CN209687780U - A kind of dynamic sealing device reused suitable for low-temperature and high-speed - Google Patents
A kind of dynamic sealing device reused suitable for low-temperature and high-speed Download PDFInfo
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- CN209687780U CN209687780U CN201920263724.3U CN201920263724U CN209687780U CN 209687780 U CN209687780 U CN 209687780U CN 201920263724 U CN201920263724 U CN 201920263724U CN 209687780 U CN209687780 U CN 209687780U
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Abstract
The utility model relates to a kind of dynamic sealing devices reused suitable for low-temperature and high-speed, applied on liquid-propellant rocket engine turbine pump, the liquid-propellant rocket engine turbine pump includes axis (18) and the bearing (9) being sheathed on axis (18), the dynamic sealing device includes main seal structure, and the main seal structure includes rotating ring (1), static components (2), bellows (3), rear ring (4), seal casinghousing (5) and axle sleeve (14).The dynamic sealing device of the utility model includes main seal structure, so that cryogenic media is easily accessible at rotating ring and static components binding face, to avoid sealing surface from dry friction occur, reduce sealing wear, sealing life is increased, thus the requirement for the bad working environments lower long-lives and reuse such as the high revolving speed, high pressure, the radial beat eccentricity that meet turbine pump be big.
Description
Technical field
The utility model relates to technical field of sealing technology, and in particular to a kind of dynamic sealing reused suitable for low-temperature and high-speed
Device.
Background technique
Currently, entering the trend of business space flight great development in world wide.High reliability, low cost, reuse, nothing
The rocket engine of pollution becomes the developing direction of liquid-propellant rocket engine.Liquid oxygen methane starts that cooling performance is good, efficiency of combustion
Height is not easy coking, specific impulse higher than oxygen kerosene engine, and wherein unit mass methane fuel cost only has the 1/3 of kerosene, less than
The 1/30 of liquid hydrogen.
Important component of the liquid oxygen pump as liquid oxygen methane engine, effect are required when being conveying engine operation
Low-temperature liquid oxygen, liquid oxygen pump and methane pump close to.Usually between the liquid oxygen pump in liquid-propellant rocket engine turbine pump and methane pump
A set of sealing device is set, two media is avoided to meet.Currently, there are mainly two types of the domestic and international sealings for low temperature environment:
1) non-contacting seal, principle is to realize to depressurize and seal step by step using labyrinth local gap, such as floating ring, fan
Palace sealing etc.；
2) common contact-type mechanical seal, principle are that friction pair is made to fit closely realization sealing using elastic element, should
Kind of sealing structure is more mature, it can be achieved that static sealing, and dielectric leakage amount is small when dynamic duty.
But high revolving speed, high pressure, the radial beat eccentricity that above two sealing means are not able to satisfy turbine pump big etc. are disliked
The requirement of bad operating condition lower long-life and reuse.
Utility model content
To solve technological deficiency and deficiency of the existing technology, the utility model provides a kind of suitable for low-temperature and high-speed
The dynamic sealing device of reuse.
Specifically, a kind of dynamic sealing dress reused suitable for low-temperature and high-speed that the utility model one embodiment proposes
It sets, is applied on liquid-propellant rocket engine turbine pump, the liquid-propellant rocket engine turbine pump includes axis and is sheathed on axis
Bearing, the dynamic sealing device include main seal structure, the main seal structure include rotating ring, static components, bellows, after
Ring, seal casinghousing and axle sleeve, wherein
The moving ring sleeve is set on the axis, and the first end face of the rotating ring is bonded with the end face of bearing, the rotating ring
Second end face is bonded with the first end face of the static components, and the first of the second end face of the static components and the bellows
End connection, the second end of the bellows is connect with the rear ring, and the static components are sheathed on the axle sleeve, and described
Axle sleeve is sheathed on the axis, and the seal casinghousing is sheathed on the static components, the bellows and the rear ring along axial direction
On, and the seal casinghousing is fixedly connected with the static components, the bellows and the rear ring.
In one embodiment of the utility model, the main seal structure further includes the first sealing ring, and described first is close
Seal is set between the first end face of the rotating ring and the axle sleeve, and the first end of first sealing ring and the rotating ring
The end face that face is in contact is provided with cone angle boss.
