CN208900237U - A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber - Google Patents
A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber Download PDFInfo
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- CN208900237U CN208900237U CN201821404598.0U CN201821404598U CN208900237U CN 208900237 U CN208900237 U CN 208900237U CN 201821404598 U CN201821404598 U CN 201821404598U CN 208900237 U CN208900237 U CN 208900237U
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- liquid rocket
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Abstract
A kind of Liquid Rocket Engine Combustion Chambers inner wall, the Inner Wall of Combustion Chamber outer surface are equipped with technique annular groove and trench wall；The technique annular groove is located at the both ends of Inner Wall of Combustion Chamber outer surface；The trench wall is located at the middle part of Inner Wall of Combustion Chamber outer surface.A kind of Liquid Rocket Engine Combustion Chambers inner wall, had not only been able to satisfy the needs and thermal life demand of modern high performance high thrust liquid-propellant rocket engine thermal protection, but also can solve the process difficulties of diffusion welding (DW) application, and cost is relatively low.
Description
Technical field
The utility model relates to a kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chambers, belong to liquid-propellant rocket engine
Field.
Background technique
Important component of the combustion chamber as liquid-propellant rocket engine, effect are in terms of including three: (1) passing through fuel cold
But channel interlayer is sent into head injector；(2) fuel and mixed oxidant gas are burnt in the combustion chamber and generates high temperature, high pressure
Combustion gas, and accelerate outside high speed ejection by one section of truncated Laval nozzle expansion of combustion chamber, to generate thrust；(3)
Re-generatively cooled protection itself.Key part of the Inner Wall of Combustion Chamber as combustion chamber, effect are to realize coolant and combustion by it
The high efficient heat exchanging for burning room high-temperature fuel gas, enables coolant to take away certain heat, protects combustion chamber not by engine propellant
The huge heat of burning release is burnt out, to guarantee the reliably working of thrust chamber.The fine or not direct relation of Inner Wall of Combustion Chamber design
It can be worked normally to engine.
Currently, Liquid Rocket Engine Combustion Chambers inner wall generally uses zirconium oxygen-free copper or chromium-bronze.Zirconium oxygen-free copper thermal conductivity
Can be good, but calorific intensity is lower, for example the oxyhydrogen engine that current China's hot-fluid is larger, chamber pressure is slightly lower mostly uses in zirconium oxygen-free copper
Wall；Chromium-bronze calorific intensity is high, but heating conduction is relatively poor, such as the liquid oxygen that current China's chamber pressure is higher, hot-fluid is relatively low
Kerosene engine generally mostly uses chromium-bronze inner wall.But with the Important Projects such as China manned moon landing, deep space exploration and heavy type
Carrier rocket develops the continuous promotion of demand, and it is imperative to develop heavy duty liquid rocket engine, and for modern high performance, height
Chamber pressure, high hot-fluid, high thrust liquid-propellant rocket engine, it is high that chamber pressure is generally up to 20MPa or more, combustion chamber heat current density
Up to 100MW/m2More than, continue to use the above copper alloy inner wall that will bring a series of difficulties for reseach of engine.For example, space flight
The high pressures high fever stream high thrust oxyhydrogen engine Inner Wall of Combustion Chamber such as aircraft sustainer SSME, Europe Vulcain crack problem is all
Once becoming the bottleneck of its Project R&D, US and European has done a large amount of work thus, has seriously affected engineering development；China
Certain type high thrust oxyhydrogen engine also often will appear the different crackle of a plurality of length by test run rear body section inner wall for several times, lead to
Data analysis is crossed it can be found that the more back pressure room efficiency of cracked item number and performance are substantially reduced.For this purpose, opening both at home and abroad
The research of new liquid rocket chamber inner wall is opened up, such as China and Europe, the U.S. developed a kind of novel silver zirconium
Copper Inner Wall of Combustion Chamber, but the development cost superelevation of silver-colored zirconium copper inner wall, are disagreed with China's low cost, highly reliable space flight thinking of development
Back.
