CN110608109B - Spray pipe structure - Google Patents
Spray pipe structure Download PDFInfo
- Publication number
- CN110608109B CN110608109B CN201910955426.5A CN201910955426A CN110608109B CN 110608109 B CN110608109 B CN 110608109B CN 201910955426 A CN201910955426 A CN 201910955426A CN 110608109 B CN110608109 B CN 110608109B
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- Prior art keywords
- spray pipe
- back lining
- insulation layer
- throat insert
- heat insulation
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Classifications
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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
-
- 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)
- Coating By Spraying Or Casting (AREA)
Abstract
A nozzle structure belongs to the technical field of solid rocket engines and comprises a throat liner 1, a back lining 2, a heat insulation layer 3, a nozzle shell 4 and a diffusion section 5. Throat insert 1 and 2 hole cooperations in back lining, be used for high temperature high pressure gas direct flushing, back lining 2 and 3 hole cooperations in the heat insulation layer, be used for high temperature thermal ablation resistance and the erosion of 1 straightway low reaches high temperature air current of throat insert, heat insulation layer 3 and the cooperation of spray tube hole, be used for resisting the heat-conduction of high temperature gas to spray tube housing 4, spray tube housing 4 is used for providing the structural strength of spray tube, 4 expansion section surfaces of spray tube housing have the protruding structure of macroscopic array, be used for connecting spray tube diffuser 5, spray tube diffuser 5 passes through the frock and moulds shaping on spray tube housing 4, be used for making high temperature high pressure gas further inflation acting, provide solid rocket engine thrust. The invention simplifies the structure of the spray pipe, reduces the weight of the spray pipe, and improves the reliability of the spray pipe due to the absence of structures such as pin holes and the like.
Description
Technical Field
The invention relates to a spray pipe structure, in particular to a spray pipe structure with a diffusion section in puncture connection based on an array protrusion on the inner surface of a shell, and belongs to the technical field of solid rocket engines.
Background
The jet pipe is one of important parts of a solid rocket engine, and is used for expanding, accelerating and discharging high-temperature and high-pressure fuel gas generated in a combustion chamber of the engine to do work and provide required thrust for the rocket.
The spray pipe operating mode is abominable, need bear the direct erosion of high temperature high pressure gas, and the heat-conduction of high temperature gas to the spray pipe inside, the spray pipe diffuser adopts high temperature resistant glue to bond to the spray pipe casing usually, for preventing that the spray pipe diffuser from taking place the bonding condition that became invalid and fly out under the high-speed gas stream effect, often through pin intensive connection between spray pipe diffuser and the spray pipe casing, but the pin joint part has weakened the local thermal protection performance of diffuser to a certain extent, and in practice take place the pinhole easily when processing the cotter hole and break through the problem. Due to the limitation of factors such as the overall size envelope and the weight of the engine, the non-metal wall thickness of the spray pipe shell and the spray pipe diffusion section is always thin, and particularly when the size of the spray pipe is small, the spray pipe shell and the spray pipe diffusion section are difficult to be connected in a strengthening mode through pins. In actual engineering, the connection between the expansion section of the spray pipe and the nonmetal diffusion section is increased through sand blasting or laser texturing on the inner surface of the expansion section of the spray pipe, but the connection is enhanced only by increasing the bonding area to a certain extent, and the strength of the spray pipe cannot meet the actual use requirement.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the shortcomings of the prior art are overcome, and a nozzle structure, in particular a nozzle structure with a diffusion section based on a shell inner surface array protrusion puncture connection is provided, wherein the nozzle structure comprises: a throat insert, a backing, an insulation layer, a nozzle casing, and a diffuser. The throat liner is matched with an inner hole of the back liner and used for resisting direct scouring of high-temperature and high-pressure gas, the back liner is matched with an inner hole of the heat insulation layer and used for resisting high-temperature thermal ablation and high-temperature air flow erosion on the downstream of a straight section of the throat liner, the heat insulation layer is matched with an inner hole of the spray pipe and used for resisting heat conduction of high-temperature gas to the spray pipe shell, the spray pipe shell is used for providing structural strength of the spray pipe, a macro array protruding structure is arranged on the surface of an expansion section of the spray pipe shell and used for being connected with a diffusion section of the spray pipe, and the diffusion section of the spray pipe is formed on the spray pipe shell through die pressing by tool equipment and used for further expanding the high-temperature and high-pressure gas to do work and providing thrust of the solid rocket engine.
