CN110030381B - Be suitable for high-speed high pressure to use dynamic seal device and aircraft - Google Patents
Be suitable for high-speed high pressure to use dynamic seal device and aircraft Download PDFInfo
- Publication number
- CN110030381B CN110030381B CN201910185707.7A CN201910185707A CN110030381B CN 110030381 B CN110030381 B CN 110030381B CN 201910185707 A CN201910185707 A CN 201910185707A CN 110030381 B CN110030381 B CN 110030381B
- Authority
- CN
- China
- Prior art keywords
- sealing
- dynamic
- rotating shaft
- pressure
- sealing device
- 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.)
- Active
Links
- 238000007789 sealing Methods 0.000 claims abstract description 181
- 239000007788 liquid Substances 0.000 claims abstract description 60
- 238000009413 insulation Methods 0.000 claims abstract description 18
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 40
- 238000007664 blowing Methods 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 230000000903 blocking effect Effects 0.000 abstract description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 15
- 238000000034 method Methods 0.000 description 14
- 239000007789 gas Substances 0.000 description 13
- 230000001603 reducing effect Effects 0.000 description 7
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 230000006837 decompression 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Devices (AREA)
Abstract
The invention relates to the technical field of sealing, in particular to a dynamic sealing device suitable for high-speed high-pressure use and an aircraft. The dynamic sealing device comprises a sealing shell, two cavities to be sealed are spaced, and a through hole for communicating the two cavities is formed in the sealing shell; a rotating shaft rotatable and at least partially disposed through the through hole; the liquid seal wheel is arranged on the rotating shaft, rotates along with the rotation of the rotating shaft and can form liquid seal with the sealing shell during rotation; and the heat insulation sealing ring is arranged between the rotating shaft and the sealing shell, is close to the liquid sealing wheel and forms combined sealing with the liquid sealing wheel, so that the liquid sealing wheel forms liquid sealing between the sealing shell and the rotating shaft by the rotating shaft at high speed, a blocking effect can be achieved on high pressure, the heat insulation sealing ring can play a role in separating high temperature, the influence of high temperature on the whole dynamic sealing device is greatly reduced, and the reliability and the service life of the dynamic sealing device are improved under severe working conditions such as high rotating speed, high pressure, large temperature gradient and the like.
Description
Technical Field
The invention relates to the technical field of sealing, in particular to a dynamic sealing device suitable for high-speed high-pressure use and an aircraft.
Background
At present, the world is in the trend of large development of commercial aerospace, and the rocket engine with high reliability, low cost, repeated use and no pollution becomes the development direction of the liquid rocket engine. The liquid oxygen methane engine in the rocket has the advantages of good cooling performance, high combustion efficiency, difficult coking, higher specific impulse than that of a liquid oxygen kerosene engine, and the cost of methane fuel per unit mass is only 1/3 of that of kerosene, and 1/30 of that of liquid hydrogen, so that the liquid oxygen methane engine can be widely applied to the field of aerospace.
The methane pump is an important component of the liquid oxygen methane engine and is used for conveying low-temperature liquid methane required by the engine in operation, and the methane pump is arranged close to the turbine cavity. A set of sealing device is arranged between the liquid rocket engine pump and the turbine, so that a seal is formed between the medium side of the engine pump and the turbine cavity, the sealing device is influenced by high temperature generated by combustion of fuel in the turbine cavity, and the temperature difference between the medium side and the turbine cavity at the sealing position is more than or equal to 600K, so that the conventional sealing device cannot be applied. In the prior art, there are two main types of seals used in high-pressure and high-speed environments at home and abroad:
The principle of the non-contact type seal is that the labyrinth partial gap is adopted to realize gradual decompression and sealing, such as floating ring, labyrinth seal and the like, the seal structure is simple, but the sealing performance is not ideal, the leakage amount of medium is large in working, and a high-pressure blowing system is additionally added to improve the sealing reliability;
The other is a contact type mechanical seal, the principle is that the elastic element is utilized to enable the friction pair to be tightly attached to realize the seal, the sealing structure is mature, static sealing can be realized, and the leakage amount of a medium is small during dynamic working. However, the friction pair sealing surface abrasion loss is large in the starting and shutting processes, and after the sealing is used for many times, the sealing performance is reduced and even fails, so that the sealing device can not meet the requirements of long service life, high reliability and repeated use under severe working conditions such as high rotating speed, ultrahigh pressure, large temperature gradient and the like of the turbine pump.
