CN110030381A - One kind being suitable for high speed and high pressure dynamic sealing device and aircraft - Google Patents
One kind being suitable for high speed and high pressure dynamic sealing device and aircraft Download PDFInfo
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- CN110030381A CN110030381A CN201910185707.7A CN201910185707A CN110030381A CN 110030381 A CN110030381 A CN 110030381A CN 201910185707 A CN201910185707 A CN 201910185707A CN 110030381 A CN110030381 A CN 110030381A
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- sealing device
- dynamic sealing
- high pressure
- fluid
- high speed
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- 238000007789 sealing Methods 0.000 title claims abstract description 131
- 208000002925 dental caries Diseases 0.000 claims abstract description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 40
- 229910002804 graphite Inorganic materials 0.000 claims description 35
- 239000010439 graphite Substances 0.000 claims description 35
- 238000005422 blasting Methods 0.000 claims description 6
- 239000002775 capsule Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 14
- 238000000034 method Methods 0.000 description 10
- 238000005299 abrasion Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 229910052799 carbon Inorganic materials 0.000 description 4
- 210000004907 gland Anatomy 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 239000003380 propellant Substances 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 230000003276 anti-hypertensive effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006837 decompression Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/164—Sealings between relatively-moving surfaces the sealing action depending on movements; pressure difference, temperature or presence of leaking fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/26—Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings
- F16J15/30—Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings with sealing rings made of carbon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/40—Sealings between relatively-moving surfaces by means of fluid
Abstract
The present invention relates to technical field of sealing technology, and in particular to one kind is suitable for high speed and high pressure dynamic sealing device and aircraft.The dynamic sealing device includes seal casinghousing, is spaced two cavitys of sealing to be formed, and the through-hole of two cavitys of connection is offered on seal casinghousing；Shaft can be rotated and at least partly be arranged through through-hole；Fluid-tight wheel, is mounted in shaft, rotates with the rotation of shaft, and can form fluid-tight between seal casinghousing in rotation；And heat-insulating and sealing ring, it is arranged between shaft and seal casinghousing, and close on the setting of fluid-tight wheel, and with fluid-tight wheel shape at combination sealing, and then the shaft of high-speed rotation makes fluid-tight wheel form fluid-tight between seal casinghousing and shaft, a retardation can be played to high pressure, heat-insulating and sealing ring can play an interval action to high temperature, it greatly reduces influence of the high temperature to entire dynamic sealing device, and then improves the reliability and service life of dynamic sealing device under the bad working environments such as high revolving speed, high pressure, temperature gradient be big.
Description
Technical field
The present invention relates to technical field of sealing technology, and in particular to one kind is suitable for high speed and high pressure dynamic sealing device and aircraft.
Background technique
Currently, entering the trend of business space flight great development, high reliability, low cost, reuse, nothing in world wide
Polluting rocket engine becomes the developing direction of liquid-propellant rocket engine.Wherein, the liquid oxygen methane engine in rocket has cold
But performance is good, high combustion efficiency, be not easy coking, specific impulse is higher than oxygen kerosene engine, and unit mass methane fuel cost
Only the 1/3 of kerosene, the 1/30 of liquid hydrogen, wider application is obtained in space industry.
Methane pumps the important component as liquid oxygen methane engine, and effect is required when being conveying engine operation
Cryogenic liquid methane, methane pump are arranged close to turbine chamber.It is usually provided between liquid-propellant rocket engine pump and turbine a set of
Sealing device is generated so that forming sealing between the side medium and turbine chamber of engine pump by turbine chamber fuel combustion
High temperature influences, the temperature difference >=600K at the sealing between side medium and turbine chamber, so that conventional sealing device can not be applicable in.It is right
This is used for there are mainly two types of the sealings under high-voltage high-speed environment both at home and abroad in the prior art:
One is non-contacting seal, principle is to realize to depressurize and seal step by step using labyrinth local gap, is such as floated
Ring, labyrinth seal etc., this kind of sealing structure is simple, but sealing performance is undesirable, and dielectric leakage amount is larger when work, close to improve
Reliability is sealed, also needs additionally to increase high pressure gas bleed system；
Another kind is contacting mechanical seal, and principle is that friction pair is made to fit closely realization sealing using elastic element,
This kind of sealing structure is more mature, it can be achieved that static sealing, and dielectric leakage amount is small when dynamic duty.But such sealing device exists
It starts and shutdown process friction secondary sealing area abrasion loss is larger, after sealing is used for multiple times, sealing performance decline, or even failure, therefore
Such sealing is less able to satisfy the bad working environments lower long-lives, high reliability such as the high revolving speed of turbine pump, hyperpressure, temperature gradient be big
With the requirement of reuse.