In one embodiment of the utility model, the main seal structure further includes the second sealing ring, and described second is close
Seal is set between the seal casinghousing and the shell of the liquid-propellant rocket engine turbine pump.
In one embodiment of the utility model, the main seal structure further includes the first screw, the seal casinghousing
It is connect by first screw with the shell of the liquid-propellant rocket engine turbine pump.
In one embodiment of the utility model, the second end face of the rotating ring is provided with oblique angle.
It further include auxiliary sealing structure in one embodiment of the utility model, the auxiliary sealing structure includes point
Body floating ring, compressed spring, several tension springs, the fission floating ring includes the first floating ring and the second floating ring, wherein
The fission floating ring is sheathed on the axle sleeve, and the compressed spring is set to first floating ring and described
Between second floating ring, several tension springs are sheathed on first floating ring and second floating ring.
In one embodiment of the utility model, the fission floating ring includes several segmentation floating rings, each described
The first end face of segmentation floating ring has the groove structure faced directly, and the second end face of the segmentation floating ring has the recessed of arc surface
Slot structure, wherein the first end face of the two neighboring segmentation floating ring fits each other with second end face.
In one embodiment of the utility model, the auxiliary sealing structure further includes third sealing ring and baffle,
In,
The first end of the baffle is bonded with the seperated floating ring, and the second end of the baffle and the liquid rocket are sent out
The shell of motivation turbine pump connects, and the third sealing ring is set to the shell of the liquid-propellant rocket engine turbine pump and described
Between baffle.
In one embodiment of the utility model, the auxiliary sealing structure further includes anti-rotation pin, the baffle
First end is connected with the seperated floating ring by anti-rotation pin.
In one embodiment of the utility model, the auxiliary sealing structure further includes the second screw, the baffle
Second end is connect with the shell of the liquid-propellant rocket engine turbine pump by second screw.
Compared with prior art, the utility model has the beneficial effects that
The dynamic sealing device of the utility model includes main seal structure, so that cryogenic media is easily accessible rotating ring and stationary ring group
At part binding face, so that sealing surface be avoided dry friction occur, reduce sealing wear, increase sealing life, to meet whirlpool
The requirement for the bad working environments lower long-lives and reuse such as high revolving speed, high pressure, the radial beat eccentricity of wheel pump be big.
Detailed description of the invention
Fig. 1 is a kind of knot of dynamic sealing device reused suitable for low-temperature and high-speed provided by the embodiment of the utility model
Structure schematic diagram；
Fig. 2 is a kind of structural schematic diagram for the rotating ring for being provided with oblique angle provided by the embodiment of the utility model；
Fig. 3 is a kind of structural representation for the first sealing ring for being provided with cone angle boss provided by the embodiment of the utility model
Figure；
Fig. 4 is a kind of structural schematic diagram of seperated floating ring lap-joint provided by the embodiment of the utility model；
Fig. 5 is the A of Fig. 4 provided by the embodiment of the utility model to schematic diagram.
Description of symbols:
1 rotating ring；2 static components；3 bellowss；Ring after 4；5 seal casinghousings；6 first screws；7 first sealing rings；8 second is close
Seal；9 bearings；10 seperated floating rings；11 compressed springs；12 tension springs；13 third sealing rings；14 axle sleeves；15 anti-rotation pins；16 gears
Plate；17 second screws；18 axis；21 graphite annulus；22 stationary rings；71 cone angle boss；101 segmentation floating rings.
Specific embodiment
Further detailed description, but the embodiment party of the utility model are done to the utility model combined with specific embodiments below
Formula is without being limited thereto.
It will be appreciated that it can be directly connected to when element arrives another element referred to as " connection " or " in conjunction with "
Or it is bonded directly to another element, or may exist intermediary element.On the contrary, when element be referred to as " being directly connected to " or
When " binding directly " arrives another element, intermediary element is not present.Identical appended drawing reference always shows identical element.
For ease of description, spatially relative term can be used herein, as " ... under ", " ... lower section ", " below
", " in ... top ", " above " etc., for describing such as elements or features and another element shown in the figure or
The relationship of feature.It will be appreciated that spatially relative term is intended to exist comprising the device other than the orientation being described in the accompanying drawings
Using or operation in different direction.For example, being described as " " other elements or feature if the device in attached drawing is reversed
The element of " below " or " under " will then be positioned as " " other elements or feature " top ".Thus, exemplary term " ...
