CN111997785A - Rocket engine combustion chamber with regenerative cooling structure - Google Patents
Rocket engine combustion chamber with regenerative cooling structure Download PDFInfo
- Publication number
- CN111997785A CN111997785A CN202010689949.2A CN202010689949A CN111997785A CN 111997785 A CN111997785 A CN 111997785A CN 202010689949 A CN202010689949 A CN 202010689949A CN 111997785 A CN111997785 A CN 111997785A
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- China
- Prior art keywords
- combustion chamber
- rocket engine
- positioning ring
- fixed
- cooling sleeve
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- Pending
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 81
- 238000001816 cooling Methods 0.000 title claims abstract description 50
- 230000001172 regenerating effect Effects 0.000 title claims abstract description 19
- 239000002826 coolant Substances 0.000 claims abstract description 24
- 238000012360 testing method Methods 0.000 claims abstract description 22
- 239000000463 material Substances 0.000 claims abstract description 11
- 239000010935 stainless steel Substances 0.000 claims abstract description 9
- 229910001220 stainless steel Inorganic materials 0.000 claims abstract description 9
- 239000007921 spray Substances 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 20
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 14
- 238000003466 welding Methods 0.000 claims description 11
- 229910052786 argon Inorganic materials 0.000 claims description 7
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000011161 development Methods 0.000 abstract description 3
- 239000011295 pitch Substances 0.000 description 5
- 239000000956 alloy Substances 0.000 description 4
- 239000003380 propellant Substances 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910001029 Hf alloy Inorganic materials 0.000 description 1
- 229910001209 Low-carbon steel Inorganic materials 0.000 description 1
- AUTWRGZQAIMMQA-UHFFFAOYSA-N [Hf].[Nb] Chemical compound [Hf].[Nb] AUTWRGZQAIMMQA-UHFFFAOYSA-N 0.000 description 1
- 230000003064 anti-oxidating effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004566 building material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000008929 regeneration Effects 0.000 description 1
- 238000011069 regeneration method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910021332 silicide Inorganic materials 0.000 description 1
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 description 1
- 238000007669 thermal treatment Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- 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 discloses a regenerative cooling structure rocket engine combustion chamber, which comprises a combustion chamber (1), a cooling sleeve (2), a positioning ring (3), a coolant interface nozzle (4) and a drainage spiral groove (5), wherein the combustion chamber (1) is of a cavity structure with a throat in the middle, the drainage spiral groove (5) is wound on an outer molded surface (13) of the combustion chamber (1) in a spiral line mode, the positioning ring (3) is of an upper and lower two-half symmetrical structure, a spray pipe molded surface (31) is arranged on the inner surface of the positioning ring, the cooling sleeve (2) is of a cylindrical structure and is sleeved outside the combustion chamber (1), and the cooling sleeve (2) is provided with 2 coolant inlet and outlet interfaces (22) which are fixedly assembled with the coolant interface nozzle (4). The invention meets the test requirements, and simultaneously, the combustion chamber can be integrally processed by selecting the stainless steel material with low price, thereby greatly reducing the project development cost and saving precious consumable resources.
Description
Technical Field
The invention relates to the technical field of rocket engine combustion chambers, in particular to a rocket engine combustion chamber with a regenerative cooling structure, which is mainly applied to projects such as scheme demonstration of new models, pre-research models, high-energy hydrocarbon propellant tests and the like.
Background
At present, materials selected by a rocket engine combustion chamber are all high-price niobium-hafnium alloy or high-temperature alloy materials, a heat-insulating silicide anti-oxidation coating needs to be sprayed on the inner surface and the outer surface of the combustion chamber after machining, the high-temperature alloy coating combustion chamber is high in cost, if the high-temperature alloy materials are not selected, the reliability of the combustion chamber in hot test is difficult to guarantee, particularly, a plurality of sets of combustion chambers need to be matched and used in projects such as scheme demonstration of new models, pre-researched models and high-energy hydrocarbon propellant tests, the situations also belong to a model exploration test stage, unpredictable factors are more, a plurality of sets of high-temperature alloy combustion chambers need to be matched and used in the stage, the project development cost is greatly increased, and precious consumable material resource waste is caused to a certain extent.
Disclosure of Invention
The invention provides a rocket engine combustion chamber with a regenerative cooling structure, which can meet the test requirements by adopting the combustion chamber with the regenerative cooling structure, does not influence the measurement of the test parameters of the engine, and particularly can be integrally processed by selecting a stainless steel material with low price, thereby greatly reducing the project development cost.