Summary of the invention
The main purpose of the present invention is to provide a kind of sealing device and aircraft, to solve or at least mitigate the prior art
Middle sealing device is unable to satisfy long-life, high reliability and repetition under the bad working environments such as high revolving speed, high pressure, temperature gradient be big
The problem of use.
To achieve the above object, being suitable for high speed and high pressure dynamic sealing device the present invention provides one kind includes:
Seal casinghousing is spaced two cavitys of sealing to be formed, and connection two cavity is offered on the seal casinghousing
Through-hole；
Shaft can be rotated and at least partly be arranged through the through-hole；
Fluid-tight wheel is mounted in the shaft, is rotated with the rotation of the shaft, and can rotation when and seal casinghousing
Between form fluid-tight；And
Heat-insulating and sealing ring is arranged between the shaft and the seal casinghousing, and closes on the fluid-tight wheel setting, and with
The fluid-tight wheel shape is at combination sealing.
Further, two cavity includes a high temperature cavity and a high-pressure chamber, and the heat-insulating and sealing ring closes on described
The setting of high temperature cavity, the fluid-tight wheel close on the high-pressure chamber setting.
Further, the heat-insulating and sealing ring includes the graphite annulus being mounted in the shaft.
Further, the quantity of graphite annulus is two.
Further, the dynamic sealing device further includes the compensating part being set in outside the heat-insulating and sealing ring, the compensation
Part has so that the pre-pressing force that heat-insulating and sealing ring inside contracts.
Further, the compensating part is the tension spring being set in outside the heat-insulating and sealing ring.
Further, the dynamic sealing device further includes the gap adjustment being arranged on the side of the heat-insulating and sealing ring
Part.
Further, the sealing blade shape in the fluid-tight wheel is arc-shaped, is radially tilted.
Further, the side of the fluid-tight wheel cooperates with the bearing clearance that is mounted in the shaft, the other side and outer
The round and seal casinghousing clearance fit.
Further, the interstice coverage is between 0.2~0.5mm.
Further, the high speed and high pressure dynamic sealing device that is suitable for further includes gas blasting's structure, the heat-insulating and sealing
There is the channel with gas blasting's fabric connectivity on ring.
Further, the sealing device is used for sealing medium side and turbine chamber, one end of the shaft and the turbine
Chamber connection, and can rotate and rotate with the turbine in the turbine chamber.
The present invention also provides a kind of aircrafts, including are suitable for high speed and high pressure dynamic sealing device, described to be suitable for high speed and high pressure
It is to be suitable for high speed and high pressure dynamic sealing device as described above with dynamic sealing device.
Further, the aircraft is rocket.
Technical solution of the present invention has the advantages that
1. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, in high revolving speed, hyperpressure, temperature
It spends under the bad working environments such as gradient is big, fluid-tight wheel and heat-insulating and sealing ring form combined labyrinth and carbon gland, and the shaft of high-speed rotation makes fluid-tight
Wheel forms fluid-tight between seal casinghousing and shaft, a retardation can be played to high pressure, revolving speed is higher, to high pressure
Retardation is stronger, and then greatly reduces impact of the high pressure to entire dynamic sealing device, and shaft and seal casinghousing it
Between, and the heat-insulating and sealing ring for closing on the setting of fluid-tight wheel can play an interval action to high temperature, greatly reduce high temperature to whole
The influence of a dynamic sealing device, and then dynamic sealing device is improved under the bad working environments such as high revolving speed, high pressure, temperature gradient be big
Reliability and service life.
2. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, dynamic sealing device further includes being arranged
Compensating part outside graphite annulus, compensating part have so that the pre-pressing force that graphite annulus inside contracts so that graphite annulus meet it is close
It is adaptable to system structure deformation and rotor bounce while the temperature interval of envelope front and back, and in split type graphite annulus inner hole
After the abrasion of shaft high-speed rotation, graphite annulus can compensate automatically under tension spring active force, guarantee graphite annulus after a number of uses
Its performance does not reduce, and meets the requirement of engine reuse, so that the better reliability of dynamic sealing device, is suitable for rocket etc.
Components are required with high environment.
3. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, it is provided on the side of graphite annulus
Gap adjustment part, specific gap adjustment part are spring, are arranged between two graphite annulus, and then in the turbine of rocket in start-up course
In, temperature distortion occurs for capsul or baffle, and gap adjustment part can play the role of a gap adjustment, avoid graphite annulus quilt
Crushing failure, further improves unfailing performance of the dynamic sealing device under high temperature and pressure use environment, and ensure that rocket can
By operation.
4. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, the sealing blade-shaped in fluid-tight wheel
Shape is arc-shaped, is tilted along circumferential direction, in this way compared with existing conventional linear type blade, energy in the fluid-tight wheel seal process
Enough formed a circumferential direction active force, sealability is stronger, decompression the relatively straight line style blade of ability can 50% improve extremely
80%, there is more good antihypertensive effect, so that the dynamic sealing device in the present embodiment is more suitable for hyperbaric environment.
5. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, the side of fluid-tight wheel be mounted on
Bearing clearance cooperation in shaft, the other side of fluid-tight wheel and outer circle and seal casinghousing clearance fit, fluid-tight wheel and seal casinghousing
Clearance fit is non-contacting seal, so that fluid-tight wheel is during the work time without abrasion, the service life is long, high reliablity, is met
The requirement that engine is reused.
6. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, fluid-tight wheel and bearing or askew
Interstice coverage can efficiently control the pressure medium at fluid-tight wheel seal inner diameter between 0.2~0.5mm.
7. provided by the invention be suitable in high speed and high pressure dynamic sealing device and aircraft, have and institute on heat-insulating and sealing ring
The channel for stating gas blasting's fabric connectivity, due to fluid-tight wheel have it is good every pressure effect so that gas pressure be lower than medium pressure
0.03~0.05MPa of power guarantees that dielectric leakage amount is no more than 5g/s, fluid-tight wheel and split type graphite annulus combined labyrinth and carbon gland, structure
Compact, process gas stops supplying in engine working process, and system gas consumption is greatly lowered.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.In the accompanying drawings:
Fig. 1 is the schematic cross-sectional view of dynamic sealing device in the embodiment of the present invention.
Fig. 2 is the schematic cross-sectional view of fluid-tight wheel in dynamic sealing device shown in Fig. 1.
Fig. 3 is the schematic view of the front view of fluid-tight wheel in dynamic sealing device shown in Fig. 1.
Wherein, the appended drawing reference in above-mentioned attached drawing are as follows:
1, fluid-tight wheel；15, blade is sealed；2, tension spring；4, seal casinghousing；6, graphite annulus；7, baffle；8, axle sleeve；10, gap
Regulating part；11, bearing；12, shaft；13, gas blasting's structure.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
It is specifically to apply in liquid-propellant rocket engine methane according to high speed and high pressure dynamic sealing device is suitable in the present embodiment
Between pump and turbine, for storing the sealing between cryogenic liquid methane and the cavity of high-temperature turbine working medium two media.
Certainly, the dynamic sealing device in the present embodiment is not limited to be applied in rocket, it can also be used to fit under high speed and high pressure
In the rotating device in the fields such as aviation, weapons.