Lower section " may include " in ... top " and " in ... lower section " two kinds of orientation.Described device can by addition position (be rotated by 90 ° or
Other orientation), and corresponding explanation is made to the opposite description language in space used herein.
The relational terms of Wen Zhong, such as " first " and " second " or the like be used merely to by an entity or operation with it is another
One entity or operation distinguish, and without necessarily requiring or implying between these entities or operation, there are any this reality
Relationship or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to the packet of nonexcludability
Contain, so that the process, method, article or equipment for including a series of elements not only includes those elements, but also including
Other elements that are not explicitly listed, or further include for elements inherent to such a process, method, article, or device.
Embodiment one
Referring to Figure 1, Fig. 1 is provided by the embodiment of the utility model a kind of close suitable for moving for low-temperature and high-speed reuse
The structural schematic diagram of seal apparatus.A kind of dynamic sealing device reused suitable for low-temperature and high-speed is present embodiments provided, this is dynamic
Sealing device low-temperature and high-speed is reused dynamic sealing and is mainly used between liquid-propellant rocket engine liquid oxygen pump and methane pump, is used for
Liquid oxygen and methane two media is isolated, belongs to liquid-propellant rocket engine turbine Sealing used for pump, certain dynamic sealing device
On the turbine pump that can be adapted for other liquid-propellant rocket engines, the utility model can also be used for the fields such as aviation, weapons
In rotating device.Specific requirement is not done herein, and the turbine pump of liquid-propellant rocket engine mainly includes axis 18 and is sheathed on axis 18
Bearing 9, which includes main seal structure, the main seal structure include rotating ring 1, static components 2, bellows 3, after
Ring 4, seal casinghousing 5 and axle sleeve 14, wherein
Rotating ring 1 is sheathed on axis 18, and the first end face of rotating ring 1 is bonded with the end face of bearing 9, realizes rotating ring 1 and bearing 9
Positioning, so that rotating ring 1 is fixed with bearing 9 by frictional force, the second end face of rotating ring 1 is bonded with the first end face of static components 2,
The second end face (i.e. sealing surface) of rotating ring 1 and static components 2 fit closely under the elastic force effect of bellows 3, guarantee rotating ring 1 with
The second end face of sealing performance at the binding face of static components 2, static components 2 is connect with the first end of bellows 3, bellows
3 second end is connect with rear ring 4, and static components 2 are sheathed on the axle sleeve 14, and axle sleeve 14 is sheathed on axis 18, axle sleeve
14 belong to clearance fit with axis 18, and seal casinghousing 5 is sheathed on static components 2, bellows 3 and rear ring 4 along axial direction, and capsul
Body 5 is fixedly connected with static components 2, bellows 3 and rear ring 4.
The sealing device of the utility model includes main seal structure, so that cryogenic media is easily accessible rotating ring and static components
At binding face, so that sealing surface be avoided dry friction occur, reduce sealing wear, increase sealing life, to meet turbine
The requirement for the bad working environments lower long-lives and reuse such as high revolving speed, high pressure, the radial beat eccentricity of pump be big.
Further, 14 outer round surface of axle sleeve sprays chromium oxide, and range of coat thicknesses is 0.05~0.15mm.
Further, static components 2 include graphite annulus and stationary ring, and wherein graphite annulus is located in the groove of stationary ring, rotating ring 1
Second end face fits with graphite annulus, i.e. the first end face of the second end face with static components 2 of rotating ring 1 is bonded, stationary ring and ripple
The first end of pipe 3 connects, i.e., the second end face of static components 2 is connect with the first end of bellows 3.
Further, bellows 3 is welding bellows, and stationary ring, rear ring 4 with static components 2 are to be welded to connect.
Further, Fig. 2 is referred to, the second end face of rotating ring 1 is provided with oblique angle, and the oblique angle is in the outer diameter of rotating ring 1
End, the angle at the oblique angle are 15~30o.Oblique angle is set close to the side of 1 outer diameter of rotating ring by the second end face in rotating ring 1, is made
It obtains cryogenic media to be easily accessible at rotating ring 1 and 2 binding face of static components, so that rotating ring 1 and the binding face of static components 2 be avoided to go out
Existing dry friction, reduces sealing wear, increases the sealing life；The medium introduced by the oblique angle of rotating ring 1, guarantees rotating ring 1
The liquid film gone out with the binding face of static components 2 does not vaporize, so that mechanical seal meets the requirement of engine reuse.
