CN110578619A - regenerative cooling body part of liquid rocket engine and channel structure thereof - Google Patents
regenerative cooling body part of liquid rocket engine and channel structure thereof Download PDFInfo
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- CN110578619A CN110578619A CN201910932687.5A CN201910932687A CN110578619A CN 110578619 A CN110578619 A CN 110578619A CN 201910932687 A CN201910932687 A CN 201910932687A CN 110578619 A CN110578619 A CN 110578619A
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- rocket engine
- cooling body
- channel structure
- groove
- liquid rocket
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
the invention relates to a regenerative cooling body part of a liquid rocket engine and a channel structure thereof, wherein the channel structure comprises a coolant inlet, a coolant inlet liquid collecting cavity, an axial groove, a circumferential groove and a coolant outlet; the coolant inlet, the coolant inlet liquid collecting cavity, the axial groove and the coolant outlet are sequentially connected and communicated; the axial grooves are at least two, and each axial groove shares a coolant inlet, a coolant inlet liquid collecting cavity and a coolant outlet; any two adjacent axial grooves are communicated through the circumferential groove. The regenerative cooling body part of the liquid rocket engine and the channel structure thereof are suitable for manufacturing by an additive manufacturing technology.
Description
Technical Field
The invention relates to the field of rocket driving equipment, in particular to a regenerative cooling body part of a liquid rocket engine and a channel structure thereof.
Background
The liquid rocket engine mostly adopts a regenerative cooling mode to realize the cooling of the body part, and adopts liquid oxidant/liquid fuel as a coolant, so that the liquid rocket engine is an effective and economic mode for protecting the thrust chamber from being burnt by heat flow.
The conventional production mode of the liquid rocket engine regeneration cooling body part is to adopt a mode of machining the inner wall and the outer wall and then connecting the inner wall and the outer wall by diffusion welding or brazing, and the liquid rocket engine regeneration cooling body part has the advantages of complex process, long production period, high cost and low production qualified rate. And the material increase manufacturing technology is adopted, the regeneration cooling body is integrally formed, the production cost of the regeneration cooling body can be reduced to a great extent, the production period can be shortened, and structural optimization can be carried out based on the material increase manufacturing technology. However, when the additive manufacturing technology is adopted to produce the regenerative cooling body, the conventional design structure cannot be directly subjected to additive manufacturing, and the adaptability of the structure is a difficult problem to be solved urgently.
Disclosure of Invention
The invention aims to provide a regenerative cooling body part of a liquid rocket engine and a channel structure thereof, which are suitable for manufacturing by an additive manufacturing technology.
In order to achieve the aim, the invention provides a regenerative cooling body part channel structure of a liquid rocket engine, which comprises a coolant inlet, a coolant inlet liquid collecting cavity, an axial groove, a circumferential groove and a coolant outlet, wherein the coolant inlet is communicated with the coolant collecting cavity; the coolant inlet, the coolant inlet liquid collecting cavity, the axial groove and the coolant outlet are sequentially connected and communicated; the axial grooves are at least two, and each axial groove shares a coolant inlet, a coolant inlet liquid collecting cavity and a coolant outlet; any two adjacent axial grooves are communicated through the circumferential groove.
The regenerative cooling body part channel structure of the liquid rocket engine is characterized in that the cross section of the axial groove channel is circular.
the regeneration cooling body part channel structure of the liquid rocket engine is characterized in that the section of the axial groove channel is a gradually-changed section.
The regenerative cooling body part channel structure of the liquid rocket engine is characterized in that the circumferential groove is a double-arc waist-shaped groove.
The regenerative cooling body part channel structure of the liquid rocket engine is characterized in that the coolant outlet comprises a divergent groove and an outlet liquid collecting cavity; the gradually expanding groove is connected with and communicated with the outlet liquid collecting cavity, and the gradually expanding groove is connected with and communicated with the axial groove.
The channel structure of the regeneration cooling body part of the liquid rocket engine is characterized in that the gradually-expanding groove is horn-shaped, one end with a small horn opening is connected with and communicated with the axial groove, and one end with a large horn opening is connected with and communicated with the outlet liquid collection cavity.
The regenerative cooling body part channel structure of the liquid rocket engine is characterized in that the diffusion angle of the divergent groove is 10-20 degrees.
The other technical scheme provided by the invention is that the regeneration cooling body part of the liquid rocket engine is provided with the channel structure of the regeneration cooling body part of the liquid rocket engine in the wall.
Compared with the prior art, the invention has the beneficial effects that:
1. The body part and the channel structure thereof are integrally designed so that the body part is suitable for being produced by adopting an additive manufacturing technology, and the liquid rocket engine has the advantages of short production period, high qualification rate, excellent performance and the like;
2. The regeneration cooling body part of the liquid rocket engine and the channel structure thereof have the advantages that the channel section of the axial groove is circular, and the structure has high structural strength and small flow resistance;
3. The liquid rocket engine regenerates and cools the body and its channel structure, the gradual change cross-sectional design of the axial trough, can change the flow area;
4. The regenerative cooling body part of the liquid rocket engine and the channel structure thereof have a unique circumferential groove structure (a double-arc waist-shaped groove), so that the risk of channel collapse in the production process can be effectively prevented, and smooth transition between axial grooves is realized;
5. The regenerative cooling body part of the liquid rocket engine and the channel structure thereof are designed with a gradually-expanding outlet slot, the diffusion angle of the channel is 20 degrees, and the local resistance loss of the channel can be effectively reduced.
Drawings
The regenerative cooling body part of the liquid rocket engine and the channel structure thereof are provided by the following embodiments and the attached drawings.
FIG. 1 is a schematic view of a liquid rocket engine regenerative cooling body channel structure according to a preferred embodiment of the present invention.
FIG. 2 is a cross-sectional view of an axial slot channel in accordance with a preferred embodiment of the present invention.
FIG. 3 is a cross-sectional view of a circumferential groove channel in a preferred embodiment of the invention.
FIG. 4 is a schematic view of the coolant outlet in the preferred embodiment of the invention.
Detailed Description
The liquid rocket engine regenerative cooling body and the channel structure thereof according to the present invention will be described in further detail with reference to fig. 1 to 4.
FIG. 1 is a schematic view of a liquid rocket engine regenerative cooling body channel configuration according to a preferred embodiment of the present invention.
Referring to fig. 1, a channel structure is placed in the wall of the regenerative cooling body of the liquid rocket engine. The channel structure of the regeneration cooling body part of the liquid rocket engine comprises a coolant inlet 1, a coolant inlet liquid collecting cavity 2, an axial groove 3, a circumferential groove 4 and a coolant outlet 5;
the coolant inlet 1, the coolant inlet liquid collecting cavity 2, the axial groove 3 and the coolant outlet 5 are sequentially connected and communicated to form a coolant axial circulation channel;
The number of the axial grooves 3 is at least two, and each axial groove 3 shares a coolant inlet 1, a coolant inlet liquid collecting cavity 2 and a coolant outlet 5; the circumferential grooves 4 are arranged between any two adjacent axial grooves 3, and the circumferential grooves 4 are communicated with each other to form a circumferential coolant circulation channel; a plurality of circumferential grooves 4 are arranged along the axial direction of the regenerative cooling body part of the liquid rocket engine;
The coolant enters the coolant inlet liquid collecting cavity 2 through the coolant inlet 1, is uniformly distributed through the axial grooves 3 and the circumferential grooves 4, and then flows out through the coolant outlet 5, so that the regenerative cooling body of the liquid rocket engine is cooled.
FIG. 2 is a cross-sectional view of an axial slot channel in a preferred embodiment of the invention.
Referring to fig. 2, the cross section of the axial groove 3 is circular, and the axial groove has the advantages of high structural strength and low flow resistance; along the axial direction, the channel section of the axial groove 3 is a gradual change section.
FIG. 3 is a cross-sectional view of a circumferential groove channel in a preferred embodiment of the invention.
Referring to fig. 3, the circumferential groove 4 is a double-arc waist-shaped groove, that is, the cross section of the groove of the circumferential groove 4 is a double-arc waist-shaped surface, so that the risk of groove collapse in the production process can be effectively prevented, and smooth transition between the axial grooves is realized.
FIG. 4 is a schematic view of the coolant outlet in the preferred embodiment of the invention.
referring to fig. 4, the coolant outlet 5 includes a divergent groove 51 and an outlet header 52; the divergent groove 51 is connected with and communicated with the outlet header chamber 52, and the divergent groove 51 is connected with and communicated with the axial groove 3;
The diffusion angle of the divergent groove 51 can be 10-20 degrees, and the local resistance loss of the channel can be effectively reduced.
The gradually-expanding groove 51 is trumpet-shaped, the end with the small opening of the trumpet is connected with and communicated with the axial groove 3, and the end with the large opening of the trumpet is connected with and communicated with the outlet liquid collecting cavity 52.
The channel structure of the regenerative cooling body part of the liquid rocket engine is suitable for production by adopting an additive manufacturing technology, and has the advantages of production integration, excellent performance and the like.
Claims (8)
1. The regenerative cooling body part channel structure of the liquid rocket engine is characterized by comprising a coolant inlet, a coolant inlet liquid collecting cavity, an axial groove, a circumferential groove and a coolant outlet;
the coolant inlet, the coolant inlet liquid collecting cavity, the axial groove and the coolant outlet are sequentially connected and communicated;
The axial grooves are at least two, and each axial groove shares a coolant inlet, a coolant inlet liquid collecting cavity and a coolant outlet; any two adjacent axial grooves are communicated through the circumferential groove.
2. A liquid rocket engine regenerative cooling body channel structure as recited in claim 1, wherein said axial slot channels are circular in cross-section.
3. a liquid rocket engine regenerative cooling body channel structure as recited in claim 2, wherein said axial slot channel cross-section is of a gradual cross-section.
4. A liquid rocket engine regenerative cooling barrel channel structure as defined in claim 1 wherein said circumferential groove is a double arcuate kidney-shaped groove.
5. A liquid rocket engine regenerative cooling body channel structure as defined in claim 1 wherein said coolant outlet includes a divergent slot and an outlet plenum; the gradually expanding groove is connected with and communicated with the outlet liquid collecting cavity, and the gradually expanding groove is connected with and communicated with the axial groove.
6. A liquid rocket engine regenerative cooling body channel structure as defined in claim 5 wherein said diverging slots are flared, the smaller end of the flare opening communicating with said axial slots and the larger end of the flare opening communicating with said outlet plenum.
7. A liquid rocket engine regenerative cooling body channel structure as defined in claim 5 wherein said diverging slots have a divergence angle of from 10 ° to 20 °.
8. Liquid rocket engine regenerative cooling body, characterized in that the walls are provided with a channel structure of the liquid rocket engine regenerative cooling body as claimed in any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910932687.5A CN110578619A (en) | 2019-09-29 | 2019-09-29 | regenerative cooling body part of liquid rocket engine and channel structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910932687.5A CN110578619A (en) | 2019-09-29 | 2019-09-29 | regenerative cooling body part of liquid rocket engine and channel structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110578619A true CN110578619A (en) | 2019-12-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910932687.5A Pending CN110578619A (en) | 2019-09-29 | 2019-09-29 | regenerative cooling body part of liquid rocket engine and channel structure thereof |
Country Status (1)
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| CN (1) | CN110578619A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112253334A (en) * | 2020-09-29 | 2021-01-22 | 西安航天动力研究所 | Gas pipeline integrated with cooling channel |
| CN112792505A (en) * | 2020-12-31 | 2021-05-14 | 湖北三江航天江北机械工程有限公司 | Inner wall groove structure regeneration cooling body part forming method |
| CN112832928A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN113153575A (en) * | 2020-03-13 | 2021-07-23 | 北京星际荣耀空间科技股份有限公司 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
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| CN104919167A (en) * | 2013-02-19 | 2015-09-16 | 三菱重工业株式会社 | Rocket engine, rocket, and method for starting rocket engine |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
| EP3267024A1 (en) * | 2016-07-07 | 2018-01-10 | Airbus DS GmbH | Rocket engine |
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| US3126702A (en) * | 1964-03-31 | newcomb | ||
| US3066702A (en) * | 1959-05-28 | 1962-12-04 | United Aircraft Corp | Cooled nozzle structure |
| US20050188678A1 (en) * | 2001-12-18 | 2005-09-01 | Volvo Aero Corporation | Component for being subjected to high thermal load during operation and a method for manufacturing such a component |
| CN104919167A (en) * | 2013-02-19 | 2015-09-16 | 三菱重工业株式会社 | Rocket engine, rocket, and method for starting rocket engine |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113153575A (en) * | 2020-03-13 | 2021-07-23 | 北京星际荣耀空间科技股份有限公司 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
| CN112253334A (en) * | 2020-09-29 | 2021-01-22 | 西安航天动力研究所 | Gas pipeline integrated with cooling channel |
| CN112253334B (en) * | 2020-09-29 | 2021-10-19 | 西安航天动力研究所 | Gas pipeline integrated with cooling channel |
| CN112792505A (en) * | 2020-12-31 | 2021-05-14 | 湖北三江航天江北机械工程有限公司 | Inner wall groove structure regeneration cooling body part forming method |
| CN112792505B (en) * | 2020-12-31 | 2022-05-13 | 湖北三江航天江北机械工程有限公司 | Inner wall groove structure regeneration cooling body part forming method |
| CN112832928A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN112832928B (en) * | 2021-03-05 | 2022-04-22 | 中国科学院力学研究所 | Method for designing cooling structure with equal inner wall strength for rocket engine |
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
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Application publication date: 20191217 |