Disclosure of Invention
The invention mainly aims to provide a sealing device and an aircraft, which are used for solving or at least relieving the problem that the sealing device in the prior art cannot meet the requirements of long service life, high reliability and repeated use under severe working conditions such as high rotating speed, high pressure, large temperature gradient and the like.
In order to achieve the above object, the present invention provides a dynamic sealing device suitable for high-speed and high-pressure use, comprising:
the sealing shell is provided with a through hole communicated with the two cavities;
a rotating shaft rotatable and at least partially disposed through the through hole;
the liquid seal wheel is arranged on the rotating shaft, rotates along with the rotation of the rotating shaft, and can form liquid seal with the sealing shell during rotation; and
The heat-insulating sealing ring is arranged between the rotating shaft and the sealing shell, is arranged close to the liquid sealing wheel and forms combined sealing with the liquid sealing wheel.
Further, the two cavities comprise a high-temperature cavity and a high-pressure cavity, the heat insulation sealing ring is arranged adjacent to the high-temperature cavity, and the liquid sealing wheel is arranged adjacent to the high-pressure cavity.
Further, the heat-insulating sealing ring comprises a graphite ring mounted on the rotating shaft.
Further, the number of graphite rings is two.
Further, the dynamic sealing device also comprises a compensation piece sleeved outside the heat insulation sealing ring, wherein the compensation piece has a pre-compression force for enabling the heat insulation sealing ring to be compressed inwards.
Further, the compensation piece is a tension spring sleeved outside the heat insulation sealing ring.
Further, the dynamic sealing device further comprises a gap adjusting piece arranged on the side edge of the heat insulation sealing ring.
Further, the sealing blades in the liquid sealing wheel are arc-shaped and incline along the radial direction.
Further, one side of the liquid seal wheel is in clearance fit with a bearing arranged on the rotating shaft, and the other side and the outer circle are in clearance fit with the seal shell.
Further, the gap ranges between 0.2 and 0.5mm.
Further, the dynamic sealing device suitable for high speed and high pressure further comprises a gas blowing structure, and the heat insulation sealing ring is provided with a channel communicated with the gas blowing structure.
Further, the sealing device is used for sealing the medium side from the turbine cavity, and one end of the rotating shaft is communicated with the turbine cavity and can rotate along with the rotation of the turbine in the turbine cavity.
The invention also provides an aircraft, which comprises the dynamic sealing device suitable for high speed and high pressure.
Further, the aircraft is a rocket.
The technical scheme of the invention has the following advantages:
1. The invention provides a dynamic sealing device suitable for high speed and high pressure and an aircraft, wherein under severe working conditions such as high rotating speed, ultrahigh pressure, large temperature gradient and the like, a combined seal is formed between a liquid sealing wheel and a heat insulation sealing ring, a liquid sealing wheel is formed between a sealing shell and the rotating shaft by a rotating shaft rotating at high speed, a blocking effect on the high pressure can be achieved, the higher the rotating speed is, the stronger the blocking effect on the high pressure is, the impact of the high pressure on the whole dynamic sealing device is further greatly reduced, and the heat insulation sealing ring arranged between the rotating shaft and the sealing shell and close to the liquid sealing wheel can play a role of spacing the high temperature, so that the influence of the high temperature on the whole dynamic sealing device is greatly reduced, and the reliability and the service life of the dynamic sealing device are further improved under severe working conditions such as high rotating speed, high pressure, large temperature gradient and the like.
2. The dynamic sealing device suitable for the high-speed high-pressure use and the aircraft provided by the invention further comprises the compensation piece sleeved outside the graphite ring, wherein the compensation piece has pre-compression force for enabling the graphite ring to be compressed inwards, so that the graphite ring has strong adaptability to system structural deformation and rotor runout while meeting the temperature interval before and after sealing, and the graphite ring can be automatically compensated under the action force of the tension spring after the inner hole of the split type graphite ring is worn due to the high-speed rotation of the rotating shaft, so that the performance of the graphite ring is not reduced after the graphite ring is repeatedly used, the requirement of the engine on repeated use is met, the reliability of the dynamic sealing device is better, and the dynamic sealing device is suitable for environments with extremely high requirements on parts such as rockets.
3. According to the dynamic sealing device and the aircraft, provided by the invention, the gap adjusting parts are arranged on the side edges of the graphite rings, the specific gap adjusting parts are springs and are arranged between the two graphite rings, so that the sealing shell or the baffle plate is deformed by heat in the starting process of the turbine of the rocket, the gap adjusting parts can play a role in gap adjustment, the graphite rings are prevented from being crushed and invalid, the reliability of the dynamic sealing device under the high-temperature and high-pressure use environment is further improved, and the reliable operation of the rocket is ensured.
4. The dynamic sealing device suitable for high speed and high pressure and the aircraft provided by the invention have the advantages that the sealing blades in the liquid sealing wheel are arc-shaped and incline along the circumferential direction, so that compared with the conventional linear blades, the dynamic sealing device can form acting force along the circumferential direction in the sealing process of the liquid sealing wheel, has stronger sealing capability, and the pressure reducing capability can be improved to 80% by 50% relative to the linear blades, and has better pressure reducing effect, so that the dynamic sealing device in the embodiment is more suitable for high pressure environment.
5. The dynamic sealing device suitable for high speed and high pressure and the aircraft provided by the invention have the advantages that one side of the liquid sealing wheel is in clearance fit with the bearing arranged on the rotating shaft, the other side and the outer circle of the liquid sealing wheel are in clearance fit with the sealing shell, the liquid sealing wheel is in clearance fit with the sealing shell, and the liquid sealing wheel is in non-contact sealing, so that the liquid sealing wheel is free from abrasion in the working process, long in service life and high in reliability, and the requirement of repeated use of an engine is met.
6. The dynamic sealing device suitable for high-speed high-pressure and the aircraft provided by the invention have the advantages that the gap between the liquid sealing wheel and the bearing or between the liquid sealing wheel and the bearing is 0.2-0.5 mm, and the medium pressure at the sealing inner diameter of the liquid sealing wheel can be effectively controlled.
7. The heat-insulating sealing ring is provided with the channel communicated with the gas blowing structure, and the liquid sealing wheel has good pressure-insulating effect, so that the gas pressure is lower than the medium pressure by 0.03-0.05 MPa, the medium leakage is ensured not to exceed 5g/s, the liquid sealing wheel and the split graphite ring are combined for sealing, the structure is compact, the process gas stops being supplied in the working process of the engine, and the gas consumption of the system is greatly reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art. In the drawings:
fig. 1 is a schematic cross-sectional view of a dynamic seal device according to an embodiment of the present invention.
Fig. 2 is a schematic cross-sectional view of a hydraulic seal wheel in the dynamic seal device shown in fig. 1.
Fig. 3 is a schematic front view of a hydraulic sealing wheel in the dynamic sealing device shown in fig. 1.
Wherein, the reference numerals in the drawings are as follows:
1. a liquid seal wheel; 15. sealing the blade; 2. a tension spring; 4. a seal housing; 6. a graphite ring; 7. a baffle; 8. a shaft sleeve; 10. a gap adjusting member; 11. a bearing; 12. a rotating shaft; 13. and a gas blowing structure.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
According to the embodiment, the dynamic sealing device suitable for high speed and high pressure is particularly applied between a methane pump and a turbine of a liquid rocket engine and used for sealing between cavities for storing two mediums, namely low-temperature liquid methane and high-temperature turbine working media.
Of course, the dynamic seal device in this embodiment is not limited to be applied to rockets, and can be applied to rotating devices in the fields of aviation, weapons and the like, which are applicable to high-speed high-pressure.
Specifically, as shown in fig. 1 to 3, the dynamic sealing device suitable for high speed and high pressure in the present embodiment includes a sealing housing 4, two cavities to be sealed are spaced apart, and a through hole for communicating the two cavities is formed in the sealing housing 4; a rotation shaft 12 rotatably provided at least partially through the through hole; the liquid seal wheel 1 is arranged on the rotating shaft 12, rotates along with the rotation of the rotating shaft 12, and can form liquid seal with the seal shell 4 during rotation; and a heat-insulating sealing ring arranged between the rotating shaft 12 and the sealing shell 4 and adjacent to the liquid sealing wheel 1 and forming combined sealing with the liquid sealing wheel 1. Furthermore, by adopting the dynamic sealing device in the embodiment, under severe working conditions such as high rotating speed, ultrahigh pressure, large temperature gradient and the like, the liquid sealing wheel 1 and the heat insulation sealing ring form combined seal, the rotating shaft 12 rotating at high speed enables the liquid sealing wheel 1 to form liquid seal between the sealing shell 4 and the rotating shaft 12, a blocking effect on the high pressure can be achieved, the higher the rotating speed is, the stronger the blocking effect on the high pressure is, the impact of the high pressure on the whole dynamic sealing device is greatly reduced, the heat insulation sealing ring arranged between the rotating shaft 12 and the sealing shell 4 and close to the liquid sealing wheel 1 can play a role of spacing the high temperature, the influence of the high temperature on the whole dynamic sealing device is greatly reduced, and the reliability and the service life of the dynamic sealing device are further improved under severe working conditions such as high rotating speed, high pressure, large temperature gradient and the like.
