CN115142988A - Long-time low-thrust spray pipe diffusion section - Google Patents
Long-time low-thrust spray pipe diffusion section Download PDFInfo
- Publication number
- CN115142988A CN115142988A CN202210793662.3A CN202210793662A CN115142988A CN 115142988 A CN115142988 A CN 115142988A CN 202210793662 A CN202210793662 A CN 202210793662A CN 115142988 A CN115142988 A CN 115142988A
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- Prior art keywords
- heat sink
- ring
- sink ring
- spray pipe
- back wall
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to the technical field of solid rocket engine spray pipes, in particular to a long-time low-thrust spray pipe diffusion section. The method comprises the following steps: the heat-insulating back wall jet pipe comprises a jet pipe shell, a back wall heat-insulating layer, a front heat sink ring, a middle heat sink ring, a rear heat sink ring, a baffle ring, a rear heat-insulating layer, a diffusion section and a throat liner, wherein the back wall heat-insulating layer is positioned on the inner side of the jet pipe shell; the front heat sink ring, the middle heat sink ring and the rear heat insulation layer are arranged adjacent to the back wall heat insulation layer; the throat insert is positioned on the inner sides of the front heat sink ring and the middle heat sink ring; the diffusion section is respectively adjacent to the middle heat sink ring, the rear heat sink ring and the throat liner along the flowing direction of fuel gas; the rear heat sink ring is respectively arranged adjacent to the rear heat insulation layer and the diffusion section; the baffle ring is positioned at the tail end of the spray pipe. The invention is suitable for the solid rocket engine with the working time of more than one hundred seconds, and improves the specific impulse of the propellant of the solid rocket engine; the ablation condition at the diffusion section is improved, and the overall reliability of the solid rocket engine is improved.
Description
Technical Field
The invention relates to the technical field of solid rocket engine spray pipes, in particular to a long-time low-thrust spray pipe diffusion section.
Background
The diffuser of the solid rocket engine nozzle is an important component of the nozzle, the ablation resistance stability of the heat insulating layer of the diffuser depends on the quality of an ablation layer, and the failure of the engine operation and the missile flight can be caused by the poor stability of the ablation layer. Typical diffuser segment materials include carbon cloth/phenolic wound products, carbon fiber/phenolic molded products, carbon/carbon composites, and the like.
The diffusion section adopting the material is mainly used for the solid rocket engine with working time of several seconds to dozens of seconds, and when the working time is more than hundred seconds, the ablation at the diffusion section is serious, and the specific impulse of the propellant is reduced.
The existing solid rocket engine nozzle diffusion section has serious ablation and reduced propellant specific impulse when working for more than one hundred seconds for a long time.
Disclosure of Invention
Technical problem to be solved by the invention
The invention provides a long-time low-thrust nozzle diffusion section, which aims to solve the problems that the conventional solid rocket engine working for a long time has serious ablation on the diffusion section, obvious reduction of specific impulse of a propellant and the like.
Technical scheme adopted by the invention for solving technical problem
A long term low thrust nozzle diffuser, comprising: the heat-insulating back wall heat-insulating jet pipe comprises a jet pipe shell 4, a back wall heat-insulating layer 1, a front heat sink ring 2, a middle heat sink ring 3, a rear heat sink ring 5, a baffle ring 6, a rear heat-insulating layer 7, a diffusion section 8 and a throat liner 9, wherein the back wall heat-insulating layer 1 is positioned on the inner side of the jet pipe shell 4; the front heat sink ring 2, the middle heat sink ring 3 and the rear heat insulation layer 7 are arranged adjacent to the back wall heat insulation layer 1 along the flowing direction of fuel gas; the throat liner 9 is positioned on the inner side of the back wall heat insulation layer 1, the inner sides of the front heat sink ring 2 and the middle heat sink ring 3 are positioned on the inner sides of the back wall heat insulation layer 1 and the throat liner 9, and the inner profile from the back wall heat insulation layer 1 to the throat liner 9 is a convergent profile; the diffusion section 8 is positioned on the inner side of the spray pipe shell 4 and is respectively adjacent to the middle heat sink ring 3, the rear heat sink ring 5 and the throat liner 9 along the flowing direction of fuel gas, and the inner profile from the throat liner 9 to the diffusion section 8 is a diffusion profile; the rear heat sink ring 5 is positioned on the inner side of the spray pipe shell 4 and is respectively adjacent to the rear heat insulation layer 7 and the diffusion section 8 along the flowing direction of fuel gas; the baffle ring 6 is positioned at the tail end of the spray pipe, and the baffle ring 6 is used for axially supporting the spray pipe.
Furthermore, the matching surfaces of the back wall heat insulation layer 1, the front heat sink ring 2, the middle heat sink ring 3, the spray pipe shell 4, the rear heat sink ring 5, the baffle ring 6, the rear heat insulation layer 7, the diffusion section 8 and the throat liner 9 are bonded by adhesive.
