CN113153575B - Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine - Google Patents
Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine Download PDFInfo
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- CN113153575B CN113153575B CN202110468900.9A CN202110468900A CN113153575B CN 113153575 B CN113153575 B CN 113153575B CN 202110468900 A CN202110468900 A CN 202110468900A CN 113153575 B CN113153575 B CN 113153575B
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- thrust chamber
- chamber body
- channel
- communicated
- coolant
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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
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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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
- F02K9/62—Combustion or thrust chambers
Abstract
The invention provides a reciprocating regenerative cooling integrated thrust chamber body structure for a liquid rocket engine, which belongs to the technical field of liquid rocket engines and comprises the following components: the outer wall of the thrust chamber body is of a sandwich structure consisting of an inner layer and an outer layer, and the front end of the thrust chamber body is provided with a coolant inlet and a coolant outlet which are respectively communicated with the sandwich structure; the interior of the sandwich structure is divided into a plurality of cooling channels by a plurality of axial ribs, each cooling channel comprises an inflow channel and an outflow channel, the inflow channel is communicated with the coolant inlet, and the outflow channel is communicated with the coolant outlet; the inflow channel and the outflow channel communicate at the rear end of the sandwich structure. The inflow channel and the outflow channel in the sandwich structure can realize bidirectional flow heat exchange of the thrust chamber body, realize convergence and diversion, avoid an additional structure of a cooling liquid supply structure and greatly simplify the structure.
Description
Related information of divisional applications
The scheme is a divisional application. The parent application of the division is an invention patent application with the application number of 2020101779456 and the name of the invention being 'reciprocating regenerative cooling integrated thrust chamber body structure for liquid rocket engine', which is filed on 3/13 of 2020.
Technical Field
The invention relates to the technical field of liquid rocket engines, in particular to a reciprocating type regenerative cooling integrated thrust chamber body structure for a liquid rocket engine.
Background
The thrust chamber of the liquid rocket engine consists of an injector, a combustion chamber and a jet pipe, and is a component for completing propellant energy conversion and generating thrust in the engine. The regenerative cooling is a common external cooling mode of the body part of the liquid rocket engine, namely, the body part of the thrust chamber adopts a sandwich structure, a cooling medium generally adopts a propellant medium, the medium flows through a regenerative cooling sandwich layer, a large amount of heat of the wall of the combustion chamber is taken away through convection heat exchange, the purpose of cooling the thrust chamber is achieved, the medium flows out of a cooling channel and is sprayed into the combustion chamber through a head injector, and heat exchange energy returns to the combustion chamber again to be recycled and regenerated.
At present, a double-wall or tube bundle type channel structure is adopted in a cooling structure, the cooling structure is realized in a welding mode, the cooling channel is complex and numerous, an inlet and outlet supply structure is difficult to integrate and design, the structure is complex, the number of welding seams is large, a welding process is complex, the difficulty is high, the processing period is long, and the cost is high.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of complex structure of the thrust chamber cooling structure in the prior art, and provide a reciprocating type regenerative cooling integrated thrust chamber body structure for a liquid rocket engine.
In order to solve the above technical problems, the present invention provides a reciprocating regenerative cooling integrated thrust chamber body structure for a liquid rocket engine, comprising:
the outer wall of the thrust chamber body is of a sandwich structure consisting of an inner layer and an outer layer, and the front end of the thrust chamber body is provided with a coolant inlet and a coolant outlet which are respectively communicated with the sandwich structure;
a plurality of axial ribs are arranged in the sandwich structure and are divided into a plurality of cooling channels, each cooling channel comprises an inflow channel and an outflow channel, the inflow channel is communicated with the coolant inlet, and the outflow channel is communicated with the coolant outlet;
axial rib with sandwich structure's rear end has the clearance, the clearance makes inflow channel and outflow channel are in sandwich structure's rear end intercommunication forms annular intermediate layer collection liquid chamber.
Preferably, a plurality of dot matrix protrusions are arranged in the inflow channel and/or the outflow channel at intervals.
