CN106050474A - Novel connecting structure for head and regenerative cooling body of rocket engine - Google Patents
Novel connecting structure for head and regenerative cooling body of rocket engine Download PDFInfo
- Publication number
- CN106050474A CN106050474A CN201610345885.8A CN201610345885A CN106050474A CN 106050474 A CN106050474 A CN 106050474A CN 201610345885 A CN201610345885 A CN 201610345885A CN 106050474 A CN106050474 A CN 106050474A
- Authority
- CN
- China
- Prior art keywords
- body portion
- head
- generatively cooled
- cooled body
- welding
- 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.)
- Granted
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/54—Leakage detectors; Purging systems; Filtration systems
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention discloses a novel connecting structure for a head and a regenerative cooling body of a rocket engine. The novel connecting structure for the head and the regenerative cooling body of the rocket engine comprises the head, the regenerative cooling body, a connecting ring and a filter screen. An installation groove is formed in the head in the direction of an injection panel and used for positioning a combustion chamber section of the regenerative cooling body. A first weld joint is arranged on the outer side of the head and used for welding the big end of the connecting ring through a high energy beam. A second weld joint is arranged on the outer side of the inner wall of the combustion chamber section of the regenerative cooling body and used for welding the head through the high energy beam. A third weld joint is arranged on the outer side of the outer wall of the regenerative cooling body and used for argon arc welding of the small end of the connecting ring. The filter screen is fixed to the inner side of the connecting ring in a spot welded mode through a filter framework. A plurality of unthreaded holes are evenly formed in the filter framework. According to the novel connecting structure for the head and the regenerative cooling body of the rocket engine, the number of the weld joints is small, overlapped weld joints are avoided, and the connecting structure is high in reliability; numerical-control welding can be achieved easily, and the weld penetration consistency is good; through the arrangement of the coolant filter screen, the capacity to resist redundant pollutants of the engine is improved; and in addition, the appearance quality of the engine is good, and the expansibility is high.
Description
Technical field
The present invention relates to spacecraft propulsion system technical field, specifically a kind of rocket motor chain-drive section and re-generatively cooled body
The new Joining Structure in portion.
Background technology
Electromotor is the heart of the spacecraft such as carrier rocket, satellite, and becoming rail posture adjustment for spacecraft provides power.In electromotor
Portion's ignition temperature reaches 3000 DEG C, far above the use temperature upper limit of engine material, it is therefore necessary to consider engine cool problem.
For high thrust motor, generally using re-generatively cooled method, it is achieved engine long time steady operation, this electromotor is referred to as
Re-generatively cooled electromotor.
The thrust chamber of re-generatively cooled electromotor generally comprises head and re-generatively cooled body portion, the metal material generally used,
Such as rustless steel, nickel, copper-silver-zircaloy or nickel-base heat resisting superalloy.For the propellant of re-generatively cooled typically by re-generatively cooled body
Portion's jet pipe end flows into, and flows through the cooling jacket in re-generatively cooled body portion wall, and flows out from re-generatively cooled body portion combustion section, then
Electromotor ejector filler is flowed into junction, re-generatively cooled body portion through head.
Engine head generally uses Welding Structure to be connected with re-generatively cooled body portion, and its attachment structure connects in including a body
Connect with outside head body, be connected in head body isolate high-temperature fuel gas and re-generatively cooled propellant, be connected to isolate again outside head body
Raw food but propellant and use environment.
Making a general survey of technology status at home and abroad, the connected mode in engine head and re-generatively cooled body portion is varied, it may have
A lot of successful cases, but generally there is following deficiency:
1) structure is complicated, and production and processing difficulty is big；
2) weld seam is densely distributed, there is weld seam secondary welding problem；
3) using manual argon arc welding, weld penetration is difficult to ensure that more；
4) outward appearance is poor.
Summary of the invention
For the above-mentioned technical problem of solution, the invention provides a kind of rocket motor chain-drive section and re-generatively cooled body portion
New Joining Structure, it is achieved that engine head is reliably connected with re-generatively cooled body portion, make simultaneously coolant can by again raw food
But body portion flows into head.