Further, the nozzle housing 4 is connected with the baffle ring 6 through threads.
Furthermore, step surfaces are arranged between the adjacent front heat sink ring 2, the middle heat sink ring 3 and the rear heat insulation layer 7.
Further, the front heat sink ring 2, the middle heat sink ring 3 and the heat sink ring 5 are made of carbon/carbon composite materials.
Furthermore, the material of the nozzle shell 4 and the baffle ring 6 is structural steel.
Further, the diffusion section 8 and the throat insert 9 are made of tungsten-infiltrated copper.
Advantageous effects obtained by the present invention
The invention provides a long-time low-thrust nozzle diffusion section, which is simple in structure, mature in material and suitable for a solid rocket engine with the working time of more than one hundred seconds, can improve the specific impulse of a propellant of the solid rocket engine, can improve the ablation condition of the diffusion section and can improve the overall reliability of the solid rocket engine.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1: a schematic diagram of a long-time low-thrust nozzle diffuser mechanism;
wherein: 1-back wall heat insulation layer, 2-front heat sink ring, 3-middle heat sink ring, 4-spray pipe shell, 5-rear heat sink ring, 6-baffle ring, 7-rear heat insulation layer, 8-diffusion section and 9-throat liner.
Detailed Description
A long term low thrust nozzle diffuser, comprising: the heat-insulating back wall heat-insulating jet pipe comprises a jet pipe shell 4, a back wall heat-insulating layer 1, a front heat sink ring 2, a middle heat sink ring 3, a rear heat sink ring 5, a baffle ring 6, a rear heat-insulating layer 7, a diffusion section 8 and a throat liner 9, wherein the back wall heat-insulating layer 1 is positioned on the inner side of the jet pipe shell 4; the front heat sink ring 2, the middle heat sink ring 3 and the rear heat insulating layer 7 are arranged adjacent to the back wall heat insulating layer 1 along the flowing direction of fuel gas; the throat insert 9 is positioned on the inner side of the back wall heat insulation layer 1, the inner sides of the front heat sink ring 2 and the middle heat sink ring 3 are positioned on the inner sides of the back wall heat insulation layer 1 and the throat insert 9, and the inner profile from the back wall heat insulation layer 1 to the throat insert 9 is a convergent profile; the diffusion section 8 is positioned on the inner side of the spray pipe shell 4 and is respectively adjacent to the middle heat sink ring 3, the rear heat sink ring 5 and the throat insert 9 along the flowing direction of fuel gas, and the inner profile from the throat insert 9 to the diffusion section 8 is a diffusion profile; the rear heat sink ring 5 is positioned on the inner side of the spray pipe shell 4 and is respectively arranged adjacent to the rear heat insulation layer 7 and the diffusion section 8 along the gas flowing direction; the baffle ring 6 is positioned at the tail end of the spray pipe, and the baffle ring 6 is used for axially supporting the spray pipe.
Furthermore, the matching surfaces of the back wall heat insulation layer 1, the front heat sink ring 2, the middle heat sink ring 3, the spray pipe shell 4, the rear heat sink ring 5, the baffle ring 6, the rear heat insulation layer 7, the diffusion section 8 and the throat liner 9 are bonded by adhesive. The spray pipe shell 4 is connected with the baffle ring 6 through threads. The adjacent front heat sink ring 2, the middle heat sink ring 3 and the rear heat insulation layer 7 are arranged in a step surface manner. The front heat sink ring 2, the middle heat sink ring 3 and the heat sink ring 5 are made of carbon/carbon composite materials. The material of the spray pipe shell 4 and the baffle ring 6 is structural steel. The diffusion section 8 and the throat insert 9 are made of tungsten copper.
In order to make the objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It is obvious that the described embodiments are only some, not all embodiments of the proposed solution. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
As shown in figure 1, when in operation, combustion gas is discharged from the front heat sink ring 2, the throat insert 9 and the diffuser section 8 at high speed, so that axial thrust is generated.
As shown in fig. 1, the front heat sink ring 2, the middle heat sink ring 3, and the heat sink ring 5 function as heat sinks to conduct heat away from the throat insert 9 and the diffuser section 8, thereby improving the working environment at the throat insert 9 and the diffuser section 8.
As shown in fig. 1, the back wall insulation layer 1 and the rear insulation layer 7 play a role of insulation, and reduce the working temperature at the spray pipe shell 4 and the baffle ring 6.
As shown in fig. 1, the nozzle casing 4 is used to withstand the pressure of the combustion gases in the nozzle.
As shown in fig. 1, the baffle ring 6 is used for axial support of the nozzle.