Preferably, the inflow channel and the outflow channel are arranged next to each other in succession in the sandwich structure.
Preferably, the method further comprises the following steps: the inlet liquid collecting cavity is positioned at the front end of the thrust chamber body and is arranged around the outer wall of the thrust chamber body; one end of the inlet liquid collection cavity is communicated with the coolant inlet, and the other end of the inlet liquid collection cavity is communicated with the inflow channel.
Preferably, the space between the inlet liquid collecting cavity and the outflow channel is sealed by a first baffle plate.
Preferably, the method further comprises the following steps:
the outlet liquid collecting cavity is positioned at the front end of the thrust chamber body and is arranged around the outer wall of the thrust chamber body; one end of the outlet liquid collection cavity is communicated with the coolant outlet, and the other end of the outlet liquid collection cavity is communicated with the outflow channel.
Preferably, the space between the outlet liquid collecting cavity and the inflow channel is sealed by a second barrier plate.
Preferably, the method further comprises the following steps:
a flange provided at a front end of the thrust chamber body, the coolant inlet and the coolant outlet being provided on an end surface of the flange.
The technical scheme of the invention has the following advantages:
1. the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine provided by the invention has the advantages that the sandwich structure of the outer wall of the thrust chamber body is internally divided into a plurality of inflow channels and outflow channels by a plurality of axial ribs, the inflow channels are communicated with a coolant inlet at the front end of the thrust chamber body, the outflow channels are communicated with a coolant outlet at the front end of the thrust chamber body, and the same sandwich layer can realize bidirectional flow heat exchange on the thrust chamber body; the inflow channel and the outflow channel are communicated at the rear end of the sandwich structure, and the collection and the direction change are realized in the channels; the additional structure of a cooling liquid inlet supply structure is avoided, and the structure is greatly simplified.
2. According to the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine, provided by the invention, the inflow channel and/or the outflow channel are/is internally provided with the plurality of dot matrix protrusions at intervals, so that the one-way circulation area can be increased, and the heat exchange capacity is effectively improved.
3. According to the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine, the inflow channel and the outflow channel are sequentially and adjacently arranged in the sandwich structure, so that the thrust chamber body can be uniformly cooled.
4. The invention provides a reciprocating regenerative cooling integrated thrust chamber body structure for a liquid rocket engine, wherein an inlet liquid collecting cavity is positioned at the front end of a thrust chamber body and is arranged around the outer wall of the thrust chamber body, one end of the inlet liquid collecting cavity is communicated with a coolant inlet, and the other end of the inlet liquid collecting cavity is communicated with an inflow channel; the inlet header can integrate the coolant inlets together, simplifying the overall structure of the thrust chamber.
5. According to the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine, the inlet liquid collecting cavity and the outflow channel are sealed through the first blocking plate, so that the outflow channel is conveniently separated from the inflow channel.
6. According to the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine, an outlet liquid collecting cavity is located at the front end of the thrust chamber body and arranged around the outer wall of the thrust chamber body, one end of the outlet liquid collecting cavity is communicated with the coolant outlet, and the other end of the outlet liquid collecting cavity is communicated with the outflow channel; the outlet liquid collection cavity can integrate the coolant outlet together, and the integral structure of the thrust chamber is simplified.
7. According to the reciprocating type regenerative cooling integrated thrust chamber body structure for the liquid rocket engine, the outlet liquid collecting cavity and the inflow channel are sealed through the second blocking plate, so that the inflow channel and the outflow channel are conveniently separated.
8. The invention provides a reciprocating type regenerative cooling integrated thrust chamber body structure for a liquid rocket engine, wherein a flange is arranged at the front end of a thrust chamber body, and a coolant inlet and a coolant outlet are arranged on the end surface of the flange; the flange is convenient for the thrust chamber to be connected with other parts of the liquid rocket engine, and the coolant inlet and the coolant outlet are integrated on the flange, so that the whole structure of the thrust chamber is compact.
