CN108979900A - A kind of collection pendular ring in liquid rocket engine thrust chamber body portion - Google Patents
A kind of collection pendular ring in liquid rocket engine thrust chamber body portion Download PDFInfo
- Publication number
- CN108979900A CN108979900A CN201810995251.6A CN201810995251A CN108979900A CN 108979900 A CN108979900 A CN 108979900A CN 201810995251 A CN201810995251 A CN 201810995251A CN 108979900 A CN108979900 A CN 108979900A
- Authority
- CN
- China
- Prior art keywords
- pendular ring
- collection
- body portion
- thrust chamber
- collection pendular
- 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
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
- F02K9/44—Feeding 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Vessels And Lids Thereof (AREA)
Abstract
A kind of collection pendular ring in liquid rocket engine thrust chamber body portion, including collection pendular ring upper cover (1), collection pendular ring lower cover (2)；The collection pendular ring lower cover (2) is equipped with radial hole (7), aggregate groove (8)；Ellipse arc is in the cross section for integrating pendular ring upper cover (1)；The cross section of collection pendular ring lower cover (2) has the slot of concave shaped；Liquid collecting cavity (6) are formed after collection pendular ring upper cover (1) sum aggregate pendular ring lower cover (2) connection；The liquid collecting cavity (6) is connected to by radial hole (7) with aggregate groove (8).The collection pendular ring is in addition to having the advantages that current sharing is good, the pressure loss is small, intensity and toughness is good, additionally it is possible to solve the problems, such as have steel bushing (3) and thrust chamber body portion welded seal poor in the prior art.
Description
Technical field
The present invention relates to a kind of collection pendular rings in liquid rocket engine thrust chamber body portion, belong to liquid-propellant rocket engine neck
Domain.
Background technique
Collect critical component of the pendular ring as thrust chamber, effect is that the collection and distribution of propellant are realized by it.Start
Machine mainly includes three aspects to the design requirement of thrust chamber collection pendular ring: (1) assignment of traffic of propellant is uniform；(2) propellant
The pressure loss is small；(3) for high-pressure engine, also require collection pendular ring that must have excellent intensity and rigidity.Particularly with according to
By evenly distributing for the liquid rocket engine thrust chamber body portion for carrying out reliable cooling thermal protection for coolant flow, collect pendular ring
Design quality be directly related to engine and can work normally.
In addition, there are one important function for collection pendular ring for thrust chamber body portion, that is, bear in higher combustion chamber
Pressure, to guarantee the reliably working of thrust chamber.Currently, chamber pressure liquid-propellant rocket engine electroforming outer wall body high for high thrust portion, by
It is lower in the intensity of electroformed nickel, intensity is such as promoted using the method for increasing outer wall thickness, blocked up electroformed nickel outer wall will lead to hair
Motivation thrust-mass ratio is greatly reduced and then influences engine performance and to cause the thrust chamber production cycle too long, thus it is general using compared with
Thin one layer of electroformed nickel outer wall outside weldings using high-strength high-temperature alloy or special steel as the scheme of the steel bushing of raw material, such as I
The liquid-propellant rocket engines such as the sustainer SSME of the five core level-one type high thrust motor of length of state and external space shuttle are equal
Using such scheme.Due to the Lavalle moulding surface structure in thrust chamber body portion, for convenience of steel bushing is assembled generally by two and half boxing
Connect composition, but such scheme, it is poor that steel bushing bears external force ability, and in order to reduce manufacturing cost mostly use plate stamping at
Type, plate stamping manufacture can not accurately guarantee the Anawgy accuracy of steel bushing semi-ring and the outer wall-shaped face of electroforming, lead to body portion and propellant
The welded seal of contact area is poor, and the failure of seal failure just once repeatedly occurs in China's h type engine h.
Summary of the invention
The technical problem to be solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of liquid-propellant rocket engine
The collection pendular ring in thrust chamber body portion, in addition to having the advantages that current sharing is good, the pressure loss is small, intensity and toughness is good, additionally it is possible to solve existing
Have in technology with the problem that steel sleeve structure or similar body portion of structured liquids thrust chamber welded seal are poor.