The purpose of the invention is realized by the following technical scheme:
a nozzle structure is characterized by comprising a throat insert, a back lining, a heat insulating layer, a nozzle shell and a diffusion section;
the throat insert is positioned in the back lining and is used for resisting direct scouring of the fuel gas flow; the throat insert and the backing are both located within the insulating layer, the backing being for resisting erosion by the gas stream downstream of the throat insert; the jet pipe shell is sleeved on the heat insulation layer, and the heat insulation layer is used for isolating the heat conduction of the throat insert and the back lining to the jet pipe shell; the local part of the diffusion section is sleeved in the spray pipe shell, the surface of the spray pipe shell sleeved with the diffusion section is provided with a convex structure, and the diffusion section is directly molded on the spray pipe shell;
the lance housing is adapted to support the entire lance structure.
Preferably, a first inner hole is formed in the throat insert; the first inner hole is divided into two sections, wherein one section close to the incoming gas flow is a convergent profile, and the other section far away from the incoming gas flow is a straight profile.
Preferably, the throat insert is fixedly connected with the backing by bonding.
Preferably, a second inner hole is formed in the backing, the throat insert is located in the second inner hole, and the backing is made of carbon fiber phenolic materials.
Preferably, the end of the backing close to the incoming flow of the gas flow is larger than the end far away from the incoming flow of the gas flow, the throat insert and the backing are both located in the heat insulation layer, and the end of the backing close to the incoming flow of the gas flow limits the backing in the heat insulation layer.
Preferably, a fourth inner hole and an expansion hole are formed in the spray pipe shell; the fourth inner hole is a stepped hole and used for limiting the heat insulating layer.
Preferably, part of the diffuser section is sleeved in an expansion hole of the nozzle shell, a staggered convex structure is arranged on the surface of the expansion hole, and the convex structure is processed by adopting but not limited to a micro electric spark or an electrochemical method.
Preferably, the convex structure is conical, cylindrical, cuboid or prismoid.
Preferably, the protruding structure is divided into 4-10 layers, the distance between every two layers is 3-8 mm, the number of every layer is 16-40, and the staggered angle between every two adjacent layers is 6-9 degrees.
Preferably, the heat insulating layer is made of glass fiber reinforced plastic material.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the invention, the macroscopic array convex structures are designed on the inner surface of the expansion section of the spray pipe shell, the number of the convex structures is determined according to the load requirement borne by the spray pipe, and the method is more reliable than the conventional method for fixedly bonding the nonmetal diffusion sections by gluing;
(2) according to the invention, the connection between the nonmetal diffusion section and the spray pipe shell is strengthened through the macroscopic array convex structure, so that the problem that a processed pin hole is easy to punch through when the connection is strengthened by using a pin is avoided, and the structure of the spray pipe is optimized;
(3) according to the invention, the connection between the nonmetal diffusion section and the spray pipe shell is strengthened through the macroscopic array convex structure, a pin connection structure is not needed, and the reduction of the structural quality of the spray pipe is facilitated.
Drawings
FIG. 1 is a schematic view of a nozzle configuration;
FIG. 2 is a schematic cross-sectional view of the nozzle housing;
FIG. 3 is a schematic top view of the nozzle housing;
FIG. 4 is an enlarged partial cross-sectional view of the nozzle housing.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example 1:
a nozzle structure comprises a throat insert 1, a back lining 2, a heat insulating layer 3, a nozzle shell 4 and a diffusion section 5;
the throat insert 1 is positioned in the back lining 2 and is used for resisting direct scouring of the fuel gas flow; the throat insert 1 and the backing 2 are both positioned in the heat insulation layer 3, and the backing 2 is used for resisting erosion of gas flow at the downstream of the throat insert 1; the nozzle shell 4 is sleeved on the heat insulation layer 3, and the heat insulation layer 3 is used for isolating the heat conduction of the throat insert 1 and the back lining 2 to the nozzle shell 4; the local part of the diffusion section 5 is sleeved in the spray pipe shell 4, the surface of the spray pipe shell 4 sleeved with the diffusion section 5 is provided with a convex structure, and the diffusion section 5 is directly molded on the spray pipe shell 4;
the lance housing 4 serves to support the entire lance structure.
A first inner hole is formed in the throat insert 1; the first inner hole is divided into two sections, wherein one section close to the incoming gas flow is a convergent profile, and the other section far away from the incoming gas flow is a straight profile. A second inner hole is formed in the backing 2, the throat insert 1 is located in the second inner hole, and the backing 2 is made of carbon fiber phenolic materials. The end of the back lining 2 close to the incoming gas flow is larger than the end far away from the incoming gas flow, the throat insert 1 and the back lining 2 are both positioned in the heat insulation layer 3, and the end of the back lining 2 close to the incoming gas flow limits the back lining 2 in the heat insulation layer 3. A fourth inner hole and an expansion hole are formed in the spray pipe shell 4; the fourth hole is a stepped hole and is used for limiting the heat insulating layer 3.
The local part of the diffusion section 5 is sleeved in an expansion hole of the spray pipe shell 4, the surface of the expansion hole is provided with a staggered convex structure, and the convex structure is processed by adopting but not limited to a micro electric spark or an electrochemical method. The convex structure is in a conical shape, a cylindrical shape, a cuboid shape or a frustum pyramid shape. The protruding structure is divided into 4~10 layers, and every layer interval 3mm ~8mm, every layer quantity is 16~40, and the angle of straggling of adjacent two-layer is 6~ 9.
Example 2:
a nozzle structure (namely a nozzle structure) with a diffusion section based on a shell inner surface array projection puncture connection mainly adopts the technical scheme that: the inner surface of the expansion section of the spray pipe shell 4 is provided with a macroscopic array protruding structure formed by micro electric spark machining, the protruding quantity of the macroscopic array can be determined according to the strength of materials and the load of the spray pipe, the protruding array is distributed in a staggered manner on the inner surface of the expansion section of the spray pipe shell 4, the nonmetal diffusion section 5 adopts a special tool to directly press and form fibers or woven materials and glue on the spray pipe shell 4 together, the spray pipe shell 4 and the nonmetal diffusion section 5 are directly connected in a reinforcing manner through the array protruding structure, connection and reinforcement through connecting pieces such as pins are not needed, the spray pipe structure is simplified, the weight of the spray pipe is reduced, and the reliability of the spray pipe is improved due to the absence of structures such as pin holes.
Specifically, a nozzle structure with a diffusion section based on a piercing connection of an array of protrusions on the inner surface of a shell, as shown in fig. 1, comprises: throat insert 1, backing 2, insulation layer 3, nozzle casing 4 and diffuser 5. The throat insert 1 is matched with an inner hole of a back lining 2, the throat insert is used for directly scouring high-temperature and high-pressure resistant gas, the back lining 2 is matched with an inner hole of a heat insulating layer 3, the throat insert is used for directly scouring high-temperature and high-pressure resistant gas, the heat insulating layer 3 is matched with an inner hole of a spray pipe shell 4, the heat conducting of high-temperature gas to the spray pipe shell 4 is resisted, the spray pipe shell 4 is used for providing the structural strength of a spray pipe, the surface of an expansion section of the spray pipe shell 4 is provided with a macroscopic array convex structure, the diffusion section 5 is used for being connected with the diffusion section 5, the diffusion section 5 is used for further expanding the high-temperature and high-pressure gas to do work, and the thrust of a solid rocket engine is provided.
The throat insert 1 is made of high-temperature-resistant metal materials such as tungsten copper or molybdenum titanium zirconium and the like and is used for resisting direct erosion of high-temperature and high-pressure fuel gas, the throat insert 1 is provided with a first inner hole which is a high-temperature and high-pressure fuel gas channel, the left section of the first inner hole is a convergent profile, the right section of the first inner hole is a straight profile and is used for bearing erosion of the high-temperature and high-pressure fuel gas, and the throat insert 1 is fixedly connected with the back lining 2 through bonding; the back lining 2 is provided with a second inner hole, the throat insert 1 is positioned in the second inner hole of the back lining 2, the right end face does not exceed the second inner hole of the back lining 2, the back lining 2 is made of ablation-resistant non-metallic materials such as carbon fiber phenolic aldehyde and the like and is used for high-temperature thermal ablation resistance and high-temperature air flow erosion downstream of the straight line section of the throat insert, the matching surface of the back lining 2 and the heat-insulating layer 3 has a certain turning inclination angle which is used for enabling the heat-insulating layer 3 to bear certain load and limiting when the back lining 2 is installed, and the back lining 2 and the heat-insulating layer 3 are fixedly connected through bonding; the heat insulation layer 3 is provided with a third inner hole, the back lining 2 is positioned in the third inner hole of the heat insulation layer 3, the heat insulation layer 3 is made of low-heat-conductivity non-metallic materials such as glass fiber reinforced plastics and the like and used for resisting heat conduction of high-temperature gas to the spray pipe shell 4, and the heat insulation layer 3 is fixedly connected with the spray pipe shell 4 through bonding; the spray pipe shell 4 is made of metal materials and used for providing structural strength of a spray pipe, the spray pipe shell 4 is provided with a fourth inner hole and an expansion section, the fourth inner hole is a step hole and used for mounting and limiting the heat insulation layer 3, the inner surface of the expansion section of the spray pipe shell 4 is provided with a macro array bulge structure formed by processing in a micro electric spark mode or an electrochemical mode and the like, the number of the macro array bulges is determined according to the strength of the materials and the load of the spray pipe, the array bulge structure is distributed on the inner surface of the expansion section of the spray pipe shell in a staggered mode, the outer circular surface of the spray pipe shell 4 is of a step-shaped structure, a sealing groove structure is designed at the step part and used for mounting and limiting an upstream combustion chamber or a gas pipeline, and the connection between the spray pipe shell 4 and the upstream combustion chamber or the gas pipeline can adopt a pin mode or a thread mode; the diffuser section 5 is directly molded by fiber or woven material and glue on the nozzle shell 4 by using special tools.
Wherein, the right end of the back lining 2 is provided with a margin in the processing process, and the inner surface of the spray pipe structure is integrally processed and formed according to the requirement of the spray pipe molded surface after the diffusion section 5 is pressed and formed.
As shown in fig. 2 to 4, in the present embodiment, the inner surface of the expansion section of the nozzle housing 4 has an array of circular truncated cone-shaped protruding structures arranged in a staggered manner, the central line of the circular truncated cone is perpendicular to the inner surface of the nozzle housing 4, and the top of the circular truncated cone faces the inner side of the nozzle. The diameter of the bottom surface of the circular truncated cone is phi 1mm, the height of the bottom surface of the circular truncated cone is 0.6mm, and the included angle between the generatrix of the circular truncated cone and the ground is 60 degrees. The circular truncated cone array comprises 5 layers, the distance between every two layers is 4mm, the number of the circular truncated cones in each layer is 24, the circular truncated cones in each layer are uniformly distributed, and the staggered angle between every two adjacent layers is 7.5 degrees. The protruding structure can be designed into a circular truncated cone type structure, a cylindrical type structure, a rectangular type structure, a truncated pyramid type structure and the like.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (4)
1. A nozzle structure is characterized by comprising a throat insert (1), a back lining (2), a heat insulating layer (3), a nozzle shell (4) and a diffusion section (5);
the throat insert (1) is positioned in the back lining (2) and is used for resisting direct scouring of the fuel gas flow; the throat insert (1) and the backing (2) are both located within the heat insulating layer (3), the backing (2) being configured to resist erosion by the gas stream downstream of the throat insert (1); the jet pipe shell (4) is sleeved on the heat insulation layer (3), and the heat insulation layer (3) is used for isolating the heat conduction of the throat insert (1) and the back lining (2) to the jet pipe shell (4); the local part of the diffuser section (5) is sleeved in the spray pipe shell (4), the surface of the spray pipe shell (4) sleeved with the diffuser section (5) is provided with a convex structure, and the diffuser section (5) is directly molded on the spray pipe shell (4);
the nozzle shell (4) is used for supporting the whole nozzle structure;
a second inner hole is formed in the back lining (2), the throat lining (1) is located in the second inner hole, and the back lining (2) is made of carbon fiber phenolic materials;
the end of the back lining (2) close to the incoming gas flow is larger than the end far away from the incoming gas flow, the throat insert (1) and the back lining (2) are both positioned in the heat insulation layer (3), and the end of the back lining (2) close to the incoming gas flow limits the position of the back lining (2) in the heat insulation layer (3);
a fourth inner hole and an expansion hole are formed in the spray pipe shell (4); the fourth inner hole is a stepped hole and is used for limiting the heat insulation layer (3);
the local part of the diffusion section (5) is sleeved in an expansion hole of the spray pipe shell (4), the surface of the expansion hole is provided with a staggered convex structure, and the convex structure is processed by adopting a micro electric spark or electrochemical method;
the convex structure is conical, cylindrical, cuboid or prismatic frustum;
the protruding structure is divided into 4-10 layers, the distance between every two layers is 3 mm-8 mm, the number of every layer is 16-40, and the staggered angle between every two adjacent layers is 6-9 degrees.
2. A nozzle arrangement according to claim 1, characterised in that the throat insert (1) is provided with a first bore; the first inner hole is divided into two sections, wherein one section close to the incoming gas flow is a convergent profile, and the other section far away from the incoming gas flow is a straight profile.
3. A spout construction according to claim 1, characterized in that the throat insert (1) is fixedly attached to the backing (2) by bonding.
4. A lance structure according to any one of claims 1 to 3, wherein the heat insulating layer (3) is formed of a glass reinforced plastics material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910955426.5A CN110608109B (en) | 2019-10-09 | 2019-10-09 | Spray pipe structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910955426.5A CN110608109B (en) | 2019-10-09 | 2019-10-09 | Spray pipe structure |
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| CN110608109A CN110608109A (en) | 2019-12-24 |
| CN110608109B true CN110608109B (en) | 2021-10-01 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459921B (en) * | 2020-11-13 | 2022-07-05 | 上海新力动力设备研究所 | Integral air injection device with multiple obliquely-cut spray pipes and air injection method |
| CN114251196B (en) * | 2021-09-26 | 2023-02-07 | 北京中科宇航技术有限公司 | Variable expansion ratio spray pipe of single-chamber double-thrust solid rocket engine |
| CN114131797A (en) * | 2021-11-05 | 2022-03-04 | 湖北三江航天江北机械工程有限公司 | Forming method and forming die for spray pipe with heat insulation layer |
| CN115711188B (en) * | 2022-11-21 | 2024-06-04 | 北京中科宇航技术有限公司 | Structure for improving sealing performance of bonding interface of integral molded spray pipe |
| CN116160721B (en) * | 2023-02-03 | 2024-05-14 | 武汉理工大学 | Rocket nozzle preparation system |
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| CN110608109A (en) | 2019-12-24 |
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