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 perspective view of a reciprocating regenerative cooling integrated thrust chamber for a liquid rocket engine provided in the present invention.
Fig. 2 is a left side view of fig. 1.
Fig. 3 isbase:Sub>A sectional view taken along the linebase:Sub>A-base:Sub>A of fig. 2.
Fig. 4 is an enlarged perspective view of a region B in fig. 3.
FIG. 5 is a schematic diagram of the inner layer structure of the outer wall of the thrust chamber body.
Description of reference numerals:
1. a thrust chamber body; 2. a flange; 3. an accommodating chamber; 4. an outer wall; 5. dot matrix protrusion; 6. a through hole; 7. a coolant inlet; 8. a coolant outlet; 9. mounting holes; 10. an axial rib; 11. an inflow channel; 12. an outflow channel; 13. an interlayer liquid collection cavity; 14. a first liquid collection plate; 15. a second liquid collection plate; 16. an outlet liquid collection chamber; 17. an inlet liquid collection chamber; 18. a first barrier plate; 19. a second blocking plate.
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 obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to 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", etc., 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 particular orientation, be constructed and operated in a particular 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 and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 in specific cases to those skilled in the art.
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.
As shown in fig. 1, the reciprocating regenerative cooling integrated thrust chamber body structure for the liquid rocket engine in the present embodiment can be conveniently manufactured by using an additive manufacturing technology.
As shown in fig. 2 and 3, the thrust chamber includes a thrust chamber body 1 and a flange 2; the middle of the thrust chamber body 1 is provided with a containing cavity 3 for introducing liquid rocket engine fuel, the outer wall 4 of the thrust chamber body 1 is provided with two layers inside, and the inner layer and the outer layer of the outer wall 4 form an annular sandwich structure; the flange 2 is integrated at the front end of the thrust chamber body 1, a through hole 6 formed in the middle of the flange 2 is communicated with the accommodating cavity 3 of the thrust chamber body 1, a coolant inlet 7 and a coolant outlet 8 are respectively formed in two sides of the through hole 6, four mounting holes 9 are symmetrically formed in the periphery of the through hole 6, and the mounting holes 9 are suitable for being connected with other components of the liquid rocket engine.
As shown in fig. 3, 4 and 5, a plurality of axial ribs 10 are arranged along the circumferential direction of the sandwich structure, the bottom ends of the axial ribs 10 are connected with the inner layer of the outer wall 4, the top ends of the axial ribs 10 are connected with the outer layer of the outer wall 4, the sandwich structure is divided into a plurality of cooling channels with equal width, each cooling channel comprises an inflow channel 11 and an outflow channel 12, and the inflow channel 11 and the outflow channel 12 are arranged adjacent to each other in sequence; axial rib 10 with sandwich structure's rear end has the clearance, the clearance makes inflow channel 11 and outflow channel 12 are in sandwich structure's rear end intercommunication forms annular intermediate layer liquid collecting cavity 13. A first liquid collecting plate 14 and a second liquid collecting plate are arranged between the thrust chamber body 1 and the flange 2, the first liquid collecting plate 14 and the second liquid collecting plate 15 are both annular conical plates, and the cross section of the second liquid collecting plate 15 is larger than that of the first liquid collecting plate 14; the first liquid collecting plate 14 is sleeved on the outer wall 4 of the thrust chamber body 1, one end of the first liquid collecting plate is connected with the flange 2, the other end of the first liquid collecting plate is connected with the outer layer of the outer wall 4 of the thrust chamber body 1, and the first liquid collecting plate 14, the flange 2 and the thrust chamber body 1 jointly form an annular outlet liquid collecting cavity 16; one end of the outlet liquid collecting cavity 16 is communicated with the coolant outlet 8, the other end of the outlet liquid collecting cavity is communicated with the outflow channel 12, and a second blocking plate 19 is arranged between the outlet liquid collecting cavity 16 and the inflow channel 11. The second liquid collecting plate 15 is sleeved on the outer wall 4 of the thrust chamber body 1, one end of the second liquid collecting plate is connected with the flange 2, the other end of the second liquid collecting plate is connected with the outer layer of the outer wall 4 of the thrust chamber body 1, and the second liquid collecting plate, the flange 2 and the first liquid collecting plate 14 jointly form an annular inlet liquid collecting cavity 17; one end of the inlet liquid collecting cavity 17 is communicated with the coolant inlet 7, the other end of the inlet liquid collecting cavity is communicated with the inflow channel 11, and a first blocking plate 18 is arranged between the inlet liquid collecting cavity 17 and the outflow channel 12. According to the structure, the coolant enters from the coolant inlet 7, flows through the inflow channel 11, enters the interlayer liquid collecting cavity 13, then enters the outflow channel 12 from the interlayer liquid collecting cavity 13, and finally flows out from the coolant outlet 8 and enters the accommodating cavity 3 of the thrust chamber body 1, so that the regenerative cooling process is realized.