The object of the invention is achieved by the following technical programs:
A kind of collection pendular ring in liquid rocket engine thrust chamber body portion, including collection pendular ring upper cover, collection pendular ring lower cover；The collection
Lid is equipped with radial hole, aggregate groove under pendular ring；
Ellipse arc is in the cross section for integrating pendular ring upper cover；The cross section of the collection pendular ring lower cover has concave shaped
Slot；Liquid collecting cavity is formed after the collection pendular ring upper cover sum aggregate pendular ring lower cover connection；The liquid collecting cavity is connected by radial hole and aggregate groove
It is logical.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the cross section of the aggregate groove are half drops or ladder
Shape.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the collection pendular ring lower cover are equipped with multiple radial holes,
Radial hole is uniformly distributed along the circumferential direction of collection pendular ring lower cover；The radial hole is elliptical aperture, and the thickness of radial hole is not more than 8mm.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the collection pendular ring pass through the first weld seam and the second weld seam
It is tightly connected with external thrust chamber body portion's outer wall.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, further includes leak hunting aperture；Second weld seam is located at collection
It closes between slot and leak hunting aperture.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the collection pendular ring upper cover sum aggregate pendular ring lower cover is using weldering
It connects in succession.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the aggregate groove pass through outside external thrust chamber body portion
The through-hole of wall is connected to the groove inside external thrust chamber body portion.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the collection pendular ring upper cover include the first collection pendular ring upper cover
With the second collection pendular ring upper cover, the first collection pendular ring upper cover and second collects one annulus of formation after pendular ring top cap connects.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, it is described to integrate pendular ring lower cover machine-shaping.
The collection pendular ring in body portion of aforesaid liquid thrust chamber, the branch that the collection pendular ring lower cover passes through collection pendular ring lower cover
Ear is connect with external steel bushing.
The present invention has the following beneficial effects: compared with the prior art
(1) the collection pendular ring in liquid rocket engine thrust chamber body portion of the invention, using double set cavity configurations, i.e. liquid collecting cavity
And collecting tank, enhance stream ability, and self-strength good rigidity；
(2) the collection pendular ring in liquid rocket engine thrust chamber body portion of the invention, it is similar using half water droplet or trapezoidal design
In dromedary hump structure, flow resistance loss is small, conducive to flowing；
(3) thickness of the invention by reducing radial hole, effectively reduces the loss along journey flow resistance；
(4) collection pendular ring lower cover of the invention is added using forging integrated machine, is integrally assembled with electroforming outer wall, fit-up gap control
Precision is high, fitting gap is small, improves welded seal and load ability.
Detailed description of the invention
Fig. 1 is the composition schematic diagram of the collection pendular ring in body portion of fluid present invention thrust chamber；
Fig. 2 is collection pendular ring and the position in thrust chamber body portion in body portion of fluid present invention thrust chamber, connect pass
It is schematic diagram.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to implementation of the invention
Mode is described in further detail.
A kind of collection pendular ring in liquid rocket engine thrust chamber body portion, including collection pendular ring upper cover 1, collection pendular ring lower cover 2；It is described
Collect pendular ring lower cover 2 and be equipped with radial hole 7, aggregate groove 8, leak hunting aperture 11, as shown in Figure 1.Entire collection pendular ring is all made of GH4169 material
Material is made.
Ellipse arc is in the cross section for integrating pendular ring upper cover 1；The cross section of the collection pendular ring lower cover 2 has concave shaped
U-type groove.The collection pendular ring upper cover 1 includes the first collection pendular ring upper cover and the second collection pendular ring upper cover, the first collection pendular ring upper cover and second
Collection pendular ring top cap forms an annulus after connecing.It is described to integrate 2 machine-shaping of pendular ring lower cover.1 He of collection pendular ring upper cover
Collect after pendular ring lower cover 2 is welded to connect and forms liquid collecting cavity 6.
The collection pendular ring lower cover 2 is equipped with multiple radial holes 7, and radial hole 7 is uniformly distributed along the circumferential direction of collection pendular ring lower cover 2,
As shown in Figure 1；The radial hole 7 is elliptical aperture, and the thickness of radial hole 7 is not more than 8mm.The liquid collecting cavity 6 by radial hole 7 with
Aggregate groove 8 is connected to.The cross section of the aggregate groove 8 is half drops or trapezoidal, as depicted in figs. 1 and 2.