Specifically, two cavities in this implementation include a high temperature cavity and a high pressure cavity, and the medium side in the rocket is the high pressure cavity, and the turbine chamber in the rocket is the high temperature cavity, and the heat insulating sealing ring in this embodiment sets up near the high temperature cavity, and liquid seal wheel 1 sets up near the high pressure cavity, and then makes the dynamic seal device in this embodiment have better high pressure high temperature durability. The sealing device in the present embodiment is used for sealing the medium side from the turbine chamber, and one end of the rotating shaft 12 is communicated with the turbine chamber and can rotate along with the rotation of the turbine in the turbine chamber.
With further reference to fig. 1, the heat-insulating seal ring in this embodiment comprises a graphite ring 6 which is sleeved on a rotating shaft 12. The graphite rings 6 are split graphite rings 6, the number of the split graphite rings is two, and the left graphite ring 6 mainly isolates the effect of process gas and medium in the pre-cooling process of the engine; the graphite ring 6 mainly plays a role in throttling and reducing pressure in the operation process, is beneficial to reducing the medium pressure at the right side graphite ring 6, and achieves the purpose of reducing the medium leakage.
Preferably, the dynamic sealing device in this embodiment further includes a compensation member sleeved outside the graphite ring 6, and the compensation member is specifically a tension spring 2 sleeved outside the graphite ring 6. According to the embodiment, the compensation piece is arranged outside the graphite ring 6, the compensation piece has the pre-compression force for enabling the graphite ring 6 to be compressed, the graphite ring 6 is enabled to meet the temperature interval before and after sealing, the adaptability to system structural deformation and rotor runout is high, the graphite ring 6 can be automatically compensated after the inner hole of the split type graphite ring 6 is worn due to the high-speed rotation of the rotating shaft 12 under the acting force of the tension spring 2, the performance of the graphite ring 6 is guaranteed not to be reduced after the graphite ring is used for many times, the requirement of repeated use of an engine is met, the reliability of the dynamic sealing device is better, and the dynamic sealing device is suitable for environments with extremely high requirements on parts such as rockets.
In this embodiment, the graphite ring 6 is specifically mounted on the shaft sleeve 8 on the rotating shaft 12, and the sides of the graphite ring are respectively matched with the seal housing 4 and the baffle plate 7 fastened on the seal housing 4, and are limited by the space formed by the seal housing 4, the baffle plate 7 and the shaft sleeve 8, so that the graphite ring 6 can reliably operate in the space.
Preferably, the side edge of the graphite ring 6 in the implementation is provided with a gap adjusting piece 10, the specific gap adjusting piece 10 is a spring and is arranged between the two graphite rings 6, so that the sealing shell or the baffle 7 is heated and deformed in the starting process of the rocket turbine, the gap adjusting piece 10 can play a role in gap adjustment, the graphite rings 6 are prevented from being crushed and invalid, the reliability of the dynamic sealing device under the high-temperature and high-pressure use environment is further improved, and the reliable operation of the rocket is ensured.
As shown in fig. 2 and 3, for the liquid seal wheel 1 in this embodiment, the shape of the sealing blade 15 in the liquid seal wheel 1 in this embodiment is preferably arc-shaped, and is inclined along the circumferential direction, so that compared with the existing conventional linear blade, in the sealing process of the liquid seal wheel 1, an acting force in the circumferential direction can be formed, the sealing capability is stronger, and the pressure reducing capability can be improved to 80% by 50% relative to the linear blade, so that the dynamic sealing device in this embodiment has a better pressure reducing effect, and is more suitable for a high-pressure environment.
Referring further to fig. 1, one side of the liquid seal wheel 1 is in clearance fit with a bearing 11 installed on a rotating shaft 12, the other side of the liquid seal wheel 1 is in clearance fit with a seal shell 4, the liquid seal wheel 1 is in clearance fit with the seal shell 4 and is in non-contact seal, so that the liquid seal wheel 1 is free of abrasion in the working process, long in service life and high in reliability, the requirement of repeated use of an engine is met, meanwhile, the liquid seal wheel 1 and a rotor rotate together at a high speed under the high-speed rotation condition, surrounding media are thrown out under the action of centrifugal force, the pressure of the media in the axial direction is greatly reduced, and the pressure of the media at the split graphite ring 6 can be reduced. Wherein, the gap range is between 0.2 and 0.5mm, and then the medium pressure at the inner sealing diameter of the liquid sealing wheel 1 can be effectively controlled.