Specifically, as shown in Figures 1 to 3, the high speed and high pressure dynamic sealing device that is suitable in this implementation includes seal casinghousing 4,
Two cavitys of sealing to be formed are spaced, the through-hole of two cavitys of connection is offered on seal casinghousing 4；Shaft 12, rotatably and at least
Extend partially through through-hole setting；Fluid-tight wheel 1 is mounted in shaft 12, is rotated with the rotation of shaft 12, and can rotation when with
Fluid-tight is formed between seal casinghousing 4；And heat-insulating and sealing ring, it is arranged between shaft 12 and seal casinghousing 4, and close on fluid-tight wheel
1 setting, and combination sealing is formed with fluid-tight wheel 1.And then using the dynamic sealing device in the present embodiment, in high revolving speed, super-pressure
Under the bad working environments such as power, temperature gradient be big, fluid-tight wheel 1 and heat-insulating and sealing ring form combined labyrinth and carbon gland, the shaft 12 of high-speed rotation
So that fluid-tight wheel 1 forms fluid-tight between seal casinghousing 4 and shaft 12, a retardation can be played to high pressure, revolving speed is got over
Height, it is stronger to the retardation of high pressure, and then impact of the high pressure to entire dynamic sealing device is greatly reduced, and in shaft
Between 12 and seal casinghousing 4, and the heat-insulating and sealing ring for closing on the setting of fluid-tight wheel 1 can play an interval action to high temperature, greatly
Reduce influence of the high temperature to entire dynamic sealing device greatly, and then under the bad working environments such as high revolving speed, high pressure, temperature gradient be big
Improve the reliability and service life of dynamic sealing device.
Specifically, two cavitys in this implementation include a high temperature cavity and a high-pressure chamber, and the side medium in rocket is height
Cavity is pressed, the turbine chamber in rocket is high temperature cavity, and the heat-insulating and sealing ring in the present embodiment closes on the setting of high temperature cavity, fluid-tight wheel
1 closes on high-pressure chamber setting, so that the dynamic sealing device in the present embodiment has better high pressure-temperature durability.Tool
Sealing device in this implementation of body is used for sealing medium side and turbine chamber, and one end of shaft 12 is connected to turbine chamber, and can be with whirlpool
Turbine in wheel chamber is rotated and is rotated.
With further reference to Fig. 1, the heat-insulating and sealing ring in this implementation includes the graphite annulus 6 being set in shaft 12.Graphite annulus 6
Specially split type graphite annulus 6, quantity are two, the main isolation technology gas in engine precooling process of left side graphite annulus 6
With the effect of medium；The graphite annulus 6 mainly plays reducing pressure by regulating flow in operation process, advantageously reduces at the graphite annulus 6 of right side
Pressure medium achievees the purpose that reduce dielectric leakage.
Preferably, the dynamic sealing device in the present embodiment further includes the compensating part being set in outside graphite annulus 6, and compensating part is specific
For the tension spring 2 being set in outside graphite annulus 6.The present embodiment has by the way that compensating part, compensating part are arranged outside graphite annulus 6 so that graphite
The pre-pressing force that ring 6 inside contracts, so that graphite annulus 6 while temperature interval before and after meeting sealing, deforms system structure
It beats with rotor adaptable, and after split type 6 inner hole of graphite annulus is because of the abrasion of 12 high-speed rotation of shaft, it is acted in tension spring 2
Graphite annulus 6 can compensate automatically under power, guarantee that its performance does not reduce graphite annulus 6 after a number of uses, meet engine and repeat to make
It is required that so that components are required high environment suitable for rocket etc. by the better reliability of dynamic sealing device.
Graphite annulus 6 is specifically mounted on the axle sleeve 8 in shaft 12 in this implementation, side respectively with seal casinghousing 4 and tight
Gu the baffle 7 on seal casinghousing 4 cooperates, the space formed by seal casinghousing 4, baffle 7 and axle sleeve 8 is limited, so that graphite
Ring 6 can reliably be run in the space.
It is preferred that being provided with gap adjustment part 10 on the side of the graphite annulus 6 in this implementation, specific gap adjustment part 10 is bullet
Spring, be arranged between two graphite annulus 6, and then the turbine of rocket during startup, capsul or baffle 7 generation become by heat
Shape, gap adjustment part 10 can play the role of a gap adjustment, graphite annulus 6 avoided to be crushed failure, further improve dynamic
Unfailing performance of the sealing device under high temperature and pressure use environment, ensure that the reliability service of rocket.
As shown in Figures 2 and 3, close in the fluid-tight wheel 1 preferably in the present embodiment to fluid-tight wheel 1 in this present embodiment
Envelope 15 shape of blade is arc-shaped, is tilted along circumferential direction, in this way compared with existing conventional linear type blade, the fluid-tight wheel 1
The active force of a circumferential direction is capable of forming in seal process, sealability is stronger, and the decompression relatively straight line style blade of ability can
50% improves to 80%, has more good antihypertensive effect, so that the dynamic sealing device in the present embodiment is more suitable for
Hyperbaric environment.
With further reference to Fig. 1, the side of fluid-tight wheel 1 and 11 clearance fit of bearing being mounted in shaft 12, the other side and
Outer circle and 4 clearance fit of seal casinghousing, fluid-tight wheel 1 and 4 clearance fit of seal casinghousing are non-contacting seal, so that liquid
Envelope wheel 1 is during the work time without abrasion, and the service life is long, high reliablity, meets the requirement of engine reuse, while fluid-tight wheel 1
Under high rotational speeds, fluid-tight wheel 1 is rotate together at high speed with rotor, surrounding medium is thrown away by centrifugal force effect, in turn
So that the pressure of medium in the axial direction is greatly lowered, pressure medium at split type graphite annulus 6 can reduce.Wherein,
Gap range can efficiently control the pressure medium at 1 seal inner diameter of fluid-tight wheel between 0.2~0.5mm.
With further reference to Fig. 1, dynamic sealing device further includes gas blasting's structure 13, is had and the gas on heat-insulating and sealing ring
Body blow down structure 13 be connected to channel, due to fluid-tight wheel 1 have it is good every pressure effect so that gas pressure be lower than pressure medium
0.03~0.05MPa guarantees that dielectric leakage amount is no more than 5g/s, 6 combined labyrinth and carbon gland of fluid-tight wheel 1 and split type graphite annulus, structure
Compact, process gas stops supplying in engine working process, and system gas consumption is greatly lowered.
A kind of aircraft is additionally provided in the present embodiment, including is suitable for high speed and high pressure dynamic sealing device, and it is high to be suitable for high speed
Pressure uses dynamic sealing device for dynamic sealing device as described above, and then advantage possessed by dynamic sealing device in the present embodiment, this
Aircraft in embodiment should also have, and details are not described herein.
Obviously, the above embodiments are merely examples for clarifying the description, and does not limit the embodiments.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of variation or
It changes.There is no necessity and possibility to exhaust all the enbodiments.And it is extended from this it is obvious variation or
It changes still within the protection scope of the invention.
Claims (14)
1. one kind is suitable for high speed and high pressure dynamic sealing device characterized by comprising
Seal casinghousing (4) is spaced two cavitys of sealing to be formed, and connection two cavity is offered on the seal casinghousing (4)
Through-hole；
Shaft (12) can be rotated and at least partly be arranged through the through-hole；
Fluid-tight wheel (1) is mounted on the shaft (12), is rotated with the rotation of the shaft (12), and can rotation when with
Seal casinghousing forms fluid-tight between (4)；And
Heat-insulating and sealing ring is arranged between the shaft (12) and the seal casinghousing (4), and closes on the fluid-tight wheel (1) and set
It sets, and forms combination sealing with the fluid-tight wheel (1).
2. according to claim 1 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that two cavity includes one
High temperature cavity and a high-pressure chamber, the heat-insulating and sealing ring close on the high temperature cavity setting, and the fluid-tight wheel (1) is closed on described
High-pressure chamber setting.
3. according to claim 1 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the heat-insulating and sealing ring packet
Include the graphite annulus (6) being mounted on the shaft (12).
4. according to claim 3 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the quantity of graphite annulus (6)
It is two.
5. according to claim 1 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the dynamic sealing device is also
Including the compensating part being set in outside the heat-insulating and sealing ring, the compensating part has so that the pre-pressing that heat-insulating and sealing ring inside contracts
Power.
6. according to claim 5 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the compensating part is to be arranged
Tension spring (2) outside the heat-insulating and sealing ring.
7. according to claim 1 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the dynamic sealing device is also
Including the gap adjustment part (10) being arranged on the side of the heat-insulating and sealing ring.