The collection pendular ring is tightly connected by the first weld seam 9 and the second weld seam 10 with external thrust chamber body portion outer wall 4.Institute
The second weld seam 10 is stated between aggregate groove 8 and leak hunting aperture 11.The aggregate groove 8 passes through external thrust chamber body portion outer wall 4
Through-hole is connected to inside external thrust chamber body portion 5 groove.It is described collection pendular ring lower cover 2 by collection pendular ring lower cover 2 trunnion with
External steel bushing 3 connects.
Embodiment:
A kind of collection pendular ring in liquid rocket engine thrust chamber body portion forms a small collection by dromedary hump shape collecting tank 8
The optimization design of chamber and radial hole 7 is closed, stream ability is good, flow resistance loss is small；It specifically includes under collection pendular ring upper cover 1, collection pendular ring
Lid 2；Collect pendular ring lower cover 2 and is equipped with radial hole 7, aggregate groove 8, leak hunting aperture 11.Entire collection pendular ring is all made of GH4169 material and is made,
Wherein collection pendular ring lower cover 2 is added using forging integrated machine, and collection pendular ring upper cover 1, collection pendular ring lower cover 2 can be conducive to parallel production
Shorten the process-cycle.
The cross section for collecting pendular ring upper cover 1 is semicircle；The cross section for collecting pendular ring lower cover 2 has the U-type groove of concave shaped.Liquid collecting
Ring upper cover 1 includes the first collection pendular ring upper cover and the second collection pendular ring upper cover, and the first collection pendular ring upper cover and the second collection pendular ring top cap connect
An annulus is formed afterwards.Collection pendular ring lower cover 2 is the integrated design, is integrally machined molding.Collect 1 sum aggregate pendular ring lower cover 2 of pendular ring upper cover
Liquid collecting cavity 6 is formed after welded connecting.
Collect pendular ring lower cover 2 and be equipped with 100 radial holes 7, radial hole 7 is uniformly distributed along the circumferential direction of collection pendular ring lower cover 2, is such as schemed
Shown in 1；Radial hole 7 is elliptical aperture, radial hole 7 with a thickness of 6mm in the present embodiment.Liquid collecting cavity 6 passes through radial hole 7 and aggregate groove
8 connections.The cross section of aggregate groove 8 is half drops, as depicted in figs. 1 and 2.
Collect pendular ring and is tightly connected by the first weld seam 9 and the second weld seam 10 with external thrust chamber body portion outer wall 4, the first weldering
Seam 9 and the second weld seam 10 are electron beam weld.Second weld seam 10 is between aggregate groove 8 and leak hunting aperture 11.If the first weldering
The case where collection pendular ring is sealed with external thrust chamber body portion outer wall 4 is not implemented in seam 9, then, can when carrying out collection pendular ring kerosine test
It observes visually in Fig. 1 and leaks kerosene at the first weld seam 9 of left side, if collection pendular ring and external thrust is not implemented in the second weld seam 10
The case where chamber body portion outer wall 4 seals is visually observed in Fig. 1 in leak hunting aperture 11 then when carrying out collection pendular ring kerosine test
Existing kerosene.
Aggregate groove 8 is connected by inside the through-hole of external thrust chamber body portion outer wall 4 and external thrust chamber body portion 5 groove
It is logical.Collection pendular ring lower cover 2 is connect by the trunnion of collection pendular ring lower cover 2 with external steel bushing 3.
The installation process of the present embodiment are as follows:
(1) collection pendular ring lower cover 2 and thrust chamber body portion outer wall 4 is welded together by electron beam weld at two, is then led to
The leak hunting aperture 11 for crossing on collection pendular ring lower cover 2 checks weld seam leakproofness by kerosine test；
(2) collection pendular ring lower cover 2 is linked together with steel bushing 3 by welding；
(3) finally its function will be realized on the collection welding collection pendular ring lower cover 2 of pendular ring upper cover 1.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, it is characterised in that: including collecting pendular ring upper cover (1), liquid collecting
Ring lower cover (2)；The collection pendular ring lower cover (2) is equipped with radial hole (7), aggregate groove (8)；
Ellipse arc is in the cross section for integrating pendular ring upper cover (1)；The cross section of collection pendular ring lower cover (2) has concave shaped
Slot；Liquid collecting cavity (6) are formed after collection pendular ring upper cover (1) sum aggregate pendular ring lower cover (2) connection；The liquid collecting cavity (6) passes through radial direction
Hole (7) is connected to aggregate groove (8).
2. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion according to claim 1, it is characterised in that: described
The cross section of aggregate groove (8) is half drops or trapezoidal.
3. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion according to claim 1, it is characterised in that: described
Collect pendular ring lower cover (2) and be equipped with multiple radial holes (7), radial hole (7) is uniformly distributed along the circumferential direction of collection pendular ring lower cover (2)；It is described
Radial hole (7) is elliptical aperture, and the thickness of radial hole (7) is not more than 8mm.
4. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion according to claim 1, it is characterised in that: described
Collect pendular ring to be tightly connected by the first weld seam (9) and the second weld seam (10) and external thrust chamber body portion outer wall (4).
5. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion according to claim 1, it is characterised in that: also wrap
Include leak hunting aperture (11)；Second weld seam (10) is located between aggregate groove (8) and leak hunting aperture (11).
6. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, feature described according to claim 1~one of 5 exist
In: collection pendular ring upper cover (1) the sum aggregate pendular ring lower cover (2) is using welded connecting.
7. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, feature described according to claim 1~one of 5 exist
In: the aggregate groove (8) passes through (5) inside the through-hole of external thrust chamber body portion outer wall (4) and external thrust chamber body portion
Groove connection.
8. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, feature described according to claim 1~one of 5 exist
In: the collection pendular ring upper cover (1) includes the first collection pendular ring upper cover and the second collection pendular ring upper cover, and the first collection pendular ring upper cover and second collects
An annulus is formed after the connection of pendular ring upper cover.
9. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, feature described according to claim 1~one of 5 exist
In: it is described to integrate pendular ring lower cover (2) machine-shaping.
10. a kind of collection pendular ring in liquid rocket engine thrust chamber body portion, feature described according to claim 1~one of 5
Be: collection pendular ring lower cover (2) is connect by the trunnion of collection pendular ring lower cover (2) with external steel bushing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810995251.6A CN108979900A (en) | 2018-08-29 | 2018-08-29 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810995251.6A CN108979900A (en) | 2018-08-29 | 2018-08-29 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108979900A true CN108979900A (en) | 2018-12-11 |
Family
ID=64547429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810995251.6A Pending CN108979900A (en) | 2018-08-29 | 2018-08-29 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108979900A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109759789A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | The thrust chamber pressure resistance interlayer manufacturing method of liquid-propellant rocket engine |
| CN109779790A (en) * | 2019-03-11 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of thrust chamber of liquid-propellant rocket engine |
| CN113431708A (en) * | 2021-05-31 | 2021-09-24 | 西安航天动力研究所 | Turbine shell with cooling structure and machining method |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3729793A (en) * | 1968-04-18 | 1973-05-01 | Bolkow Gmbh | Method of constructing a fluid cooled combustion chamber |
| JPS51133613A (en) * | 1975-05-02 | 1976-11-19 | Messerschmitt Boelkow Blohm | Cooling medium gathering ring |
| RU2391544C1 (en) * | 2008-12-17 | 2010-06-10 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Liquid-propellant engine chamber |
| RU2465483C1 (en) * | 2011-03-31 | 2012-10-27 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ им. М.В. Хруничева") | Manufacturing method of nozzle of combustion chamber of liquid-propellant engine (lpe) |
| CN203264476U (en) * | 2013-03-15 | 2013-11-06 | 北京航天动力研究所 | High-speed high-flow filter unit |
| KR20130141814A (en) * | 2012-06-18 | 2013-12-27 | 한국항공우주연구원 | Apparatus for strength and leakage test of regeneratively-cooled combustion chamber |
| RU145545U1 (en) * | 2014-05-19 | 2014-09-20 | Оао "Кузнецов" | LIQUID ROCKET ENGINE CAMERA NOZZLE |
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN106438109A (en) * | 2016-10-31 | 2017-02-22 | 北京航天动力研究所 | Liquid-propellant rocket engine thrust chamber interlayer structure with throat reinforcing bushing |
| CN107084073A (en) * | 2017-06-15 | 2017-08-22 | 葛明龙 | Manned moon landing steps on Mars rocket ultra-large type liquid oxygen thrust chamber |
| CN208885408U (en) * | 2018-08-29 | 2019-05-21 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
-
2018
- 2018-08-29 CN CN201810995251.6A patent/CN108979900A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3729793A (en) * | 1968-04-18 | 1973-05-01 | Bolkow Gmbh | Method of constructing a fluid cooled combustion chamber |
| JPS51133613A (en) * | 1975-05-02 | 1976-11-19 | Messerschmitt Boelkow Blohm | Cooling medium gathering ring |
| RU2391544C1 (en) * | 2008-12-17 | 2010-06-10 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Liquid-propellant engine chamber |
| RU2465483C1 (en) * | 2011-03-31 | 2012-10-27 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ им. М.В. Хруничева") | Manufacturing method of nozzle of combustion chamber of liquid-propellant engine (lpe) |
| KR20130141814A (en) * | 2012-06-18 | 2013-12-27 | 한국항공우주연구원 | Apparatus for strength and leakage test of regeneratively-cooled combustion chamber |
| CN203264476U (en) * | 2013-03-15 | 2013-11-06 | 北京航天动力研究所 | High-speed high-flow filter unit |
| CN104948347A (en) * | 2014-03-31 | 2015-09-30 | 北京航天动力研究所 | Thrust chamber collector with flow uniformizing function |
| RU145545U1 (en) * | 2014-05-19 | 2014-09-20 | Оао "Кузнецов" | LIQUID ROCKET ENGINE CAMERA NOZZLE |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN106438109A (en) * | 2016-10-31 | 2017-02-22 | 北京航天动力研究所 | Liquid-propellant rocket engine thrust chamber interlayer structure with throat reinforcing bushing |
| CN107084073A (en) * | 2017-06-15 | 2017-08-22 | 葛明龙 | Manned moon landing steps on Mars rocket ultra-large type liquid oxygen thrust chamber |
| CN208885408U (en) * | 2018-08-29 | 2019-05-21 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
Non-Patent Citations (1)
| Title |
|---|
| 韩非: "冷却剂不同流动方式对膨胀循环推力室再生冷却换热的影响", 航空动力学报, vol. 21, no. 6, pages 1116 - 1122 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109759789A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | The thrust chamber pressure resistance interlayer manufacturing method of liquid-propellant rocket engine |
| CN109759789B (en) * | 2019-01-24 | 2020-07-03 | 蓝箭航天空间科技股份有限公司 | Method for manufacturing pressure-resistant interlayer of thrust chamber of liquid rocket engine |
| CN109779790A (en) * | 2019-03-11 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of thrust chamber of liquid-propellant rocket engine |
| CN113431708A (en) * | 2021-05-31 | 2021-09-24 | 西安航天动力研究所 | Turbine shell with cooling structure and machining method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108979900A (en) | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion | |
| CN208885408U (en) | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion | |
| CN204878738U (en) | Structure of obturaging | |
| CN213245359U (en) | Combined valve with lengthened neck for pipeline | |
| CN106787375B (en) | Oil seal structure is taken turns to turbo generator | |
| CN202349438U (en) | Novel flange structure of automotive exhaust pipe | |
| CN214196498U (en) | Novel multilayer metal cylinder gasket with structure changing shape of whole water channel sealing rib | |
| CN213743705U (en) | Cylinder head and engine with same | |
| CN209687565U (en) | A kind of automobile direct fuel-injection engine valve retainer | |
| CN210576045U (en) | Sealing structure for high-temperature battery | |
| CN214769556U (en) | Brazing welding cylinder sleeve | |
| CN203626998U (en) | Novel metal cylinder head gasket for increasing fuel gas sealing surface pressure for double cylinders arranged in V-shaped mode | |
| CN206190601U (en) | Novel water pump housing | |
| CN208347951U (en) | A kind of laser welding balanced surface air cylinder pad | |
| CN206035560U (en) | Modified gasengine cylinder head discharge valve seat | |
| CN220539736U (en) | Corrosion-resistant wet cylinder sleeve | |
| CN212203134U (en) | Long-shaft low-temperature stop valve | |
| CN204003139U (en) | Piston for ethanol fuel engine | |
| CN217107239U (en) | Cylinder head and engine | |
| CN112628013B (en) | Mostly plastic internal combustion engine cylinder head | |
| CN218193530U (en) | Tool for fixing transient liquid phase transition connection of fuel nozzle pipe | |
| CN217926093U (en) | Engine cylinder cover structure | |
| CN211038857U (en) | Engine cylinder gasket with good sealing effect | |
| CN212985384U (en) | Cylinder cover and engine with same | |
| CN213175858U (en) | Piston with high pressure at end part |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |