CN117703628A - Liquid rocket engine injector flange heat insulation structure and liquid rocket engine - Google Patents
Liquid rocket engine injector flange heat insulation structure and liquid rocket engine Download PDFInfo
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- CN117703628A CN117703628A CN202311787791.2A CN202311787791A CN117703628A CN 117703628 A CN117703628 A CN 117703628A CN 202311787791 A CN202311787791 A CN 202311787791A CN 117703628 A CN117703628 A CN 117703628A
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- heat insulation
- injector
- liquid rocket
- rocket engine
- flange
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- 238000009413 insulation Methods 0.000 title claims abstract description 48
- 239000007788 liquid Substances 0.000 title claims abstract description 37
- 238000002485 combustion reaction Methods 0.000 claims abstract description 13
- 239000003380 propellant Substances 0.000 claims description 10
- 238000003466 welding Methods 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000011144 upstream manufacturing Methods 0.000 abstract description 3
- 238000003754 machining Methods 0.000 abstract description 2
- 239000002737 fuel gas Substances 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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Abstract
The invention provides a liquid rocket engine injector flange heat insulation structure and a liquid rocket engine, which relate to the field of liquid rocket engines, and comprise cross ribs, heat insulation holes and injector frames, wherein the heat insulation holes are positioned on the cross ribs, and the cross ribs are connected to heat insulation blocks at the bottom ends of the injector frames; the root of the cross rib is provided with a semicircle, and the injector frame increases thermal resistance through the cooperation of the semicircle and the heat insulation hole to realize heat insulation. The flange heat insulation structure of the injector of the liquid rocket engine is reasonable and simple in structure, can increase heat resistance and reduce heat conduction of the high-temperature combustion chamber to the upstream; the design of the cross rib root semicircle and the design of the heat insulation hole reduce local stress concentration, are beneficial to the direct forming of drill bit machining in small-size space, can ensure the structural strength resisting mechanical test examination, and are particularly suitable for small-size space attitude control liquid rocket engines.
Description
Technical Field
The invention relates to the field of liquid rocket engines, in particular to a flange heat insulation structure of a liquid rocket engine injector and a liquid rocket engine.
Background
The space attitude control liquid rocket engine provides attitude adjustment power for spacecrafts such as satellites, spaceship, deep space probes and the like, the propellant is mixed and combusted in a combustion chamber after passing through a control valve to generate high-temperature and high-pressure fuel gas, the fuel gas expands to generate thrust after being sprayed out, the temperature of the fuel gas in the combustion chamber is up to about 2700 ℃, and the temperature of the outer wall is about 1200-1500 ℃. As an important component for realizing the propulsion function of the spacecraft, the engine is required to have light weight and compact space, so that the temperature gradient between the electromagnetic valve and the combustion chamber is large, the heat dissipation space is limited, and the upper surface of the injector flange is usually stuck with a thermal control adhesive to fix the thermistor for monitoring the on-orbit working state of the engine. When the engine is continuously ignited to work or after the engine is shut down, the high-temperature combustion chamber can conduct heat upstream, so that the temperature of the injector flange and the electromagnetic valve is higher, and the service life and reliability of nonmetallic parts such as the thermal control adhesive on the injector flange, a sealing part between the electromagnetic valve and the injector flange, an electromagnetic valve core action part and the like are seriously influenced.
The effect of reducing the temperature of the flange and the electromagnetic valve can be achieved by improving the design of the injection parameters in the engine at the present stage, but the iteration period is long, and the test cost is high. In order to resist the vibration and impact mechanics environment test and examination in the rocket flight and in-orbit maneuvering process, an entity welding structure is adopted between the injector flange and the high-temperature combustion chamber, so that sufficient structural strength is ensured, and the thermal resistance is smaller.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a flange heat insulation structure of a liquid rocket engine injector and a liquid rocket engine.
The invention provides a flange heat insulation structure of a liquid rocket engine injector, which comprises cross ribs, heat insulation holes and an injector frame, wherein the heat insulation holes are formed in the cross ribs, and the cross ribs are connected to heat insulation blocks at the bottom end of the injector frame;
the root of the cross rib is provided with a semicircle, and the injector frame increases thermal resistance through the cooperation of the semicircle and the heat insulation hole to realize heat insulation.
Preferably, the injector frame is provided with a central hollow structure and a valve support hollow structure, and the plurality of central hollow structures are distributed in a triangular mode.
Preferably, the height of the cross rib is equal to the diameter of the semicircle.
Preferably, the aperture of the heat-insulating hole is half the height of the cross rib.
Preferably, the height of the cross rib is 4-8mm, the diameter of the semicircle is 4-8mm, and the aperture of the heat insulation hole is 2-4mm.
Preferably, the cross rib, the insulating aperture, and the injector frame material are 7715D or TC4 titanium alloy.
The invention also provides a liquid rocket engine, which adopts the flange heat insulation structure of the injector of the liquid rocket engine.
Preferably, the bottom end of the injector frame is connected with the high-temperature combustion chamber by high-energy beam welding.
Preferably, propellant control valves are symmetrically arranged on two sides of the top of the injector frame respectively, and are in one-to-one correspondence connection with valve supports on the injector frame.
Preferably, the propellant control valve is 40 ° from horizontal.