The technical scheme adopted by the invention is that the regenerative cooling structure rocket engine combustion chamber comprises a combustion chamber, a cooling sleeve, a positioning ring, a coolant interface nozzle and a drainage spiral groove, wherein the combustion chamber is of a cavity structure with a throat in the middle, the drainage spiral groove is wound on the outer molded surface of the combustion chamber in a spiral line form, the positioning ring is of an upper half and a lower half symmetrical structure, the inner surface of the positioning ring is provided with a spray pipe molded surface which is positioned and installed with the upper surface of the drainage spiral groove at the throat position of the combustion chamber, the cooling sleeve is of a cylindrical structure, is divided, is symmetrical in an upper half and a lower half, is buckled together and sleeved outside the combustion chamber and is welded and fixed with a connecting flange and a fixing flange of the combustion chamber, and the upper surface and the lower surface of the cooling sleeve are respectively provided with.
The combustion chamber is provided with a flange connecting hole, a sealing groove, an outer molded surface of the combustion chamber, a fixed flange and sealing teeth; the flange connecting hole is connected with the injector in a sealing mode through a bolt, the outer molded surface of the combustion chamber is fixed with the drainage spiral groove in a spot welding mode, the fixing flange is installed in a matched mode with the embedded groove of the cooling sleeve and is fixed through an argon arc fillet weld, and the sealing teeth) are matched with the test airtight tool in a sealing mode.
One end of the cooling sleeve is provided with a welding groove which is fixed with a fixed flange of the combustion chamber through an argon arc fillet weld, the other end of the cooling sleeve is provided with a sealing flange connecting hole and an embedding groove, and a standard bolt penetrates through the sealing flange connecting hole to be connected and fixed with the test airtight tool.
The pipeline interface of the coolant interface nozzle is processed into a step table, and the step table is matched with the coolant inlet and outlet interface of the cooling sleeve to be assembled and welded and fixed by argon arc.
The drainage spiral groove is made of common soft steel wires, is wound on the outer molded surface in a spiral line mode at a certain pitch and is fixed with the outer molded surface of the combustion chamber in a spot welding mode.
The combustion chamber, the cooling sleeve and the positioning ring are all made of stainless steel materials.
The cross sections of the upper half and the lower half of the positioning ring are of structures with wide upper parts and narrow lower parts and are used for being matched and fixed with the throat part of the combustion chamber.
The invention has the beneficial effects that: the combustion chamber, the positioning ring and the cooling sleeve are made of stainless steel materials, so that the test cost is low, the purchase is easy, the structure of the combustion chamber is simple, the manufacturability is good, the thermal structure strength of the combustion chamber is stable and reliable, and the combustion chamber can be repeatedly used. Drainage helicla flute adopts ordinary mild steel wire, wind on outer profile according to the helix form with certain pitch, can be according to the structural feature of combustion chamber, it is intensive a little at the winding of throat position, it is sparse a little relatively in other positions, can be better carry out the thermal treatment to the throat position, through the structure that adopts the holding ring, fill combustion chamber throat position outer wall, make cooling sleeve can set the columniform structure into, workable, simple to operate, the holding ring plays fixed effect to the drainage helicla flute simultaneously, and can prevent the coolant liquid at the detention of throat position, and it is fixed with outer profile of combustion chamber through spot welding form. Through the coolant interface mouth that sets up, can control the flow of coolant liquid, the rocket engine combustion chamber that simultaneously adjustment regeneration cooling structure combustion chamber size can replace many models, many thrust magnitudes.
Drawings
FIG. 1 is a schematic structural diagram of a rocket engine combustion chamber with a regenerative cooling structure.
Fig. 2 is a cross-sectional view of fig. 1.
Fig. 3 is a schematic view of the combustion chamber structure.
Fig. 4 is a cross-sectional view of fig. 3.
FIG. 5 is a schematic view of a cooling sleeve construction.
FIG. 6 is a schematic view of a retaining ring.
Fig. 7 is a structural schematic diagram of a coolant interface nozzle.
The labels in the figure are: 1. the device comprises a combustion chamber, 2, a cooling sleeve 3, a positioning ring, 4, a coolant interface nozzle, 5, a flow guide spiral groove, 11, a flange connecting hole, 12, a sealing groove, 13, an outer molded surface of the combustion chamber, 14, a fixed flange, 15 sealing teeth, 21, a welding groove, 22, a coolant inlet and outlet interface, 23, a sealing flange connecting hole, 24, an embedded groove, 31, a spray pipe molded surface, 41 and a step platform.
Detailed Description
The invention will be further described with reference to the accompanying drawings, and as shown in fig. 1 to 7, the invention relates to a regenerative cooling structure rocket engine combustion chamber and a test application method, which mainly comprise a combustion chamber 1, a cooling sleeve 2, a positioning ring 3, a coolant interface nozzle 4, a drainage spiral groove 5 and the like, wherein the combustion chamber 1 is integrally processed by a stainless steel rod, so that the dimensional tolerance and the roughness of the inner profile of the combustion chamber 1 are ensured; the cooling sleeve 2 is integrally processed by a stainless steel bar, and is divided into two parts by linear cutting at a set position; the positioning ring 3 is integrally processed without a steel bar and is divided into two parts along the axis by linear cutting; the stainless steel material can be selected from the following materials: 1Cr18Ni9Ti, 0Cr18Ni9 and Cr17Ni 2. The coolant interface nozzle 4 is a standard straight-through conical opening, and can be a standard part product; the drainage spiral groove 5 is made of a common soft steel wire in the building material market, is wound on the outer molded surface 13 of the combustion chamber in a spiral line mode at a specific thread pitch, and is fixed with the outer molded surface 13 of the combustion chamber in a spot welding mode, and a cooling spiral channel is formed on the outer molded surface 13 of the combustion chamber. The number of the screw pitches can be determined according to the number of the cooling liquid required, for example, the screw pitches can be wound densely at the throat position and can be relatively sparse at other positions, the positioning ring 3 is divided into an upper half and a lower half which are symmetrical, the upper half and the lower half are buckled together and positioned on the cooling spiral channel at the throat position of the combustion chamber 1, so that the positioning ring 3 fills the throat position of the combustion chamber 1, the cooling sleeve 2 can be arranged into a cylinder shape to facilitate processing and acquisition of sectional materials, the upper half and the lower half of the cooling sleeve 2 are buckled together and fixed with the combustion chamber 1 in an argon arc welding mode, and finally, the coolant inlet and outlet port 22 reserved on the coolant port nozzle 4 and the cooling sleeve 2 is welded and fixed to form the combustion chamber with a regenerative cooling structure. The regenerative cooling structure combustion chamber and the injector are connected through bolts to form a rocket engine, the rocket engine is fixedly mounted on a test run rack and connected with a test parameter sensor, and a standard bolt penetrates through a sealing flange connecting hole 11 of the regenerative cooling structure combustion chamber to be connected and fixed with a test airtight tool, so that a sealing tooth 15 is in contact, sealed and matched with the test airtight tool, and the overall airtightness of the ground test system is checked. After the air tightness of the test system is checked to be qualified, a ball head of a coolant pipeline is in contact fit with a sealing surface of a taper opening of a cooling nozzle, the ball head and the sealing surface are fixedly connected through a jacket nut, after all tests are checked and debugged to be qualified before the test, in the process of formal ignition test, a coolant electromagnetic valve or a lever valve is opened 2-3 s before a test propellant is opened to a main line electromagnetic valve every time, so that a coolant circularly flows in a spiral channel, the heat of the wall surface of a combustion chamber of a rocket engine is taken away by the heat transfer of the coolant flowing at a high speed, the temperature of the wall surface of the combustion chamber is effectively controlled within the allowable temperature range of stainless steel materials, the wall surface of the combustion chamber in a gas.
Claims (7)
1. The regenerative cooling structure rocket engine combustion chamber is characterized in that: comprises a combustion chamber (1), a cooling sleeve (2), a positioning ring (3), a coolant interface nozzle (4) and a drainage spiral groove (5), wherein the combustion chamber (1) is of a hollow cavity structure with a throat part in the middle, the drainage spiral groove (5) is wound on an outer molded surface (13) of the combustion chamber in a spiral line form, the positioning ring (3) is of an upper half symmetrical structure and a lower half symmetrical structure, a spray pipe molded surface (31) is arranged on the inner surface of the positioning ring (3), the positioning ring and the upper surface of the drainage spiral groove (5) at the throat part of the combustion chamber (1) are positioned and installed, the cooling sleeve (2) is of a cylindrical structure, the upper half and the lower half symmetrical structure after being separated are buckled together and sleeved outside the combustion chamber (1) and are welded and fixed with a connecting flange and a fixing flange (14) of the combustion chamber (1), and the upper surface and the lower surface of the, which is assembled and fixed with the coolant interface nozzle (4).
2. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: the combustion chamber (1) is provided with a flange connecting hole (11), a sealing groove (12), a combustion chamber outer molded surface (13), a fixed flange (14) and sealing teeth (15); the sealing device is characterized in that the flange connecting hole (11) is in sealing connection with the injector through a bolt, the outer molded surface (13) of the combustion chamber is fixed with the drainage spiral groove (5) in a spot welding mode, the fixing flange (14) is installed in a matched mode with the embedding groove (24) of the cooling sleeve (2) and is fixed through an argon arc fillet weld, and the sealing tooth (15) is in sealing fit with the test airtight tool.
3. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: cooling sleeve (2) one end set up welding groove (21), it is fixed through argon arc fillet weld with mounting flange (14) of combustion chamber (1), cooling sleeve (2) other end sets up sealed flange connecting hole (23) and embedding recess (24), standard bolt passes sealed flange connecting hole (23) and is connected fixedly with experimental airtight frock.
4. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: the pipeline interface of the coolant interface nozzle (4) is processed into a step platform (41) which is matched with the coolant inlet and outlet interface (22) of the cooling sleeve (2) for assembly and argon arc welding fixation.
5. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: the drainage spiral groove (5) adopts a common soft steel wire, is wound on the outer molded surface (13) in a spiral line mode at a certain pitch and is fixed with the outer molded surface (13) of the combustion chamber in a spot welding mode.
6. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: the combustion chamber (1), the cooling sleeve (2) and the positioning ring (3) are all made of stainless steel materials.
7. A rocket engine combustion chamber with a regenerative cooling structure as recited in claim 1 wherein: the cross sections of the upper half and the lower half of the positioning ring (3) are of structures with wide upper parts and narrow lower parts and are used for being matched and fixed with the throat part of the combustion chamber (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010689949.2A CN111997785A (en) | 2020-07-17 | 2020-07-17 | Rocket engine combustion chamber with regenerative cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010689949.2A CN111997785A (en) | 2020-07-17 | 2020-07-17 | Rocket engine combustion chamber with regenerative cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111997785A true CN111997785A (en) | 2020-11-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010689949.2A Pending CN111997785A (en) | 2020-07-17 | 2020-07-17 | Rocket engine combustion chamber with regenerative cooling structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151197A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Cooling drainage structure of thin-wall high-rib round-square casing |
| CN114294679A (en) * | 2022-01-06 | 2022-04-08 | 中南大学 | A composite thermal protection concave combustion chamber |
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | A water-cooled nozzle for an experimental liquid rocket engine |
| CN115614775A (en) * | 2022-08-26 | 2023-01-17 | 西安航天动力研究所 | Cooling unit for improved flow uniformity in cooling channels and regeneratively cooled combustor |
| CN116609067A (en) * | 2023-04-24 | 2023-08-18 | 山西平阳重工机械有限责任公司 | Loading device for cold run-in test of external combustion engine products |
| US11779985B1 (en) * | 2020-11-15 | 2023-10-10 | Herbert U. Fluhler | Fabricating method for low cost liquid fueled rocket engines |
| CN117532131A (en) * | 2024-01-09 | 2024-02-09 | 北京智创联合科技股份有限公司 | Rocket engine combustion chamber and manufacturing method thereof |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11779985B1 (en) * | 2020-11-15 | 2023-10-10 | Herbert U. Fluhler | Fabricating method for low cost liquid fueled rocket engines |
| CN114151197A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Cooling drainage structure of thin-wall high-rib round-square casing |
| CN114294679A (en) * | 2022-01-06 | 2022-04-08 | 中南大学 | A composite thermal protection concave combustion chamber |
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | A water-cooled nozzle for an experimental liquid rocket engine |
| CN115614775A (en) * | 2022-08-26 | 2023-01-17 | 西安航天动力研究所 | Cooling unit for improved flow uniformity in cooling channels and regeneratively cooled combustor |
| CN116609067A (en) * | 2023-04-24 | 2023-08-18 | 山西平阳重工机械有限责任公司 | Loading device for cold run-in test of external combustion engine products |
| CN117532131A (en) * | 2024-01-09 | 2024-02-09 | 北京智创联合科技股份有限公司 | Rocket engine combustion chamber and manufacturing method thereof |
| CN117532131B (en) * | 2024-01-09 | 2024-03-26 | 北京智创联合科技股份有限公司 | Rocket engine combustion chamber and manufacturing method thereof |
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