CN109296474A - A kind of rocket engine - Google Patents
A kind of rocket engine Download PDFInfo
- Publication number
- CN109296474A CN109296474A CN201811129627.1A CN201811129627A CN109296474A CN 109296474 A CN109296474 A CN 109296474A CN 201811129627 A CN201811129627 A CN 201811129627A CN 109296474 A CN109296474 A CN 109296474A
- Authority
- CN
- China
- Prior art keywords
- engine
- head
- throat
- diffuser
- combustion portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 34
- 239000000446 fuel Substances 0.000 claims abstract description 32
- 239000002826 coolant Substances 0.000 claims abstract description 23
- 239000007800 oxidant agent Substances 0.000 claims abstract description 22
- 230000001590 oxidative effect Effects 0.000 claims abstract description 22
- 239000000945 filler Substances 0.000 claims abstract description 16
- 238000000465 moulding Methods 0.000 claims abstract description 9
- 230000008450 motivation Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 239000007921 spray Substances 0.000 abstract description 13
- 238000007493 shaping process Methods 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 17
- 238000010146 3D printing Methods 0.000 description 6
- 238000003754 machining Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 239000003380 propellant Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001737 promoting effect Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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
-
- 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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- 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
- F02K9/97—Rocket nozzles
Abstract
The present invention is suitable for field of aerospace technology, provide a kind of rocket engine, it include: head injector, oxidant inlet, head flanges, fuel connecting line, fuel inlet, engine combustion portion, engine throat, engine diffuser and engine fuselage coolant flow channel, head injector, oxidant inlet, head flanges, fuel inlet, engine throat, engine diffuser and the design of engine fuselage coolant flow channel integrated molding；Oxidant inlet and fuel inlet are formed on head injector, head flanges are formed in the periphery of head injector, head injector is connected to engine combustion portion, engine combustion portion is connected to engine throat, engine throat is connected to engine diffuser, and engine fuselage coolant flow channel is formed in engine combustion portion and is connect by fuel conduit with engine head ejector filler.Solve that coolant flow channel is complex-shaped, headset is excessive, ejector filler spray runner complicated difficult is with problems such as machine-shapings.
Description
Technical field
The present invention is suitable for field of aerospace technology more particularly to a kind of rocket engine.
Background technique
Rocket and spacecraft need the support of power propulsion system during becoming rail, posture adjustment, and rocket engine
It is the component part of the most critical of space propultion dynamical system.
The ejector filler of rocket motor chain-drive section and the shape of combustion chamber be directly related to engine fuel whether be sufficiently mixed,
Full combustion, to be directly related to the performance of engine.However, being limited by machining, it is difficult to complete complexity
Runner form and make the more preferable of propellants.Simultaneously because head and combustion chamber non-integral design, when assembly, will also be related to
And sealing problem to head and combustion chamber connectivity problem and between the two, this makes engine, and there are weight increase and reliabilities
The problem of reduction.
Summary of the invention
Rocket engine provided by the invention, it is intended to solve rocket engine since components are more, manufacture difficulty it is big and
The problem of reducing the performance of rocket engine.
The invention is realized in this way a kind of rocket engine, comprising: head injector, oxidant inlet, head method
Blue, fuel connecting line, fuel inlet, engine combustion portion, engine throat, engine diffuser and engine fuselage are cooling
Runner, the head injector, the oxidant inlet, the head flanges, the fuel inlet, the engine throat,
The engine diffuser and engine fuselage coolant flow channel integrated molding design；The oxidant inlet and the combustion
Material entrance is formed on the head injector, and the head flanges are formed in the periphery of the head injector, the head
Ejector filler is connected to the engine combustion portion, and the engine combustion portion is connected to the engine throat, the engine
Throat is connected to the engine diffuser, and the engine fuselage coolant flow channel is formed in the engine combustion portion and leads to
The fuel conduit is crossed to connect with the engine head ejector filler.
Further, the head flanges include four fixed parts, and four fixed parts are along the head spray
The circumferential spaced set of device, each fixed part have been respectively formed on fixation hole.
Further, multiple mounting holes are formed on the engine diffuser, each mounting hole starts described in
The circumferential spaced set of machine diffuser.
Further, the engine combustion portion, the engine throat and the engine diffuser are in hollow
Tubular setting, the diameter of the engine throat are less than the diameter in the engine combustion portion, the engine diffuser it is interior
Portion space is in cone.
The beneficial effect of rocket engine provided in an embodiment of the present invention is: the head spray of rocket engine of the invention
Infuse device, oxidant inlet, head flanges, fuel inlet, engine throat, engine diffuser and engine fuselage coolant flow channel
Integrated molding design, is then manufactured by 3D printing technique；Solve that coolant flow channel is complex-shaped, the meticulous machining work of runner
Skill is complicated, headset is excessive, ejector filler spray runner complicated difficult with problems such as machine-shapings reduces rocket engine
Components, greatly improve the performance of rocket engine.
Detailed description of the invention
Fig. 1 is the overall structure diagram of rocket engine provided by the invention.
Wherein, each appended drawing reference in figure:
1- head injector；11- oxidant inlet；12- fuel inlet；13- fixed part；131- fixation hole；The head 2- method
It is blue；3- fuel connecting line；4- engine combustion portion；5- engine throat；6- engine diffuser；61- mounting hole.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
Distinguishing characteristics between the present invention and the prior art is:
Head injector 1, oxidant inlet 11, head flanges 2, fuel inlet 12, engine throat 5, engine diffusion
Section 6 and the design of engine fuselage coolant flow channel integrated molding；Oxidant inlet 11 and fuel inlet 12 are formed in head spray
On device 1, head flanges 2 are formed in the periphery of head injector 1, and head injector 1 is connected to engine combustion portion 4, engine
Combustion section 4 is connected to engine throat 5, and engine throat 5 is connected to engine diffuser 6, engine fuselage coolant flow channel (figure
Do not show) it is formed in engine combustion portion 4 and is connect by fuel conduit with engine head ejector filler 1.
The beneficial effect of rocket engine provided in an embodiment of the present invention is: the head spray of rocket engine of the invention
Infuse device 1, oxidant inlet 11, head flanges 2, fuel inlet 12, engine throat 5, engine diffuser 6 and engine fuselage
The design of coolant flow channel integrated molding, is then manufactured by 3D printing technique；Solve that coolant flow channel is complex-shaped, runner is meticulous
Process for machining is complicated, headset is excessive, ejector filler spray runner complicated difficult with problems such as machine-shapings reduces fire
The components of arrow engine greatly improve the performance of rocket engine.
Embodiment one
A kind of rocket engine, comprising: head injector 1, oxidant inlet 11, head flanges 2, fuel connecting line 3,
Fuel inlet 12, engine combustion portion 4, engine throat 5, engine diffuser 6 and engine fuselage coolant flow channel, head spray
Infuse device 1, oxidant inlet 11, head flanges 2, fuel inlet 12, engine throat 5, engine diffuser 6 and engine fuselage
The design of coolant flow channel integrated molding；Oxidant inlet 11 and fuel inlet 12 are formed on head injector 1, head flanges 2
It is formed in the periphery of head injector 1, head injector 1 is connected to engine combustion portion 4, engine combustion portion 4 and engine
Throat 5 is connected to, and engine throat 5 is connected to engine diffuser 6, and engine fuselage coolant flow channel is formed in engine combustion portion
It is connect on 4 and by fuel conduit with engine head ejector filler 1.Oxidant is by oxidant inlet 11 in engine working process
It is directly entered engine head ejector filler 1, fuel enters engine fuselage coolant flow channel by fuel inlet 12, carries out to engine
Enter motivation head injector 1 through fuel connecting tube after cooling, oxidant, fuel are in combustion chamber mixing, burning, high temperature and pressure combustion
Gas is ejected through engine throat 5 and engine diffuser 6, forms thrust.Head injector 1, oxidant inlet 11, head
Flange 2, fuel inlet 12, engine throat 5, engine diffuser 6 and the design of engine fuselage coolant flow channel integrated molding,
Then it is manufactured by 3D printing technique；Solve that coolant flow channel is complex-shaped, the meticulous process for machining of runner is complicated, headset
Excessively, ejector filler spray runner complicated difficult is with problems such as machine-shapings, while reducing the components of rocket engine, mentions significantly
The performance of rocket engine is risen.
Embodiment two
The present embodiment is a kind of improved procedure based on embodiment one, and head flanges 2 include four fixed parts 13, and four solid
Portion 13 is determined along the circumferential spaced set of head injector 1, and each fixed part 13 has been respectively formed on fixation hole 131.Rocket motor
The head flanges 2 of machine and head injector 1 are integrally formed by 3D printing technique, solve that headset is excessive, ejector filler sprays
Beam road complicated difficult is with problems such as machine-shapings.Four fixed parts 13 are equally spacedly formed on the periphery of head injector 1, are led to
Crossing fixation hole 131, head injector 1 can be fixed with external equipment well.
Embodiment three
The present embodiment is a kind of improved procedure based on embodiment one, is formed with multiple mounting holes on engine diffuser 6
61, circumferential spaced set of each mounting hole 61 along engine diffuser 6.The tail portion of the namely engine of engine diffuser 6,
Its direction determines the direction of engine jet, and the effect of multiple mounting holes is the long jet pipe of connection more securely, realizes short spray
Pipe engine transitions growth jet pipe engine.
Example IV
The present embodiment is a kind of improved procedure based on embodiment one, engine combustion portion 4, engine throat 5 and is started
Machine diffuser 6 is arranged in hollow tube-shape, and the diameter of engine throat 5 is less than the diameter in engine combustion portion 4, engine diffusion
The inner space of section 6 is in cone.Propellant burns in engine combustion portion 4 generates the gas of high temperature and pressure, by starting
Machine throat 5 accelerates, then is sprayed by engine diffuser 6, and the inner space of engine diffuser 6 is in cone, by that will expand
The mode that scattered section is gradually expanded increases promoting area and obtaining stable thrust for high-temperature gas.
Head injector, oxidant inlet, head flanges, fuel inlet, the engine larynx of rocket engine of the invention
Portion, engine diffuser and the design of engine fuselage coolant flow channel integrated molding, are then manufactured by 3D printing technique；It solves
Coolant flow channel is complex-shaped, the meticulous process for machining of runner is complicated, ejector filler spray runner complicated difficult is with difficulties such as machine-shapings
Topic, while reducing the components of rocket engine, greatly improve the performance of rocket engine.The head method of rocket engine
It is blue to be integrally formed with head injector by 3D printing technique, solve headset excessively, ejector filler spray runner complicated difficult
With problems such as machine-shapings.Four fixed parts are equally spacedly formed on the periphery of head injector, can be very by fixation hole
Head injector and external equipment are fixed well；The effect of multiple mounting holes is the long jet pipe of connection more securely, real
Existing short jet pipe engine transitions growth jet pipe engine.Propellant burns in engine combustion portion generates the gas of high temperature and pressure
Body, by engine, throat accelerates, then is sprayed by engine diffuser, and the inner space of engine diffuser is in cone,
Increase the thrust for promoting area stable with acquisition of high-temperature gas in such a way that diffuser is gradually expanded.
The above is merely preferred embodiments of the present invention, be not intended to limit the invention, it is all in spirit of the invention and
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within principle.
Claims (4)
1. a kind of rocket engine, comprising: head injector, oxidant inlet, head flanges, fuel connecting line, fuel enter
Mouthful, engine combustion portion, engine throat, engine diffuser and engine fuselage coolant flow channel, it is characterised in that: the head
Portion's ejector filler, the oxidant inlet, the head flanges, the fuel inlet, the engine throat, the engine expand
Dissipate section and engine fuselage coolant flow channel integrated molding design；The oxidant inlet and the fuel inlet are formed in
On the head injector, the head flanges are formed in the periphery of the head injector, the head injector with it is described
The connection of engine combustion portion, the engine combustion portion are connected to the engine throat, the engine throat and the hair
The connection of motivation diffuser, the engine fuselage coolant flow channel are formed in the engine combustion portion and by the cartridges
Road is connect with the engine head ejector filler.
2. rocket engine as described in claim 1, it is characterised in that: the head flanges include four fixed parts, four
For the fixed part along the circumferential spaced set of the head injector, each fixed part has been respectively formed on fixation hole.
3. rocket engine as described in claim 1, it is characterised in that: be formed with multiple installations on the engine diffuser
Hole, circumferential spaced set of each mounting hole along the engine diffuser.
4. rocket engine as described in claim 1, it is characterised in that: the engine combustion portion, the engine throat
It is in hollow tube-shape setting with the engine diffuser, the diameter of the engine throat is less than the engine combustion portion
Diameter, the inner space of the engine diffuser is in cone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811129627.1A CN109296474A (en) | 2018-09-27 | 2018-09-27 | A kind of rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811129627.1A CN109296474A (en) | 2018-09-27 | 2018-09-27 | A kind of rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109296474A true CN109296474A (en) | 2019-02-01 |
Family
ID=65164829
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811129627.1A Pending CN109296474A (en) | 2018-09-27 | 2018-09-27 | A kind of rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109296474A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021101568A1 (en) * | 2019-11-22 | 2021-05-27 | Aerojet Rocketdyne, Inc. | Catalytic thruster |
| RU2800409C1 (en) * | 2019-11-22 | 2023-07-21 | Аэроджет Рокетдайн, Инк. | Catalytic thruster |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180010553A1 (en) * | 2016-07-07 | 2018-01-11 | Airbus Ds Gmbh | Rocket engine |
| US20180087443A1 (en) * | 2016-09-01 | 2018-03-29 | Additive Rocket Corporation | Additive manufactured combustion engine |
| CN209011970U (en) * | 2018-09-27 | 2019-06-21 | 宁波天擎航天科技有限公司 | A kind of rocket engine |
-
2018
- 2018-09-27 CN CN201811129627.1A patent/CN109296474A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180010553A1 (en) * | 2016-07-07 | 2018-01-11 | Airbus Ds Gmbh | Rocket engine |
| US20180087443A1 (en) * | 2016-09-01 | 2018-03-29 | Additive Rocket Corporation | Additive manufactured combustion engine |
| CN209011970U (en) * | 2018-09-27 | 2019-06-21 | 宁波天擎航天科技有限公司 | A kind of rocket engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021101568A1 (en) * | 2019-11-22 | 2021-05-27 | Aerojet Rocketdyne, Inc. | Catalytic thruster |
| RU2800409C1 (en) * | 2019-11-22 | 2023-07-21 | Аэроджет Рокетдайн, Инк. | Catalytic thruster |
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