The oblique angle being arranged at 1 outer diameter of rotating ring enters rotating ring 1 and stationary ring group to form medium cooling duct convenient for medium
At the binding face of part 2, rubbing surface is effectively cooled down.
Further, please referring also to Fig. 1 and Fig. 3, main seal structure further include the first sealing ring 7, and the first sealing ring 7 is set
It is placed between the first end face of rotating ring 1 and axle sleeve 14, and the end face that the first sealing ring 7 is in contact with the first end face of rotating ring 1 is set
It is equipped with cone angle boss 71.It is provided with cone angle boss 71 on first sealing ring 7, is fitted close with 1 inner hole of rotating ring, guarantees rotating ring 1
Radial and axial static seal.
Further, referring to Figure 1, main seal structure further includes the second sealing ring 8, and the second sealing ring 8 is set to sealing
Between shell 5 and the shell of liquid-propellant rocket engine turbine pump.The shell of seal casinghousing 5 and liquid-propellant rocket engine turbine pump it
Between sealing by the second sealing ring 8 realize, belong to static seal.
Further, referring to Figure 1, main seal structure further includes the first screw 6, seal casinghousing 5 by the first screw 6 with
The shell of liquid-propellant rocket engine turbine pump connects.
Referring to Figure 1, the dynamic sealing device of the utility model embodiment includes auxiliary sealing structure, auxiliary sealing structure packet
Include two seperated floating rings 10, compressed spring 11, several tension springs 12, wherein
Seperated floating ring 10 is sheathed on axle sleeve 14, and compressed spring 11 is set between two seperated floating rings 10, is being pressed
A seperated floating ring 10 and the shell of liquid-propellant rocket engine turbine pump can be made closely to paste under the active force of contracting spring 11
It closes, another seperated floating ring 10 and the end face of baffle 16 fit closely, and are arranged at least on each seperated floating ring 10
One tension spring 12, tension spring 12, in axle sleeve 14, cooperate for banding the first floating ring 101 and the second floating ring 102 with axle sleeve 14.
Seperated floating ring 10 forms radial seal with axle sleeve 14, as auxiliary seal, and low pressure process gas is blown at the D of Fig. 1, can
Guarantee that working medium does not leak at B.
Further, Fig. 4 and Fig. 5 are referred to, seperated floating ring 10 includes several segmentation floating rings 101, and each segmentation is floating
The first end face of rotating ring 101 has the groove structure faced directly, which is set in first end face and segmentation floating ring 101
The intersection of diameter, and each face in the groove structure be face directly, for example, the groove structure include the first face and the second face,
First face and the second face are to face directly, and have certain angle between first face and second face, and for example 90 degree；Segmentation
The second end face of floating ring 101 has the groove structure of arc surface, which is set to second end face and segmentation floating ring
The intersection of 101 internal diameters, and each face in the groove structure is arc surface, which is the face of outwardly convex, for example,
The groove structure includes the first face and the second face, and first face and the second face are arc surface, wherein each fission floating ring 10
In it is two neighboring segmentation floating ring 101 first end face fit each other with second end face, it is this by 101 structure of segmentation floating ring
The seperated floating ring 10 of composition makes the binding face of two neighboring segmentation floating ring 101 be in contact always during the work time
State adapts to working environment axial, that radial beat eccentricity is big so as to guarantee the air-tightness at binding face.Seperated floating ring
10 form axial seal with axle sleeve 14, and split type floating ring 10 can compensate automatically in its bore wear, seperated floating ring 10
It is circular shape at the lap hermetically of two segmentation floating rings 101, which acts together when rotor radial is beated, and has circle
The segmentation floating ring 101 of cambered surface is contacted with the face that there is the segmentation floating ring 101 faced directly to be in contact for line, so as to guarantee to paste
The air-tightness at conjunction face place.
The faying surface of the two neighboring segmentation floating ring 101 of seperated floating ring 10 is arc surface cooperation, is floated convenient for seperated
Ring 10 is circumferential to compensate under big circular runout.
The present embodiment using split type floating ring 10 be used as auxiliary seal, auxiliary purging system's pressure be 0.15~
0.25MPa belongs to low bleed pressure, and it reduce the pressure that engine carries gas cylinder.