The purpose of the present invention is achieved through the following technical solutions: a kind of rocket motor chain-drive section and re-generatively cooled body portion
New Joining Structure, including head, re-generatively cooled body portion, connects ring and drainage screen, and head spray panel direction is provided with installation
Groove, for positioning the combustion section in re-generatively cooled body portion, arranges the first weld seam outside described head, for high energy beam current welding even
The big end of T-Ring；Described re-generatively cooled body portion combustion section inner wall outside arranges the second weld seam, for high energy beam current welded header, structure
Connect in becoming head body；Described re-generatively cooled body portion outer exterior wall arranges the 3rd weld seam, connects ring small end for argon arc welding；Described
Drainage screen is fixed on inside connection ring by filter skeleton spot welding, promotes electromotor anti-fifth wheel pollution capacity；Described filtration
It is evenly arranged some unthreaded holes on device skeleton, has made coolant be flowed into head by re-generatively cooled body portion.
Preferably, the thickness of described connection ring is 2mm, big end internal diameter Φ 140mm (tolerance 0.05mm～0.1mm), small end
Internal diameter is Φ 120mm (tolerance 0.05mm～0.2mm), and overall length is 30mm.
Preferably, the thickness of described filter skeleton is 2mm, vertical with the hypotenuse being connected in the middle of ring, is evenly arranged 24
The unthreaded hole of Φ 3, the lower limb of filter skeleton a size of Φ 120mm (tolerance 0.05mm～0.2mm).
Preferably, drainage screen spot welding is fixed on the little side of filter skeleton, and drainage screen precision is 400 μm；
Preferably, described re-generatively cooled body portion combustor end inner wall outside is welded with head 1 by welding lock base frame rank, platform
Be Φ 117mm (tolerance-0.1mm～-0.05mm) along external diameter under rank, on step along external diameter be Φ 120mm (tolerance-0.2mm～-
0.05mm)。
Preferably, described re-generatively cooled body portion combustor end outer exterior wall is welded with being connected ring 3 small end by annular boss,
Annular boss external diameter is Φ 120mm (tolerance-0.2mm～-0.05mm).
Preferably, welding is held greatly by welding lock base frame rank with being connected ring 3 outside described head, along external diameter under lock base frame rank
For Φ 140mm (tolerance-0.1mm～-0.05mm).
Preferably, the internal diameter of described mounting groove is Φ 117mm (tolerance 0.05mm～0.1mm).
Compared with prior art, the method have the advantages that
Weld seam bar number is few, non-overlapping weld seam, and attachment structure reliability is high；Facilitating implementation numerical control welding, weld penetration is consistent
Property is good；By the setting of coolant filtration net, improve electromotor anti-fifth wheel pollution capacity, and electromotor presentation quality be good,
Expansion is strong, it is adaptable to rocket motor chain-drive section and the connection in re-generatively cooled body portion, also has one to connecting between marmon clamp nested structure
Fixed reference.
Accompanying drawing explanation
Fig. 1 is the signal of the new Joining Structure in the embodiment of the present invention a kind of rocket motor chain-drive section and re-generatively cooled body portion
Figure；
Fig. 2 is the enlarged drawing of the A in Fig. 1.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in the technology of this area
Personnel are further appreciated by the present invention, but limit the present invention the most in any form.It should be pointed out that, the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, it is also possible to make some deformation and improvement.These broadly fall into the present invention
Protection domain.
As Figure 1-Figure 2, the new of a kind of rocket motor chain-drive section and re-generatively cooled body portion is embodiments provided
Type attachment structure, including head, re-generatively cooled body portion, connects ring and drainage screen, and head spray panel direction is provided with mounting groove,
For positioning the combustion section in re-generatively cooled body portion, the first weld seam 5 is set outside described head, is welded to connect for high energy beam current
The big end of ring；Described re-generatively cooled body portion combustion section inner wall outside arranges the second weld seam 6, for high energy beam current welded header, structure
Connect in becoming head body；Described re-generatively cooled body portion outer exterior wall arranges the 3rd weld seam 7, connects ring small end for argon arc welding；Institute
State drainage screen to be fixed on inside connection ring by filter skeleton spot welding, promote electromotor anti-fifth wheel pollution capacity；Described mistake
It is evenly arranged some unthreaded holes on filter skeleton, has made coolant be flowed into head by re-generatively cooled body portion.
The thickness of described connection ring 3 is 2mm, and big end internal diameter Φ 140mm (tolerance 0.05mm～0.1mm), small end inner diameter is
Φ 120mm (tolerance 0.05mm～0.2mm), overall length is 30mm.
The thickness of described filter skeleton is 2mm, vertical with the hypotenuse being connected in the middle of ring, is evenly arranged the light of 24 Φ 3
Hole, the lower limb of filter skeleton a size of Φ 120mm (tolerance 0.05mm～0.2mm).
Drainage screen 4 spot welding is fixed on the little side of filter skeleton, and drainage screen precision is 400 μm；
Described re-generatively cooled body portion 2 combustor end inner wall outside is welded with head 1 by welding lock base frame rank, edge under step
External diameter is Φ 117mm (tolerance-0.1mm～-0.05mm), on step along external diameter be Φ 120mm (tolerance-0.2mm～-
0.05mm)。
Described re-generatively cooled body portion 2 combustor end outer exterior wall is welded with being connected ring 3 small end by annular boss, convex annular
Platform external diameter is Φ 120mm (tolerance-0.2mm～-0.05mm).
Outside described head 1 by welding lock base frame rank be connected ring 3 and hold greatly welding, locking under base frame rank along external diameter is Φ
140mm (tolerance-0.1mm～-0.05mm).
The internal diameter of described mounting groove is Φ 117mm (tolerance 0.05mm～0.1mm).
Originally be embodied as assembling process as follows:
S1, connect ring 3 filter skeleton little side spot welding drainage screen 4；
S2, connection ring 3 is inserted in re-generatively cooled body portion 2 combustor end, is pushed into re-generatively cooled body portion 2 peri-laryngeal；
S3, re-generatively cooled body portion 2 is fixed in the mounting groove of head 1, uses high energy beam fluid welding to form weld seam 1, weld seam
Fusion penetration 1.6mm～2.1mm；
S4, connection ring 3 is pushed into head 1 by re-generatively cooled Shen Bu 2 throat position；
S5, employing high energy beam fluid welding form weld seam 2, weld penetration 2.1mm～3.0mm；
S6, employing argon arc welding form weld seam 3.
When being originally embodied as electromotor work, coolant is flowed into by re-generatively cooled body portion 2 nozzle hole end, through re-generatively cooled body
The cooling jacket in portion 2, enters the attachment structure between head 1 and re-generatively cooled body portion 2, leads to subsequently into the radial direction in head 1
Road, flows into engine chamber and participates in combustion reaction.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims, this not shadow
Ring the flesh and blood of the present invention.
Claims (8)
1. a rocket motor chain-drive section and the new Joining Structure in re-generatively cooled body portion, it is characterised in that include head, regeneration
Cooling body portion, connection ring and drainage screen, head spray panel direction is provided with mounting groove, for positioning the combustion in re-generatively cooled body portion
Burn room section, the first weld seam (5) is set outside described head, is welded to connect the big end of ring for high energy beam current；Described re-generatively cooled body
Portion's combustion section inner wall outside arranges the second weld seam (6), for high energy beam current welded header, connects in constituting head body；Described again
Raw food but body portion outer exterior wall arranges the 3rd weld seam (7), connects ring small end for argon arc welding；Described drainage screen passes through filter
Skeleton spot welding is fixed on inside connection ring；Some unthreaded holes have been evenly arranged it on described filter skeleton.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, the thickness of described connection ring 3 is 2mm, and big end internal diameter Φ 140mm, small end inner diameter is Φ 120mm, and overall length is 30mm.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, the thickness of described filter skeleton is 2mm, vertical with the hypotenuse being connected in the middle of ring, is evenly arranged the light of 24 Φ 3
Hole, the lower limb of filter skeleton a size of Φ 120mm.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, drainage screen 4 spot welding is fixed on the little side of filter skeleton, and drainage screen precision is 400 μm.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, described re-generatively cooled body portion 2 combustor end inner wall outside is welded with head 1 by welding lock base frame rank, edge under step
External diameter is Φ 117mm, and step is Φ 120mm along external diameter.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, described re-generatively cooled body portion 2 combustor end outer exterior wall is welded with being connected ring 3 small end by annular boss, convex annular
Platform external diameter is Φ 120mm.
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levy and be, outside described head 1 by welding lock base frame rank be connected ring 3 and hold greatly welding, locking under base frame rank along external diameter is Φ
140mm。
A kind of rocket motor chain-drive section the most according to claim 1 and the new Joining Structure in re-generatively cooled body portion, it is special
Levying and be, the internal diameter of described mounting groove is Φ 117mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610345885.8A CN106050474B (en) | 2016-05-23 | 2016-05-23 | A kind of new Joining Structure in rocket motor chain-drive section and re-generatively cooled body portion |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610345885.8A CN106050474B (en) | 2016-05-23 | 2016-05-23 | A kind of new Joining Structure in rocket motor chain-drive section and re-generatively cooled body portion |
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| Publication Number | Publication Date |
|---|---|
| CN106050474A true CN106050474A (en) | 2016-10-26 |
| CN106050474B CN106050474B (en) | 2017-12-15 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762227A (en) * | 2016-12-26 | 2017-05-31 | 西安航天发动机厂 | A kind of liquid rocket engine thrust chamber body portion high temperature brazing anti-deformation rotating shaft |
| CN107917016A (en) * | 2017-11-29 | 2018-04-17 | 北京航天动力研究所 | A kind of high pressure-bearing precombustion chamber head shell structure |
| CN108488006A (en) * | 2018-03-20 | 2018-09-04 | 北京宇航系统工程研究所 | It is a kind of to weld ultra-thin-wall tank entirely and be suitable for all-welded welding structure |
| CN108979900A (en) * | 2018-08-29 | 2018-12-11 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
| CN109827191A (en) * | 2019-01-17 | 2019-05-31 | 上海空间推进研究所 | A kind of double cooling re-generatively cooled body portion structures of liquid-propellant rocket engine |
| CN110159456A (en) * | 2019-04-16 | 2019-08-23 | 上海空间推进研究所 | Thrust chamber |
| CN111237087A (en) * | 2020-01-19 | 2020-06-05 | 西北工业大学 | Novel active and passive micropore plate composite cooling structure for aerospace power and cooling method |
| CN111997785A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Rocket engine combustion chamber with regenerative cooling structure |
| CN112628021A (en) * | 2020-12-01 | 2021-04-09 | 蓝箭航天空间科技股份有限公司 | Sealing welding method for end part of thrust chamber and rocket engine thrust chamber |
| CN113175393A (en) * | 2021-04-25 | 2021-07-27 | 北京航天动力研究所 | Straight-flow groove type edge film cooling structure of thrust chamber |
| CN114483382A (en) * | 2021-12-29 | 2022-05-13 | 北京航天动力研究所 | 3D prints integration spray tube extension |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762227A (en) * | 2016-12-26 | 2017-05-31 | 西安航天发动机厂 | A kind of liquid rocket engine thrust chamber body portion high temperature brazing anti-deformation rotating shaft |
| CN106762227B (en) * | 2016-12-26 | 2018-02-06 | 西安航天发动机厂 | A kind of liquid rocket engine thrust chamber body portion high temperature brazing anti-deformation rotating shaft |
| CN107917016A (en) * | 2017-11-29 | 2018-04-17 | 北京航天动力研究所 | A kind of high pressure-bearing precombustion chamber head shell structure |
| CN107917016B (en) * | 2017-11-29 | 2024-02-09 | 北京航天动力研究所 | Head shell structure of high-pressure-bearing precombustion chamber |
| CN108488006A (en) * | 2018-03-20 | 2018-09-04 | 北京宇航系统工程研究所 | It is a kind of to weld ultra-thin-wall tank entirely and be suitable for all-welded welding structure |
| CN108979900A (en) * | 2018-08-29 | 2018-12-11 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
| CN109827191B (en) * | 2019-01-17 | 2020-11-10 | 上海空间推进研究所 | Double-cooling regenerative cooling body part structure of liquid rocket engine |
| CN109827191A (en) * | 2019-01-17 | 2019-05-31 | 上海空间推进研究所 | A kind of double cooling re-generatively cooled body portion structures of liquid-propellant rocket engine |
| CN110159456A (en) * | 2019-04-16 | 2019-08-23 | 上海空间推进研究所 | Thrust chamber |
| CN111237087A (en) * | 2020-01-19 | 2020-06-05 | 西北工业大学 | Novel active and passive micropore plate composite cooling structure for aerospace power and cooling method |
| CN111237087B (en) * | 2020-01-19 | 2024-03-22 | 西北工业大学 | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method |
| CN111997785A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Rocket engine combustion chamber with regenerative cooling structure |
| CN112628021A (en) * | 2020-12-01 | 2021-04-09 | 蓝箭航天空间科技股份有限公司 | Sealing welding method for end part of thrust chamber and rocket engine thrust chamber |
| CN113175393A (en) * | 2021-04-25 | 2021-07-27 | 北京航天动力研究所 | Straight-flow groove type edge film cooling structure of thrust chamber |
| CN113175393B (en) * | 2021-04-25 | 2022-07-29 | 北京航天动力研究所 | Straight-flow groove type edge film cooling structure of thrust chamber |
| CN114483382A (en) * | 2021-12-29 | 2022-05-13 | 北京航天动力研究所 | 3D prints integration spray tube extension |
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| Publication number | Publication date |
|---|---|
| CN106050474B (en) | 2017-12-15 |
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