, so that the integral structure of the injector is greatly simplified, the production cost is reduced, the part deformation caused by heat input in the welding process is effectively avoided, and the influence on assembly and key size is reduced.
The operating principle of the injector is as follows:
during the operation of the injector, the first propellant in the oxidant inlet 10 is introduced into the second oxidant flow section 32 through the first oxidant flow section 31, and then introduced into the combustion chamber through the oxidant injection holes 50 which are uniformly distributed;
the second propellant in the fuel inlet 20 passes through the first fuel flow section 41 and then into the fuel upper chamber 421, and then passes through the evenly distributed flow-equalizing holes 70 and then evenly passes through the fuel lower chamber 422, so that the lateral incoming flow in the first fuel flow section 41 is evenly converted into an axial incoming flow parallel to the direction of the axis L1, and then passes through the evenly distributed fuel injection holes 60 and finally enters into the combustion chamber;
because the oxidant injection holes 50 and the fuel injection holes 60 are arranged in a one-to-one correspondence manner, and each oxidant injection hole 50 and the corresponding fuel injection hole 60 form a preset angle at the injection port of the injector and form a pair of mutual impact holes, the first oxidant and the second propellant can collide with each other along the preset angle and are fully mixed, thereby realizing efficient and stable combustion in the combustion chamber.
The utility model also provides an engine, in particular a liquid rocket engine, comprising: the injector comprises an engine body and the injector.
The utility model also provides an aircraft, in particular a rocket aircraft, which comprises an aircraft body and the engine.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the utility model.
Claims (10)
1. An injector, comprising:
one end of the oxidant channel is communicated with the oxidant inlet (10), and the other end of the oxidant channel is communicated with the oxidant injection hole (50);
one end of the fuel flow passage is communicated with the fuel inlet (20), and the other end of the fuel flow passage is communicated with the fuel injection hole (60);
the fuel flow channel is circumferentially arranged relative to the oxidant flow channel;
the oxidant injection holes (50) and the fuel injection holes (60) are arranged in a one-to-one correspondence.
2. The injector of claim 1, wherein said fuel flow passage comprises a first fuel flow segment (41) and a second fuel flow segment (42); the second fuel flow section (42) is coincident with the axis of the oxidant flow channel, the first fuel flow section (41) and the second fuel flow section (42) forming a predetermined angle; said first fuel flow section (41) being adapted to communicate with said fuel inlet (20); the second fuel flow section (42) is adapted to communicate with the fuel injection orifice (60).
3. The injector of claim 2, wherein said second fuel flow segment (42) comprises an upper fuel chamber (421) and a lower fuel chamber (422), said upper fuel chamber (421) and said lower fuel chamber (422) being in communication therebetween; the upper fuel cavity (421) is adapted to communicate with the first fuel flow section (41) and the lower fuel cavity (422) is adapted to communicate with the fuel injection holes (60).
4. Injector according to claim 3, characterized in that the oxidant flow channel and the fuel flow channel are internally provided with rounded corners and/or dome structures.
5. The injector of claim 4, further comprising a flow equalizing port (70), wherein the upper fuel chamber (421) and the lower fuel chamber (422) are in communication with each other through the flow equalizing port (70).
6. Injector according to claim 5, characterized in that said fuel injection holes (60) are provided in the outer ring layer of said oxidant injection holes (50).
7. Injector according to claim 6, characterized in that the extension of the axis of said oxidant injection hole (50) and the extension of the axis of said fuel injection hole (60) intersect at the lower end of said injector and form a predetermined angle.
8. Injector according to any of claims 1 to 7, characterized in that it is integrally formed or 3D printed.
9. An engine, comprising: an engine block and an injector according to any of claims 1 to 8.
10. An aircraft, characterized in that it comprises: an aircraft body, and an engine as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202220442130.0U CN216714560U (en) | 2022-03-02 | 2022-03-02 | Injector, engine and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220442130.0U CN216714560U (en) | 2022-03-02 | 2022-03-02 | Injector, engine and aircraft |
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| CN216714560U true CN216714560U (en) | 2022-06-10 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114382614A (en) * | 2022-03-02 | 2022-04-22 | 北京星际荣耀科技有限责任公司 | Injector, engine and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114382614A (en) * | 2022-03-02 | 2022-04-22 | 北京星际荣耀科技有限责任公司 | Injector, engine and aircraft |
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