Further, auxiliary sealing structure further includes third sealing ring 13 and baffle 16, wherein the first end of baffle 16 with
Seperated floating ring 10 is bonded, and the second end of baffle 16 is connect with the shell of liquid-propellant rocket engine turbine pump, third sealing ring 13
It is set between the shell of liquid-propellant rocket engine turbine pump and baffle 16, third sealing ring 13 is for making liquid-propellant rocket engine
Sealing function is generated between the shell and baffle 16 of turbine pump.
Further, auxiliary sealing structure further includes anti-rotation pin 15, and the first end of baffle 16 is logical with seperated floating ring 10
The connection of anti-rotation pin 15 is crossed, anti-rotation pin 15 is used to prevent the rotation of seperated floating ring 10.
Further, auxiliary sealing structure further includes the second screw 17, the second end and liquid-propellant rocket engine of baffle 16
The shell of turbine pump is connected by the second screw 17.
The dynamic sealing device that low-temperature and high-speed provided by the utility model is reused, meets following technical conditions: medium pressure
Power :≤1.5MPa；Sealing medium: liquid oxygen, methane, liquid hydrogen etc.；Medium temperature≤- 196 DEG C: revolving speed≤50000r/min.
The dynamic sealing device of the utility model embodiment solves existing low-temperature and high-speed sealing and is not able to satisfy turbine pump height turn
The requirement for the bad working environments lower long-lives and reuse such as speed, high pressure, ultralow temperature, radial beat eccentricity be big.
The binding face of the lap-joint of the two neighboring segmentation floating ring of the seperated floating ring of the utility model embodiment uses
Arc surface, it is mobile convenient for the circumferential direction of seperated floating ring, meet the big adverse circumstances of turbine pump radial beat eccentricity.
Finally, it should be noted that above embodiments are only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that:
It is still possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is carried out etc.
With replacement；And these are modified or replaceed, various embodiments of the utility model technology that it does not separate the essence of the corresponding technical solution
The spirit and scope of scheme.
Claims (10)
1. a kind of dynamic sealing device reused suitable for low-temperature and high-speed, is applied on liquid-propellant rocket engine turbine pump, institute
Stating liquid-propellant rocket engine turbine pump includes axis (18) and the bearing (9) being sheathed on axis (18), which is characterized in that it is described move it is close
Seal apparatus includes main seal structure, the main seal structure include rotating ring (1), static components (2), bellows (3), rear ring (4),
Seal casinghousing (5) and axle sleeve (14), wherein
The rotating ring (1) is sheathed on the axis (18), and the first end face of the rotating ring (1) is bonded with the end face of bearing (9), institute
The second end face for stating rotating ring (1) is bonded with the first end face of the static components (2), the second end face of the static components (2)
It is connect with the first end of the bellows (3), the second end of the bellows (3) is connect with the rear ring (4), and the stationary ring
Component (2) is sheathed on the axle sleeve (14), and the axle sleeve (14) is sheathed on the axis (18), the seal casinghousing (5)
Along axial direction be sheathed on the static components (2), the bellows (3) and it is described after on ring (4), and the seal casinghousing (5) with
The static components (2), the bellows (3) are fixedly connected with the rear ring (4).
2. dynamic sealing device according to claim 1, which is characterized in that the main seal structure further includes the first sealing ring
(7), first sealing ring (7) is set between the first end face of the rotating ring (1) and the axle sleeve (14), and described first
The end face that sealing ring (7) is in contact with the first end face of the rotating ring (1) is provided with cone angle boss (71).
3. dynamic sealing device according to claim 1, which is characterized in that the main seal structure further includes the second sealing ring
(8), second sealing ring (8) be set to the seal casinghousing (5) and the liquid-propellant rocket engine turbine pump shell it
Between.
4. dynamic sealing device according to claim 1, which is characterized in that the main seal structure further includes the first screw
(6), the seal casinghousing (5) is connect by first screw (6) with the shell of the liquid-propellant rocket engine turbine pump.
5. dynamic sealing device according to claim 1, which is characterized in that the second end face of the rotating ring (1) is provided with tiltedly
Angle.
6. dynamic sealing device according to claim 1, which is characterized in that further include auxiliary sealing structure, the auxiliary is close
Seal structure includes two seperated floating rings (10), compressed springs (11), several tension springs (12), wherein
The fission floating ring (10) is sheathed on the axle sleeve (14), and the compressed spring (11) is set to two fissions
Between floating ring (10), at least one described tension spring (12) is arranged on each seperated floating ring (10).