In specific implementation, the matching surfaces of the back wall heat insulation layer 1, the front heat sink ring 2, the middle heat sink ring 3, the spray pipe shell 4, the rear heat sink ring 5, the baffle ring 6, the rear heat insulation layer 7, the diffusion section 8 and the throat liner 9 are bonded by adhesive, and the spray pipe shell 4 is connected with the baffle ring 6 through threads. The back wall heat insulating layer 1 and the back heat insulating layer 7 are made of high silica fiber/phenolic resin molded products. The front heat sink ring 2, the middle heat sink ring 3 and the heat sink ring 5 are made of carbon/carbon composite materials. The material of the spray pipe shell 4 and the baffle ring 6 is structural steel. The diffusion section 8 and the throat liner 9 are made of tungsten copper infiltrated material which is not ablated in the working process.
The working time of a certain type of solid rocket engine is not less than 150s, the average thrust is 1000N-1200N, and the nozzle diffusion section adopts the form, so that the environment test, the high, low and normal temperature ground test run test and the flight test check are completed, and the operation is normal.
Claims (7)
1. A long duration low thrust nozzle diffuser, comprising: the heat-insulating back wall spray pipe comprises a spray pipe shell (4), a back wall heat-insulating layer (1), a front heat sink ring (2), a middle heat sink ring (3), a rear heat sink ring (5), a baffle ring (6), a rear heat-insulating layer (7), a diffusion section (8) and a throat liner (9), wherein the back wall heat-insulating layer (1) is positioned on the inner side of the spray pipe shell (4); the front heat sink ring (2), the middle heat sink ring (3) and the rear heat insulation layer (7) are arranged adjacent to the back wall heat insulation layer (1) along the flowing direction of fuel gas; the throat insert (9) is positioned on the inner side of the back wall heat insulation layer (1), the inner sides of the front heat sink ring (2) and the middle heat sink ring (3) are positioned on the inner sides of the back wall heat insulation layer (1) and the throat insert (9), and the inner molded surface from the back wall heat insulation layer (1) to the throat insert (9) is a convergent molded surface; the diffusion section (8) is positioned on the inner side of the spray pipe shell (4) and is respectively adjacent to the middle heat sink ring (3), the rear heat sink ring (5) and the throat insert (9) along the flowing direction of fuel gas, and the inner profile from the throat insert (9) to the diffusion section (8) is a diffusion profile; the rear heat sink ring (5) is positioned on the inner side of the spray pipe shell (4) and is respectively adjacent to the rear heat insulation layer (7) and the diffusion section (8) along the flowing direction of fuel gas; the baffle ring (6) is positioned at the tail end of the spray pipe, and the baffle ring (6) is used for axially supporting the spray pipe.
2. The long term low thrust nozzle diffuser according to claim 1, wherein: the back wall heat insulation layer (1), the front heat sink ring (2), the middle heat sink ring (3), the spray pipe shell (4), the rear heat sink ring (5), the baffle ring (6), the rear heat insulation layer (7), the diffusion section (8) and the throat liner (9) are bonded by adhesive among matching surfaces.
3. The long duration low thrust nozzle diffuser of claim 1, wherein: the spray pipe shell (4) is in threaded connection with the baffle ring (6).
4. The long duration low thrust nozzle diffuser of claim 1, wherein: the adjacent front heat sink ring (2), the middle heat sink ring (3) and the rear heat insulation layer (7) are arranged in a step surface way.
5. The long duration low thrust nozzle diffuser of claim 1, wherein: the front heat sink ring (2), the middle heat sink ring (3) and the heat sink ring (5) are made of carbon/carbon composite materials.
6. The long term low thrust nozzle diffuser according to claim 1, wherein: the spray pipe shell (4) and the baffle ring (6) are made of structural steel.
7. The long term low thrust nozzle diffuser according to claim 1, wherein: the diffusion section (8) and the throat insert (9) are made of tungsten copper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210793662.3A CN115142988A (en) | 2022-07-05 | 2022-07-05 | Long-time low-thrust spray pipe diffusion section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210793662.3A CN115142988A (en) | 2022-07-05 | 2022-07-05 | Long-time low-thrust spray pipe diffusion section |
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| Publication Number | Publication Date |
|---|---|
| CN115142988A true CN115142988A (en) | 2022-10-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210793662.3A Pending CN115142988A (en) | 2022-07-05 | 2022-07-05 | Long-time low-thrust spray pipe diffusion section |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115573829A (en) * | 2022-10-28 | 2023-01-06 | 西安长峰机电研究所 | Ablation-resistant structure of expansion section outlet |
-
2022
- 2022-07-05 CN CN202210793662.3A patent/CN115142988A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115573829A (en) * | 2022-10-28 | 2023-01-06 | 西安长峰机电研究所 | Ablation-resistant structure of expansion section outlet |
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