8. according to any one of claim 1 to 7 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that described
Sealing blade (15) shape in fluid-tight wheel (1) is arc-shaped, is radially tilted.
9. according to any one of claim 1 to 7 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that described
The side of fluid-tight wheel (1) and bearing (11) clearance fit being mounted on the shaft (12), the other side and outer circle with it is described close
Capsule body (4) clearance fit.
10. according to claim 9 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that the interstice coverage exists
Between 0.2~0.5mm.
11. according to any one of claim 1 to 7 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that described
Further include gas blasting's structure (13) suitable for high speed and high pressure dynamic sealing device, has and the gas on the heat-insulating and sealing ring
Blow down the channel of structure (13) connection.
12. according to any one of claim 1 to 7 be suitable for high speed and high pressure dynamic sealing device, which is characterized in that described
Sealing device is used for sealing medium side and turbine chamber, and one end of the shaft (12) is connected to the turbine chamber, and can be with described
Turbine in turbine chamber is rotated and is rotated.
13. a kind of aircraft, including it is suitable for high speed and high pressure dynamic sealing device, which is characterized in that the high speed and high pressure that is suitable for is used
Dynamic sealing device is to be suitable for high speed and high pressure dynamic sealing device described in any one of claims 1 to 12.
14. aircraft according to claim 13, which is characterized in that the aircraft is rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910185707.7A CN110030381A (en) | 2019-03-12 | 2019-03-12 | One kind being suitable for high speed and high pressure dynamic sealing device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910185707.7A CN110030381A (en) | 2019-03-12 | 2019-03-12 | One kind being suitable for high speed and high pressure dynamic sealing device and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN110030381A true CN110030381A (en) | 2019-07-19 |
Family
ID=67235938
Family Applications (1)
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|---|---|---|---|
| CN201910185707.7A Pending CN110030381A (en) | 2019-03-12 | 2019-03-12 | One kind being suitable for high speed and high pressure dynamic sealing device and aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111030354A (en) * | 2019-12-10 | 2020-04-17 | 宁波上中下自动变速器有限公司 | Motor and vehicle |
| CN112431788A (en) * | 2020-10-29 | 2021-03-02 | 北京航天动力研究所 | High-speed low-leakage liquid seal wheel floating ring combined sealing device |
| CN112502859A (en) * | 2020-10-09 | 2021-03-16 | 蓝箭航天技术有限公司 | High-speed dynamic sealing element test device for rocket engine |
| CN112628190A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Combined sealing device for liquid rocket engine turbine pump |
| CN112728087A (en) * | 2021-01-07 | 2021-04-30 | 湖北航天技术研究院总体设计所 | Shaft seal device for liquid rocket engine |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101821481A (en) * | 2007-10-13 | 2010-09-01 | 康明斯涡轮增压技术有限公司 | Turbomachine |
| CN202194853U (en) * | 2011-07-22 | 2012-04-18 | 中国航天科技集团公司第六研究院第十一研究所 | Floating ring sealing device capable of achieving axial force balance |
| CN104329260A (en) * | 2014-10-30 | 2015-02-04 | 江苏海天泵阀制造有限公司 | Slurry transmitting pump under vertical magnetic driving multiple sealing liquid |
| CN104565363A (en) * | 2014-12-30 | 2015-04-29 | 中国航天科技集团公司第六研究院第十一研究所 | Combined type sealing device for low-temperature engine oxidizing agent |
| CN105358800A (en) * | 2013-07-03 | 2016-02-24 | 舍弗勒技术股份两合公司 | Central valve system for a dry belt drive |
| CN107588038A (en) * | 2017-10-11 | 2018-01-16 | 西安航天动力研究所 | A kind of turbine pump mechanical seal structure |
| CN207246090U (en) * | 2017-10-11 | 2018-04-17 | 西安航天动力研究所 | A kind of turbine pump mechanical seal structure |
| CN107975600A (en) * | 2017-11-23 | 2018-05-01 | 西安航天动力研究所 | A kind of self forcing cooling refractory machinery seals device |
| CN207634701U (en) * | 2017-11-30 | 2018-07-20 | 潍坊鑫山环保重工科技有限公司 | A kind of rubber-plastic sealing structure for belt Alkali-filter |
| CN208169191U (en) * | 2018-05-08 | 2018-11-30 | 利欧集团湖南泵业有限公司 | A kind of multi-panel double sealing structure of large size the Yellow River pump |
| CN208295124U (en) * | 2018-06-09 | 2018-12-28 | 山东浩信浩德精密机械有限公司 | Hub unit |
| WO2019031377A1 (en) * | 2017-08-07 | 2019-02-14 | イーグル工業株式会社 | Segment seal |
| CN209875952U (en) * | 2019-03-12 | 2019-12-31 | 北京星际荣耀空间科技有限公司 | Dynamic sealing device suitable for high speed and high pressure and aircraft |
-
2019
- 2019-03-12 CN CN201910185707.7A patent/CN110030381A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101821481A (en) * | 2007-10-13 | 2010-09-01 | 康明斯涡轮增压技术有限公司 | Turbomachine |
| CN202194853U (en) * | 2011-07-22 | 2012-04-18 | 中国航天科技集团公司第六研究院第十一研究所 | Floating ring sealing device capable of achieving axial force balance |
| CN105358800A (en) * | 2013-07-03 | 2016-02-24 | 舍弗勒技术股份两合公司 | Central valve system for a dry belt drive |
| CN104329260A (en) * | 2014-10-30 | 2015-02-04 | 江苏海天泵阀制造有限公司 | Slurry transmitting pump under vertical magnetic driving multiple sealing liquid |
| CN104565363A (en) * | 2014-12-30 | 2015-04-29 | 中国航天科技集团公司第六研究院第十一研究所 | Combined type sealing device for low-temperature engine oxidizing agent |
| WO2019031377A1 (en) * | 2017-08-07 | 2019-02-14 | イーグル工業株式会社 | Segment seal |
| CN207246090U (en) * | 2017-10-11 | 2018-04-17 | 西安航天动力研究所 | A kind of turbine pump mechanical seal structure |
| CN107588038A (en) * | 2017-10-11 | 2018-01-16 | 西安航天动力研究所 | A kind of turbine pump mechanical seal structure |
| CN107975600A (en) * | 2017-11-23 | 2018-05-01 | 西安航天动力研究所 | A kind of self forcing cooling refractory machinery seals device |
| CN207634701U (en) * | 2017-11-30 | 2018-07-20 | 潍坊鑫山环保重工科技有限公司 | A kind of rubber-plastic sealing structure for belt Alkali-filter |
| CN208169191U (en) * | 2018-05-08 | 2018-11-30 | 利欧集团湖南泵业有限公司 | A kind of multi-panel double sealing structure of large size the Yellow River pump |
| CN208295124U (en) * | 2018-06-09 | 2018-12-28 | 山东浩信浩德精密机械有限公司 | Hub unit |
| CN209875952U (en) * | 2019-03-12 | 2019-12-31 | 北京星际荣耀空间科技有限公司 | Dynamic sealing device suitable for high speed and high pressure and aircraft |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111030354A (en) * | 2019-12-10 | 2020-04-17 | 宁波上中下自动变速器有限公司 | Motor and vehicle |
| CN112502859A (en) * | 2020-10-09 | 2021-03-16 | 蓝箭航天技术有限公司 | High-speed dynamic sealing element test device for rocket engine |
| CN112502859B (en) * | 2020-10-09 | 2022-03-04 | 蓝箭航天技术有限公司 | High-speed dynamic sealing element test device for rocket engine |
| CN112431788A (en) * | 2020-10-29 | 2021-03-02 | 北京航天动力研究所 | High-speed low-leakage liquid seal wheel floating ring combined sealing device |
| CN112628190A (en) * | 2020-12-18 | 2021-04-09 | 西安航天动力研究所 | Combined sealing device for liquid rocket engine turbine pump |
| CN112628190B (en) * | 2020-12-18 | 2024-02-09 | 西安航天动力研究所 | Combined sealing device for turbopump of liquid rocket engine |
| CN112728087A (en) * | 2021-01-07 | 2021-04-30 | 湖北航天技术研究院总体设计所 | Shaft seal device for liquid rocket engine |
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