As shown in fig. 5, a plurality of dot matrix protrusions 5 are arranged in the outflow channel 12 and the inflow channel 11 at intervals, the dot matrix protrusions 5 can increase the one-way circulation area, and the heat exchange capacity is effectively improved.
The working process and principle are as follows:
firstly, coolant flows into an inlet liquid collecting cavity 17 from a coolant inlet 7, is dispersed into a plurality of inflow channels 11 of a sandwich structure, flows along the arrow direction of the inflow channels 11 in fig. 4, and carries away heat of the outer wall of a thrust chamber by convective heat exchange to achieve the effect of cooling; meanwhile, the coolant flows are continuously divided and combined through the plurality of dot matrix bulges 5 in the inflow channel 11, and form sufficient forced convection heat exchange with the high-temperature outer wall of the thrust chamber; then, the coolant flowing into the channel 11 is collected into an interlayer liquid collecting cavity 13 at the rear end of the interlayer structure, the coolant is dispersed into a plurality of outflow channels 12 through the interlayer liquid collecting cavity 13, flows along the arrow direction of the outflow channels 12 in fig. 4 to continuously cool and exchange heat with the outer wall structure of the thrust chamber, finally enters an outlet liquid collecting cavity 16, and then flows out from a coolant outlet 8; and finally, the coolant enters the thrust chamber accommodating cavity 3 through a valve, an injector and other structures for combustion, the heat exchange energy is recovered and regenerated, the thrust performance of the engine is continuously contributed, and the cycle work is carried out. On one hand, the temperature of the outer wall of the thrust chamber is reduced by using the heat exchange of the coolant, so that the reliability of the product is improved; on the other hand, heat exchange energy continuously enters the thrust chamber body along with the cooling medium for recycling, product performance is improved, and energy utilization rate is high.
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 invention.
Claims (4)
1. The integrated thrust chamber body portion structure of reciprocating type regenerative cooling for liquid rocket engine, its characterized in that includes:
the thrust chamber comprises a thrust chamber body (1), wherein a containing cavity (3) is formed in the middle of the thrust chamber body (1), an outer wall (4) of the thrust chamber body (1) is of a sandwich structure formed by an inner layer and an outer layer, a coolant inlet (7) and a coolant outlet (8) which are respectively communicated with the sandwich structure are formed in the front end of the thrust chamber body (1), and the coolant outlet (8) can be communicated with the containing cavity (3);
the sandwich structure is internally divided into a plurality of cooling channels by a plurality of axial ribs (10), each cooling channel comprises an inflow channel (11) and an outflow channel (12), the inflow channel (11) is communicated with the coolant inlet (7), and the outflow channel (12) is communicated with the coolant outlet (8);
a gap is reserved between the axial rib (10) and the rear end of the sandwich structure, and the gap enables the inflow channel (11) and the outflow channel (12) to be communicated at the rear end of the sandwich structure to form an annular sandwich liquid collecting cavity (13);
the inlet liquid collecting cavity (17) is positioned at the front end of the thrust chamber body (1) and is arranged around the outer wall (4) of the thrust chamber body (1); one end of the inlet liquid collection cavity (17) is communicated with the coolant inlet (7), and the other end is communicated with the inflow channel (11); the space between the inlet liquid collecting cavity (17) and the outflow channel (12) is sealed by a first baffle plate (18);
the outlet liquid collecting cavity (16) is positioned at the front end of the thrust chamber body (1) and is arranged around the outer wall (4) of the thrust chamber body (1); one end of the outlet liquid collection cavity (16) is communicated with the coolant outlet (8), and the other end of the outlet liquid collection cavity is communicated with the outflow channel (12); the outlet liquid collecting cavity (16) and the inflow channel (11) are closed by a second blocking plate (19).