7. dynamic sealing device according to claim 6, which is characterized in that the fission floating ring (10) includes several segmentations
The first end face (102) of floating ring (101), each segmentation floating ring (101) has the groove structure faced directly, the segmentation
The second end face (103) of floating ring (101) has the groove structure of arc surface, wherein the two neighboring segmentation floating ring
(101) first end face fits each other with second end face.
8. dynamic sealing device according to claim 6, which is characterized in that the auxiliary sealing structure further includes third sealing
Enclose (13) and baffle (16), wherein
The first end of the baffle (16) is bonded with the seperated floating ring (10), the second end of the baffle (16) and the liquid
The shell of body rocket engine turbopump connects, and the third sealing ring (13) is set to the liquid-propellant rocket engine turbine pump
Shell and the baffle (16) between.
9. dynamic sealing device according to claim 8, which is characterized in that the auxiliary sealing structure further includes anti-rotation pin
(15), the first end of the baffle (16) is connected with the seperated floating ring (10) by anti-rotation pin (15).
10. dynamic sealing device according to claim 8, which is characterized in that the auxiliary sealing structure further includes the second spiral shell
It follows closely (17), the second end of the baffle (16) and the shell of the liquid-propellant rocket engine turbine pump pass through second screw
(17) it connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920263724.3U CN209687780U (en) | 2019-03-01 | 2019-03-01 | A kind of dynamic sealing device reused suitable for low-temperature and high-speed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920263724.3U CN209687780U (en) | 2019-03-01 | 2019-03-01 | A kind of dynamic sealing device reused suitable for low-temperature and high-speed |
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| Publication Number | Publication Date |
|---|---|
| CN209687780U true CN209687780U (en) | 2019-11-26 |
Family
ID=68603456
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920263724.3U Withdrawn - After Issue CN209687780U (en) | 2019-03-01 | 2019-03-01 | A kind of dynamic sealing device reused suitable for low-temperature and high-speed |
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| Country | Link |
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| CN (1) | CN209687780U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109779947A (en) * | 2019-03-01 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of dynamic sealing device reused suitable for low-temperature and high-speed |
| CN112096652A (en) * | 2020-09-02 | 2020-12-18 | 航天科工火箭技术有限公司 | Liquid disengaging type dynamic sealing device |
-
2019
- 2019-03-01 CN CN201920263724.3U patent/CN209687780U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109779947A (en) * | 2019-03-01 | 2019-05-21 | 北京星际荣耀空间科技有限公司 | A kind of dynamic sealing device reused suitable for low-temperature and high-speed |
| CN109779947B (en) * | 2019-03-01 | 2024-05-24 | 北京星际荣耀空间科技有限公司 | Dynamic sealing device suitable for low-temperature high-speed reuse |
| CN112096652A (en) * | 2020-09-02 | 2020-12-18 | 航天科工火箭技术有限公司 | Liquid disengaging type dynamic sealing device |
| CN112096652B (en) * | 2020-09-02 | 2024-05-03 | 航天科工火箭技术有限公司 | Liquid-release dynamic sealing device |
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| TR01 | Transfer of patent right |
Effective date of registration: 20200102 Address after: 100176 Beijing Daxing District Beijing economic and Technological Development Zone, 9 South of Shing Sheng 1 1 3 story 329 Co-patentee after: Beijing Star glory Technology Co.,Ltd. Patentee after: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. Co-patentee after: Beijing Star smart Manufacturing Technology Co.,Ltd. Address before: 100176 Building No. 9, Dishengnan Street, Daxing Economic and Technological Development Zone, Beijing, 329 Patentee before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Beijing Star glory Space Technology Co.,Ltd. Patentee after: Beijing Star glory Technology Co.,Ltd. Patentee after: Beijing Star smart Manufacturing Technology Co.,Ltd. Address before: 100176 329, 3rd floor, building 1, No.9, Disheng South Street, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. Patentee before: Beijing Star glory Technology Co.,Ltd. Patentee before: Beijing Star smart Manufacturing Technology Co.,Ltd. |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20191126 Effective date of abandoning: 20240524 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20191126 Effective date of abandoning: 20240524 |