In addition, to shorten the combustion chamber manufacturing cycle and reducing manufacturing cost, modern age advanced Liquid Rocket Engine Combustion Chambers
The connection type of inside and outside wall mostly uses diffusion welding craft.Compared to electroforming mode, the advantages of diffusion welding (DW) includes three aspects: (1) outer wall
One layer of high-strength alloy or special steel such as S-06 etc. can be used, intensity is high, light-weight, can substantially mitigate body portion weight；(2)
Inside and outside wall can parallel production, the processing of outer wall, the later weldering of inner wall, outer wall can be carried out simultaneously when carrying out inner wall Xiyanping injection
Connecing only needs several days time, and the production cycle greatly shortens with respect to electroforming process；(3) bonding strength of diffusion welding (DW) inside and outside wall is higher than electroforming
Mode.So each main spacefaring nation of recent domestic none not using diffusion welding (DW) combustion chamber as motor power room emphasis
The direction of tackling key problem.But performance can be substantially after diffusion welding (DW) for the zirconium oxygen-free copper inner wall that currently generallys use of China's oxyhydrogen engine
Decline, causes diffusion welding craft that can not promote and apply on high thrust motor；And traditional combustion room interior wall construction generally can
Cause end in burner ends head poor welding quality and welding process cracked, this problem is also to restrict domestic and international diffusion welding (DW)
Technique is widely used in one of the biggest problem of combustion chamber manufacture.
Utility model content
Technical problem to be solved by the utility model is: having overcome the deficiencies of the prior art and provide a kind of liquid rocket hair
Motivation Inner Wall of Combustion Chamber and combustion chamber be both able to satisfy the needs and heat of modern high performance high thrust liquid-propellant rocket engine thermal protection
Requirements for life, and can solve the process difficulties of diffusion welding (DW) application, and cost is relatively low.
The utility model aim is achieved by the following technical programs:
A kind of Liquid Rocket Engine Combustion Chambers inner wall, the Inner Wall of Combustion Chamber outer surface are equipped in technique annular groove and groove
Wall；
The technique annular groove is located at the both ends of Inner Wall of Combustion Chamber outer surface；The trench wall is located at Inner Wall of Combustion Chamber appearance
The middle part in face.
Aforesaid liquid rocket chamber inner wall, groove width L2=2L1~3L1 of each technique annular groove are described
L1 is the end face of Inner Wall of Combustion Chamber and the minimum spacing of technique annular groove.
Aforesaid liquid rocket chamber inner wall, residual wall thickness Δ=δ of 0.8 δ~1.5 of the technique annular groove, institute
Stating δ is trench wall residual thickness.
Aforesaid liquid rocket chamber inner wall, the technique annular groove quantity of described every one end in Inner Wall of Combustion Chamber outer surface
No less than 1.
Aforesaid liquid rocket chamber inner wall, the cross section of the technique annular groove are rectangle or round rectangle.
Aforesaid liquid rocket chamber inner wall, the Liquid Rocket Engine Combustion Chambers inner wall use chromium-zirconium-copper material
Material.
Aforesaid liquid rocket chamber inner wall, using machining mode processing technology annular groove.
A kind of Liquid Rocket Engine Combustion Chambers, the Liquid Rocket Engine Combustion Chambers include outer wall and above-mentioned interior
Wall；
The outer wall is connect with inner wall using diffusion welding (DW).
Aforesaid liquid rocket chamber, the outer wall use GH4169 material or S-06 material.
Aforesaid liquid rocket chamber, the Liquid Rocket Engine Combustion Chambers use Lavalle moulding surface structure.
The utility model has the following beneficial effects: compared with the prior art
(1) the technique groove of the utility model can guarantee that the welding quality of inner wall end is good, experiment proves that welding
End is no longer cracked in journey；
(2) Inner Wall of Combustion Chamber of the utility model uses chromium-zirconium-copper material, and cost is relatively low, and cost is generally adopted with current China
Zirconium oxygen-free copper or chromium-bronze material cost are suitable；
(3) the Inner Wall of Combustion Chamber good heat conductivity of the utility model, thermal coefficient and zirconium oxygen-free copper are close, bigger than chromium-bronze
It is big to improve；
(4) the Inner Wall of Combustion Chamber calorific intensity of the utility model is high, and calorific intensity is suitable with silver-colored zirconium copper, mentions significantly than zirconium oxygen-free copper
It is high；
(5) the Inner Wall of Combustion Chamber thermal fatigue property of the utility model is good, especially suitable for long-life, reusable liquid
Rocket engine；
(6) Inner Wall of Combustion Chamber of the utility model is unobvious in the performance decline for being diffused postwelding.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model Liquid Rocket Engine Combustion Chambers inner wall；
Fig. 2 is the partial enlargement diagram of the utility model technique annular groove, trench wall.
Specific embodiment
The utility model is described in further detail in the following with reference to the drawings and specific embodiments:
A kind of Liquid Rocket Engine Combustion Chambers inner wall, using chromium-zirconium-copper material, the Inner Wall of Combustion Chamber outer surface is equipped with
Technique annular groove 2 and trench wall 1, as depicted in figs. 1 and 2.Lower, good heat conductivity, calorific intensity using chromium-zirconium-copper material cost
Height, thermal fatigue property is good, and performance decline is small after diffusion welding (DW), the service life of Inner Wall of Combustion Chamber not only greatly improved, but also can make to spread
Welding is applied on high thrust motor combustion chamber.And the design of technique annular groove 2 then efficiently solves Inner Wall of Combustion Chamber
End Welding Problems, ensure that welding quality is good, by the multiple validation trial of engineering, the end of Inner Wall of Combustion Chamber is welded
End is no longer cracked in the process.
The technique annular groove 2 is located at the both ends of Inner Wall of Combustion Chamber outer surface, and the quantity of the technique annular groove 2 of every one end is no less than
1, the cross section of technique annular groove 2 is rectangle or round rectangle, is machined mode machine-shaping；The trench wall 1 is located at
The middle part of Inner Wall of Combustion Chamber outer surface.
Groove width L2=2L1~the 3L1, the L1 of each technique annular groove 2 are end face and the technique ring of Inner Wall of Combustion Chamber
The minimum spacing of slot 2, i.e., near Inner Wall of Combustion Chamber end face technique annular groove 2 side wall and Inner Wall of Combustion Chamber end face most narrow spacing
From the value range of L1 is 1mm~3mm.As shown in Figure 2.The residual wall thickness Δ of the technique annular groove=0.8 δ~1.5 δ, it is described
δ is trench wall residual thickness.
The design of the technique annular groove 2 of the utility model then efficiently solves the end Welding Problems of Inner Wall of Combustion Chamber, even if
Cracked great process difficulties are addressed in diffusion welding (DW) application process, be ensure that welding quality, are overcome the prior art
Major defect and technology prejudice, realize application of the diffusion welding craft on high thrust motor combustion chamber.
A kind of Liquid Rocket Engine Combustion Chambers, the Liquid Rocket Engine Combustion Chambers include outer wall and above-mentioned inner wall.
The outer wall is connect with inner wall using diffusion welding (DW), and outer wall uses GH4169 material or S-06 material.The liquid-propellant rocket engine
The chamber pressure that combustion chamber can work is not less than 100MW/m not less than 20MPa, combustion chamber heat current density2。
Embodiment:
A kind of Liquid Rocket Engine Combustion Chambers inner wall, using chromium-zirconium-copper material, Inner Wall of Combustion Chamber outer surface is equipped with technique
Annular groove 2 and trench wall 1.Combustion chamber uses Lavalle moulding surface structure.
Technique annular groove 2 is located at the both ends of Inner Wall of Combustion Chamber outer surface, the quantity of the technique annular groove 2 of every one end in the present embodiment
It is 2, the cross section of technique annular groove 2 is rectangle, using milling machine machine-shaping；The trench wall 1 is located at outside Inner Wall of Combustion Chamber
The middle part on surface, the trench wall 1 are half oblong.
The groove width L2=2.5L1, L1 of each technique annular groove 2 are end face and the technique annular groove of Inner Wall of Combustion Chamber in the present embodiment
2 minimum spacing.The residual wall thickness Δ of technique annular groove=1.0 δ in the present embodiment, δ are trench wall residual thickness, and L1 value is
2mm。
A kind of Liquid Rocket Engine Combustion Chambers, including outer wall and above-mentioned inner wall.The outer wall and inner wall use diffusion welding (DW)
Connection, outer wall use GH4169 material.The chamber pressure that the Liquid Rocket Engine Combustion Chambers can work be 22MPa,
Combustion chamber heat current density is 130MW/m2。
The optimal specific embodiment of the above, only utility model, but the protection scope of the utility model not office
It is limited to this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in
Change or replacement should be covered within the scope of the utility model.
The content being not described in detail in the utility model specification belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of Liquid Rocket Engine Combustion Chambers inner wall, it is characterised in that: the Inner Wall of Combustion Chamber outer surface is equipped with technique ring
Slot and trench wall；
The technique annular groove is located at the both ends of Inner Wall of Combustion Chamber outer surface；The trench wall is located at Inner Wall of Combustion Chamber outer surface
Middle part.
2. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: each technique
Groove width L2=2L1~the 3L1, the L1 of annular groove are the end face of Inner Wall of Combustion Chamber and the minimum spacing of technique annular groove.
3. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: the technique annular groove
Residual wall thickness Δ=0.8 δ~1.5 δ, the δ is trench wall residual thickness.
4. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: in the combustion chamber
The technique annular groove quantity of the every one end in wall outer surface is no less than 1.
5. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: the technique annular groove
Cross section be rectangle or round rectangle.
6. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: the liquid rocket
Engine combustion chamber interior walls use chromium-zirconium-copper material.
7. a kind of Liquid Rocket Engine Combustion Chambers inner wall according to claim 1, it is characterised in that: using machining
Mode processing technology annular groove.
8. a kind of Liquid Rocket Engine Combustion Chambers, it is characterised in that: the Liquid Rocket Engine Combustion Chambers include outer wall and
Inner wall described in one of claim 1~7；
The outer wall is connect with inner wall using diffusion welding (DW).
9. a kind of Liquid Rocket Engine Combustion Chambers according to claim 8, it is characterised in that: the outer wall uses
GH4169 material or S-06 material.
10. a kind of Liquid Rocket Engine Combustion Chambers according to claim 8, it is characterised in that: the liquid rocket hair
Motivation combustion chamber uses Lavalle moulding surface structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821404598.0U CN208900237U (en) | 2018-08-29 | 2018-08-29 | A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821404598.0U CN208900237U (en) | 2018-08-29 | 2018-08-29 | A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208900237U true CN208900237U (en) | 2019-05-24 |
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ID=66570684
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| Application Number | Title | Priority Date | Filing Date |
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| CN201821404598.0U Active CN208900237U (en) | 2018-08-29 | 2018-08-29 | A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869098A (en) * | 2018-08-29 | 2018-11-23 | 北京航天动力研究所 | A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber |
| CN113653573A (en) * | 2021-08-05 | 2021-11-16 | 陕西斯瑞新材料股份有限公司 | Manufacturing method of inner wall blank of combustion chamber of aerospace engine |
-
2018
- 2018-08-29 CN CN201821404598.0U patent/CN208900237U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869098A (en) * | 2018-08-29 | 2018-11-23 | 北京航天动力研究所 | A kind of Liquid Rocket Engine Combustion Chambers inner wall and combustion chamber |
| CN113653573A (en) * | 2021-08-05 | 2021-11-16 | 陕西斯瑞新材料股份有限公司 | Manufacturing method of inner wall blank of combustion chamber of aerospace engine |
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