Compared with the prior art, the invention has the following beneficial effects:
(1) The flange heat insulation structure of the injector of the liquid rocket engine is reasonable and simple in structure, can increase heat resistance and reduce heat conduction of the high-temperature combustion chamber to the upstream;
(2) The invention reduces local stress concentration through the semicircular design of the root of the cross rib and the design of the heat insulation hole, is beneficial to the direct forming of the drill bit machining in small-size space, can ensure the structural strength resisting the check of mechanical tests, and is particularly suitable for small-size space attitude control liquid rocket engines.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a flange heat insulation structure of an injector of a liquid rocket engine according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of section X-X of FIG. 1;
FIG. 3 is a schematic view of the structure of the Y-view in FIG. 1;
FIG. 4 is a schematic representation of an embodiment of a liquid rocket engine employing the present invention.
In the figure: the device comprises a cross rib 1, a semicircular root 11, a heat insulation hole 2, a 3-injector frame, a 31-center hollow structure, a 32-valve support hollow structure, a 4-high temperature combustion chamber and a 5-propellant control valve.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
The invention provides a flange heat insulation structure of a liquid rocket engine injector, which is shown in fig. 1-3, and comprises a cross rib 1, heat insulation holes 2 and an injector frame 3, wherein the heat insulation holes 2 are through holes and are positioned on the cross rib 1, the cross rib 1 is positioned on a heat insulation block at the bottom end of the injector frame 3, the injector frame 3 is provided with a plurality of hollow structures, the hollow structures comprise a center hollow structure 31 and a valve support hollow structure 32, and the center hollow structures 31 are distributed in a triangular mode. The root of the cross rib 1 is a semicircle 11, and the height of the cross rib 1 is equal to the diameter of the semicircle 11; the height of the cross rib 1 is 5mm, and the diameter of the semicircle 11 is 5mm. The aperture of the heat insulation hole 2 is half of the height of the cross rib 1, and the aperture of the heat insulation hole 2 is 2.5mm. The cross rib, the heat insulation hole and the injector frame material are 7715D titanium alloy.
Example 2
The invention provides a liquid rocket engine, as shown in fig. 4, comprising a flange heat insulation structure of a liquid rocket engine injector in embodiment 1.
The heat insulation blocks at the bottom end of the injector frame 3 are connected with the high-temperature combustion chamber 4 by adopting high-energy beam welding, the propellant control valves 5 are obliquely and symmetrically arranged at two sides of the top of the injector frame 3 at an angle of 40 degrees, and the propellant control valves 5 are correspondingly connected with valve supports at the top of the injector frame 3 one by one.
More specifically, the liquid rocket engine provided by the invention is subjected to identification-stage vibration, impact mechanical environment test examination and thermal test ignition verification, the highest temperature of the outer wall of the high-temperature combustion chamber 4 is 1320 ℃ during ignition, and the temperature of the upper surface of the injector flange is reduced from 300 ℃ to 150 ℃ before improvement. After the engine is shut down, the temperature of the shell transferred to the propellant control valve 5 by the high-temperature combustion chamber 4 is reduced from 85 ℃ to 60 ℃ before improvement, and the shell is effectively controlled within the allowable temperature range of the nonmetallic valve core component.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. The flange heat insulation structure of the injector of the liquid rocket engine is characterized by comprising a cross rib (1), heat insulation holes (2) and an injector frame (3), wherein the heat insulation holes (2) are positioned on the cross rib (1), and the cross rib (1) is connected to a heat insulation block at the bottom end of the injector frame (3);
the root of the cross rib (1) is provided with a semicircle (11), and the injector frame (3) realizes heat insulation by increasing thermal resistance through the cooperation of the semicircle (11) and the heat insulation hole (2).
2. The flange heat insulation structure of the liquid rocket engine injector according to claim 1, wherein a central hollow structure (31) and valve support hollow structures (32) are arranged on the injector frame (3), and a plurality of the central hollow structures (31) are distributed in a triangular shape.
3. A liquid rocket engine injector flange insulation structure according to claim 1, characterized in that the height of the cross rib (1) is equal to the diameter of the semicircle (11).
4. A liquid rocket engine injector flange insulation structure according to claim 3, characterized in that the aperture of the insulation hole (2) is half the height of the cross rib (1).
5. A liquid rocket engine injector flange insulation structure according to claim 4, wherein the height of the cross rib (1) is 4-8mm, the diameter of the semicircle (11) is 4-8mm, and the aperture of the insulation hole (2) is 2-4mm.
6. A liquid rocket engine injector flange insulation structure according to claim 1, wherein the cross rib (1), the insulation aperture (2) and the injector frame (3) material is 7715D or TC4 titanium alloy.
7. A liquid rocket engine, characterized in that the flange heat insulation structure of the liquid rocket engine injector is adopted in any one of claims 1-6.
8. A liquid rocket engine according to claim 7, wherein the bottom end of the injector frame (3) is connected with the high-temperature combustion chamber (4) by high-energy beam welding.
9. A liquid rocket engine according to claim 7, wherein propellant control valves (5) are symmetrically arranged on two sides of the top of the injector frame (3), and the propellant control valves (5) are connected with valve supports on the injector frame (3) in a one-to-one correspondence.
10. A liquid rocket engine according to claim 9, wherein the propellant control valve (5) is 40 ° from horizontal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311787791.2A CN117703628A (en) | 2023-12-22 | 2023-12-22 | Liquid rocket engine injector flange heat insulation structure and liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311787791.2A CN117703628A (en) | 2023-12-22 | 2023-12-22 | Liquid rocket engine injector flange heat insulation structure and liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117703628A true CN117703628A (en) | 2024-03-15 |
Family
ID=90158723
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311787791.2A Pending CN117703628A (en) | 2023-12-22 | 2023-12-22 | Liquid rocket engine injector flange heat insulation structure and liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117703628A (en) |
-
2023
- 2023-12-22 CN CN202311787791.2A patent/CN117703628A/en active Pending
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