2. The reciprocating regenerative cooling integrated thrust chamber body structure for a liquid rocket engine according to claim 1, wherein a plurality of dot matrix protrusions (5) are provided at intervals in the inflow channel (11) and/or the outflow channel (12).
3. The reciprocating regenerative cooling integrated thrust cell body structure for a liquid rocket engine according to claim 1, wherein the inflow channel (11) and the outflow channel (12) are arranged next to each other in sequence within the sandwich structure.
4. The reciprocating regenerative cooling integrated thrust chamber body structure for a liquid rocket engine of claim 1, further comprising:
a flange (2) provided at a front end of the thrust chamber body (1), the coolant inlet (7) and the coolant outlet (8) being provided on an end face of the flange (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110468900.9A CN113153575B (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010177945.6A CN111156102A (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
| CN202110468900.9A CN113153575B (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010177945.6A Division CN111156102A (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113153575A CN113153575A (en) | 2021-07-23 |
| CN113153575B true CN113153575B (en) | 2022-11-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010177945.6A Withdrawn CN111156102A (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
| CN202110468900.9A Active CN113153575B (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010177945.6A Withdrawn CN111156102A (en) | 2020-03-13 | 2020-03-13 | Reciprocating type regenerative cooling integrated thrust chamber body structure for liquid rocket engine |
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| CN (2) | CN111156102A (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111878238A (en) * | 2020-07-23 | 2020-11-03 | 西北工业大学 | Double-layer cooling channel for reducing temperature of aircraft component |
| CN112359408A (en) * | 2020-10-22 | 2021-02-12 | 西安理工大学 | Method for reducing flow resistance of 3D printing thrust chamber interlayer cooling structure |
| CN113266492B (en) * | 2021-04-16 | 2022-03-15 | 北京星际荣耀空间科技股份有限公司 | Engine thrust chamber, rocket engine and liquid rocket |
| CN114645803A (en) * | 2022-03-17 | 2022-06-21 | 北京航空航天大学 | Composite material winding regenerative cooling thrust chamber and processing technology |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5616973A (en) * | 1994-06-29 | 1997-04-01 | Yeomans Chicago Corporation | Pump motor housing with improved cooling means |
| RU2158841C2 (en) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Liquid-propellant thrust chamber and its casing |
| WO2010068636A2 (en) * | 2008-12-08 | 2010-06-17 | Firestar Engineering, Llc | Regeneratively cooled porous media jacket |
| 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 |
| CN209818184U (en) * | 2019-02-25 | 2019-12-20 | 蓝箭航天空间科技股份有限公司 | Cooling jacket for thrust chamber of liquid rocket engine and thrust chamber |
| CN110578619A (en) * | 2019-09-29 | 2019-12-17 | 上海空间推进研究所 | regenerative cooling body part of liquid rocket engine and channel structure thereof |
-
2020
- 2020-03-13 CN CN202010177945.6A patent/CN111156102A/en not_active Withdrawn
- 2020-03-13 CN CN202110468900.9A patent/CN113153575B/en active Active
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| CN111156102A (en) | 2020-05-15 |
| CN113153575A (en) | 2021-07-23 |
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