Further referring to fig. 1, the dynamic sealing device further comprises a gas blowing structure 13, the heat insulation sealing ring is provided with a channel communicated with the gas blowing structure 13, the gas pressure is lower than the medium pressure by 0.03-0.05 MPa due to the good pressure insulation effect of the liquid sealing wheel 1, the medium leakage is ensured not to exceed 5g/s, the liquid sealing wheel 1 and the split graphite ring 6 are combined and sealed, the structure is compact, the process gas stops supplying during the working process of the engine, and the gas consumption of the system is greatly reduced.
The present embodiment also provides an aircraft, which includes a dynamic sealing device suitable for high-speed and high-pressure, and the dynamic sealing device suitable for high-speed and high-pressure is the dynamic sealing device described above, so that the dynamic sealing device in this embodiment has advantages, and the aircraft in this embodiment should also have advantages, which are not described herein.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (11)
1. A dynamic seal device suitable for high-speed, high-pressure and high-temperature applications, comprising:
the sealing shell (4) is used for separating two cavities to be sealed, and a through hole for communicating the two cavities is formed in the sealing shell (4);
a spindle (12) rotatable and disposed at least partially through the through-hole;
The liquid seal wheel (1) is arranged on the rotating shaft (12), rotates along with the rotation of the rotating shaft (12), and can form liquid seal with the seal shell (4) during rotation; and
The heat-insulating sealing ring is arranged between the rotating shaft (12) and the sealing shell (4), is arranged close to the liquid sealing wheel (1) and forms combined sealing with the liquid sealing wheel (1);
the two cavities comprise a high-temperature cavity and a high-pressure cavity, the heat insulation sealing ring is arranged adjacent to the high-temperature cavity, and the liquid sealing wheel (1) is arranged adjacent to the high-pressure cavity;
The heat-insulating sealing ring comprises a graphite ring (6) arranged on the rotating shaft (12);
the dynamic sealing device also comprises a compensation piece sleeved outside the heat insulation sealing ring, and the compensation piece has pre-compression force for enabling the heat insulation sealing ring to be compressed inwards.
2. Dynamic sealing device suitable for high speed, high pressure and high temperature applications according to claim 1, characterized in that the number of graphite rings (6) is two.
3. The dynamic sealing device for high speed, high pressure and high temperature according to claim 2, wherein the compensator is a tension spring (2) sleeved outside the heat insulation sealing ring.
4. Dynamic sealing device suitable for high speed, high pressure and high temperature applications according to claim 1, characterized in that it further comprises a gap adjusting element (10) provided on the side of the heat insulating sealing ring.
5. Dynamic sealing device suitable for high speed, high pressure and high temperature according to any of claims 1 to 4, characterized in that the sealing blades (15) in the hydraulic sealing wheel (1) are arc-shaped in shape, sloping in radial direction.
6. Dynamic sealing device suitable for high speed, high pressure and high temperature according to any of claims 1 to 4, characterized in that one side of the hydraulic sealing wheel (1) is in clearance fit with a bearing (11) mounted on the rotating shaft (12), and the other side and the outer circle are in clearance fit with the sealing housing (4).
7. The dynamic seal device for high-speed, high-pressure and high-temperature applications as claimed in claim 6, wherein said gap ranges between 0.2 and 0.5 mm.
8. Dynamic sealing device for high speed, high pressure and high temperature according to any one of claims 1 to 4, characterized in that it further comprises a gas blowing structure (13), said heat insulating sealing ring having a channel communicating with said gas blowing structure (13).
9. Dynamic sealing device for high speed, high pressure and high temperature according to any of claims 1 to 4, characterized in that the sealing device is used for sealing medium side with turbine chamber, one end of the rotating shaft (12) is communicated with the turbine chamber and can rotate with the rotation of the turbine in the turbine chamber.
10. An aircraft comprising a dynamic sealing device for high speed, high pressure and high temperature, characterized in that the dynamic sealing device for high speed, high pressure and high temperature is a dynamic sealing device for high speed, high pressure and high temperature according to any one of claims 1 to 9.
11. The aircraft of claim 10, wherein the aircraft is a rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910185707.7A CN110030381B (en) | 2019-03-12 | 2019-03-12 | Be suitable for high-speed high pressure to use dynamic seal device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910185707.7A CN110030381B (en) | 2019-03-12 | 2019-03-12 | Be suitable for high-speed high pressure to use dynamic seal device and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110030381A CN110030381A (en) | 2019-07-19 |
| CN110030381B true CN110030381B (en) | 2024-06-21 |
Family
ID=67235938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910185707.7A Active CN110030381B (en) | 2019-03-12 | 2019-03-12 | Be suitable for high-speed high pressure to use dynamic seal device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110030381B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111030354B (en) * | 2019-12-10 | 2021-05-07 | 宁波上中下自动变速器有限公司 | Motor and vehicle |
| 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 |
| CN112431788B (en) * | 2020-10-29 | 2022-04-22 | 北京航天动力研究所 | High-speed low-leakage liquid seal wheel floating ring combined sealing device |
| 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 |
| CN112728087B (en) * | 2021-01-07 | 2023-03-24 | 湖北航天技术研究院总体设计所 | Shaft seal device for liquid rocket engine |
Citations (2)
| 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 |
| 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 |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| DE102013212935B4 (en) * | 2013-07-03 | 2024-02-08 | Schaeffler Technologies AG & Co. KG | Actuator camshaft adjuster system for a dry belt drive |
| CN104329260B (en) * | 2014-10-30 | 2016-09-21 | 江苏海天泵阀制造有限公司 | A kind of vertical magnetic drives slurry feeding pump under multi-sealed liquid |
| WO2019031377A1 (en) * | 2017-08-07 | 2019-02-14 | イーグル工業株式会社 | Segment seal |
| CN107588038B (en) * | 2017-10-11 | 2023-06-23 | 西安航天动力研究所 | Mechanical sealing structure of turbine pump |
| 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 |
| 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/CN110030381B/en active Active
Patent Citations (2)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110030381A (en) | 2019-07-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110030381B (en) | Be suitable for high-speed high pressure to use dynamic seal device and aircraft | |
| CN110005545B (en) | Squirrel-cage elastic supporting bearing cavity structure | |
| CN107387261B (en) | Combined mechanical sealing device | |
| CN109779947B (en) | Dynamic sealing device suitable for low-temperature high-speed reuse | |
| CN105114353B (en) | A kind of oxyhydrogen engine turbine pump Rayleigh slot type floating ring seal arrangement | |
| CN209875952U (en) | Dynamic sealing device suitable for high speed and high pressure and aircraft | |
| CN107588038B (en) | Mechanical sealing structure of turbine pump | |
| CN107387772B (en) | Compact ultra-high-speed high-temperature-resistant mechanical sealing device | |
| US11187093B2 (en) | Face seal assembly with thermal management circuit and an associated method thereof | |
| CN109162955B (en) | End surface labyrinth combined automatic disengaging type dynamic sealing device for engine turbo pump | |
| CN111828100A (en) | Serial dry gas sealing device for industrial steam turbine | |
| CN110094236B (en) | Helium turbine shafting structure | |
| CN113090337A (en) | Reverse shaft sealing device for double-rotor aircraft engine | |
| CN111120393A (en) | Energy storage sealing structure and dynamic sealing device for high-pressure easily-vaporized medium | |
| CN113551039A (en) | Self-adaptive graphite sealing structure for intermediate bearing cavity of aircraft engine | |
| CN111810253A (en) | Double-end-face dry air sealing device for industrial steam turbine | |
| CN203702642U (en) | Low-temperature large-shaft-diameter dry gas sealing device for centrifugal compressor | |
| CN209687780U (en) | A kind of dynamic sealing device reused suitable for low-temperature and high-speed | |
| CN110439631B (en) | Labyrinth sealing structure capable of controlling active clearance | |
| CN112012954B (en) | Turbo pump sealing mechanism and turbo pump | |
| CN213360189U (en) | Split carbon ring type single-end-face dry air sealing device for industrial steam turbine | |
| CN111810251A (en) | Split carbon ring type double-end-face dry air sealing device for industrial steam turbine | |
| CN109139913A (en) | A kind of radial direction double end-face mechanical sealing device | |
| CN111810252A (en) | Split carbon ring type serial dry gas sealing device for industrial steam turbine | |
| CN210566259U (en) | Anchor-shaped dry gas sealing mechanism |
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 | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |