CN112610697A - Mechanical seal structure for aviation oil-cooled motor - Google Patents
Mechanical seal structure for aviation oil-cooled motor Download PDFInfo
- Publication number
- CN112610697A CN112610697A CN202011506402.0A CN202011506402A CN112610697A CN 112610697 A CN112610697 A CN 112610697A CN 202011506402 A CN202011506402 A CN 202011506402A CN 112610697 A CN112610697 A CN 112610697A
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- Prior art keywords
- ring
- mechanical seal
- static
- groove
- wave spring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 230000003068 static effect Effects 0.000 claims abstract description 36
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 238000012856 packing Methods 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 abstract description 6
- 238000010030 laminating Methods 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000003889 chemical engineering Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 210000004907 gland Anatomy 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- 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
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
-
- 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
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/3436—Pressing means
- F16J15/3452—Pressing means the pressing force resulting from the action of a spring
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Mechanical Sealing (AREA)
Abstract
The application belongs to the field of mechanical sealing of aero-engines, and relates to a mechanical sealing structure for an aero-oil-cooled motor, which comprises a supporting ring (3), wherein a containing groove is formed in the inner wall, facing a motor linear shaft, of the supporting ring (3); the static ring (2) is arranged in the accommodating groove, a wave spring (1) is arranged between one end of the static ring (2) and a radial wall in the accommodating groove, a part of the other end of the static ring (2) extends out of an opening of the accommodating groove and abuts against a movable ring (7), and the movable ring (7) is arranged on a spring shaft of the motor; wherein, the containing groove is internally provided with a limiting bulge, and the static ring (2) can be abutted to the ring surface formed by the limiting bulge in the process of compressing the wave spring (1). This application designs spacing arch in the support ring, can guarantee that quiet ring and rotating ring terminal surface keep closely laminating constantly, can prevent again because of the axial atress surpasss the problem that the maximum atress of wave spring leads to the lubricating oil leakage volume exceeds standard.
Description
Technical Field
The application belongs to the field of mechanical sealing of aero-engines, and particularly relates to a mechanical sealing structure for an aero-oil cooling motor.
Background
The development of modern airplanes, particularly multi-electric airplanes, has higher and higher requirements on the capacity of an aero-generator, and the advantage of an oil-cooled generator has great advantage in the direction of a high-power motor. For an aviation oil-cooled generator, in order to prevent lubricating oil inside the generator from leaking and polluting or influencing the normal operation of other equipment on an airplane, the lubricating oil leakage amount of the generator needs to be controlled within an acceptable range of the airplane, so that the lubricating oil leakage amount is a very critical technical index, the mechanical sealing technology of the aviation generator is derived, and the mechanical sealing structure (dynamic sealing structure) also becomes one of key parts of the aviation oil-cooled generator. Compared with the traditional packing seal, the mechanical seal has long service life; compared with gap sealing, labyrinth sealing and the like, the mechanical seal has the advantages of more compact size, convenience in installation, high structural reliability and the like. In conclusion, the mechanical seal is more reasonable to select to the lubricating oil leakage amount problem of the aviation oil-cooled generator.
The mechanical seal is also called end face seal, and is a dynamic seal for a rotating shaft. The mechanical seal is widely applied to industries such as petroleum, chemical engineering, metallurgy, aviation, atomic energy and the like. The mechanical seal is a shaft seal device which is kept jointed by one or a plurality of pairs of end faces which slide relatively and are vertical to a shaft under the action of fluid pressure and elasticity (or magnetic force) of a compensation mechanism and matched with auxiliary seal to achieve leakage resistance.
A conventional mechanical seal structure is shown in fig. 1, and comprises a stationary ring (stationary ring) 11, a rotating ring (moving ring) 12, an elastic element 13, a spring seat 14, a set screw 15, a rotating ring auxiliary seal ring 16, a stationary ring auxiliary seal ring 18, and the like, and a prevention pin 17 is fixed on a gland 19 to prevent the stationary ring from rotating.
Fig. 2 shows another mechanical seal configuration, which includes a rotating ring 21 and a stationary ring assembly. The stationary ring assembly comprises a tightening block 22, a mounting seat 23, a saddle spring 24, a gasket 25, an O-shaped sealing ring 26 and a stationary ring 27. The three advantages of the invention are: (1) the saddle spring 24 provides external force to the static ring 27 to enable the static ring 27 to be propped against the end face of the movable ring to keep close fit, and the arrangement of the saddle spring 24 can push the static ring 27 to move axially after the contact end faces of the movable ring and the static ring are worn, so that the static ring 27 can always keep close fit; (2) tungsten carbide or chrome plating is sprayed on the contact end face of the movable ring 21, so that the flatness and the smoothness of the contact end face of the movable ring are greatly improved, the hardness is greatly improved, and the movable ring is more wear-resistant; (3) the O-shaped sealing ring 26 can make the static ring 27 or the dynamic ring 21 generate angular floating, and when the center of the rotating shaft slightly moves the axis, the dynamic ring or the static ring makes adaptive movement, thereby greatly enhancing the sealing effect of the mechanical sealing element.
The existing mechanical sealing structure basically provides close fit force between a movable ring and a fixed ring through a spring and provides abrasion compensation, however, the structure easily loses elasticity due to long-term use of the spring element, and the sealing effect is poor.
Disclosure of Invention
In order to solve the above problem, this application provides an aviation oil is mechanical seal structure for cold machine, mainly includes:
the supporting ring is provided with an accommodating groove on the inner wall of the supporting ring facing the motor elastic shaft, the accommodating groove is formed by an L-shaped structure extending towards the motor elastic shaft, the accommodating groove comprises a top wall, a radial wall and an axial wall, the radial wall and the axial wall form the L-shaped structure, and the accommodating groove is opened at the other side symmetrical to the radial wall;
the static ring is arranged in the containing groove, a wave spring is arranged between one end of the static ring and the radial wall in the containing groove, a part of the other end of the static ring extends out of the opening of the containing groove and abuts against the movable ring, and the movable ring is arranged on the elastic shaft of the motor;
the fixed ring can be abutted to a ring surface formed by the limiting bulges in the process of compressing the wave spring.
Preferably, the stationary ring is a graphite ring.
Preferably, the moving ring and the elastic shaft of the motor are designed integrally.
Preferably, a gasket is arranged between the wave spring and the static ring, and the gasket can abut against a ring surface formed by the limiting bulge along with the static ring in the process of compressing the wave spring.
Preferably, the limit projection is provided as an annular projection extending from the inside of the stationary ring receiving groove.
Preferably, the limiting protrusion is provided in a stepped structure provided between the radial wall and the top wall in the receiving groove, wherein the stepped structure divides the support ring into a receiving groove portion having a smaller inner diameter and a receiving groove portion having a larger inner diameter, the wave spring is provided in the receiving groove portion having the smaller inner diameter, and the stationary ring is provided in the receiving groove portion having the larger inner diameter.
Preferably, an O-ring seal is disposed between the stationary ring and the axial wall of the vessel.
Preferably, the top wall of the containing groove is provided with an annular groove at a position close to the opening, a clamping ring is accommodated in the annular groove in a matching mode, and the part, protruding from the annular groove, of the clamping ring is used for limiting the containing groove where the static ring is separated from the annular groove in the axial direction.
The invention has the following advantages and effects:
(1) structure of prevention wave spring inefficacy: the limiting bulge is designed in the supporting ring, so that the end faces of the static ring and the dynamic ring can be kept to be tightly attached all the time, and the problem that the oil leakage amount exceeds the standard due to the fact that the axial stress exceeds the maximum stress of the wave spring can be prevented;
(2) wear compensation of the stationary ring: when the end surface of the static ring is abraded, the static ring makes small compensation movement along the axial direction under the action of the spring force of the wave spring.
Drawings
Fig. 1 is a schematic view of a conventional mechanical seal structure.
Fig. 2 is a schematic view of another prior art mechanical seal structure.
FIG. 3 is a schematic diagram of the mechanical seal structure for an aviation oil-cooled motor of the present application.
The device comprises a base, a support ring, a wave spring, a gasket, a support ring, a static ring, a sealing ring, a clamping ring and a movable ring, wherein the base comprises 1-the wave spring, 2-the gasket, 3-the support ring, 4-the static ring, 5-the O-shaped sealing ring, 6-the clamping ring and 7-the movable ring.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
As shown in fig. 3, the present application provides a mechanical seal structure for an aviation oil-cooled motor, which mainly includes:
the supporting ring 3 is provided with an accommodating groove on the inner wall of the supporting ring 3 facing the electric motor elastic shaft, the accommodating groove is formed by an L-shaped structure extending towards the electric motor elastic shaft, the accommodating groove comprises a top wall, and a radial wall and an axial wall which form the L-shaped structure, and the accommodating groove is opened at the other side symmetrical to the radial wall;
the static ring 4 is arranged in the containing groove, the wave spring 1 is arranged between one end of the static ring 4 and the radial wall in the containing groove, a part of the other end of the static ring 4 extends out of the opening of the containing groove and abuts against the movable ring 7, and the movable ring 7 is arranged on the elastic shaft of the motor;
wherein, be provided with spacing arch in the appearance groove, quiet ring 4 can support in the process of compression wave spring 1 connect to on the anchor ring that spacing arch formed.
This application designs spacing arch in the support ring, can guarantee that quiet ring and rotating ring terminal surface keep closely laminating constantly, can prevent again because of the axial atress surpasss the problem that the maximum atress of wave spring leads to the lubricating oil leakage volume exceeds standard.
On the other hand, this application forms the holding groove with support ring downwardly extending, simplifies support ring and quiet ring holder as an organic whole in essence, simplifies on the one hand and simplifies the generator overall structure, and on the other hand eliminates revealing that the clearance passageway between support ring and the quiet ring holder produced, saves the seal structure between support ring and the quiet ring holder.
In some alternative embodiments, the stationary ring 4 is a graphite ring. The spring force of the wave spring enables the graphite ring and the end face of the movable ring to be tightly attached, after the graphite ring is abraded, the graphite ring makes small compensating movement along the axial direction under the action of the spring force of the wave spring, the compensating and vibration absorbing effects are achieved, and the attaching degree of the sealing end face can be improved.
In some alternative embodiments, the moving loop 7 is integrally designed with the elastic shaft of the motor.
In some alternative embodiments, a washer 2 is arranged between the wave spring 1 and the stationary ring 4, and the washer 2 can abut against the ring surface formed by the limiting protrusion along with the stationary ring 4 in the process of compressing the wave spring 1.
In some alternative embodiments, the stop lug is provided as an annular lug extending from the inside of the groove of the stationary ring 4.
In some alternative embodiments, the limiting protrusions are provided in a stepped structure provided between the radial wall and the top wall in the receiving groove, wherein the stepped structure divides the support ring 3 into a receiving groove portion with a smaller inner diameter and a receiving groove portion with a larger inner diameter, the wave spring 1 is provided in the receiving groove portion with the smaller inner diameter, and the stationary ring 4 is provided in the receiving groove portion with the larger inner diameter.
As shown in fig. 3, the stepped structure includes a lower end surface extending in the axial direction (rightward) from the radial wall, and a side end surface extending in the radial direction (upward) from the end of the lower end surface, wherein the inner diameter of the lower end surface is larger than the outer diameter of the wave spring 1 but smaller than the outer diameter of the support ring 3 or the washer 2, so that the distance of the lower end surface in the axial direction provides a minimum storage space for the wave spring, i.e., when the wave spring is compressed to the maximum, it can still be located in the corresponding groove-containing space of the lower end surface, preventing the spring from being compressed due to the large-scale movement of the elastic shaft in the axial direction, and causing the spring to fail.
In some alternative embodiments, an O-ring seal 5 is provided between the stationary ring 2 and the axial wall of the vessel.
In some alternative embodiments, the top wall of the groove is provided with an annular groove near the opening, a clamping ring 6 is accommodated in the annular groove, and the part of the clamping ring 6 protruding from the annular groove is used for limiting the groove where the static ring 4 is separated along the axial direction.
The invention provides a mechanical sealing structure which is suitable for an aviation oil-cooled generator and has the advantages of long-time use, compact structure, suitability for axial movement and the like. This structure has three advantages: (1) the arrangement of a failure prevention structure of the wave spring prevents the wave spring from failing due to the fact that the axial abnormal stress is larger than the maximum stress of the wave spring; (2) the static ring support and the support ring are integrated, so that the structure is simplified, and vibration is reduced; (3) the wave spring provides external force to the quiet ring, makes its top support at the rotating ring terminal surface, keeps closely laminating, and wave spring's setting can be so that move, quiet ring contact tip face after by wearing and tearing, can promote quiet ring along axial displacement, keeps closely laminating all the time. The structure has stronger adaptability, and can be properly modified on the original basis to be suitable for various occasions.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (8)
1. The utility model provides an aviation oil is mechanical seal structure for cold motor which characterized in that includes:
the supporting circuit comprises a supporting ring (3), wherein an accommodating groove is formed in the inner wall, facing a motor elastic shaft, of the supporting ring (3), the accommodating groove is formed by an L-shaped structure extending towards the motor elastic shaft, the accommodating groove comprises a top wall, a radial wall and an axial wall, the radial wall and the axial wall form the L-shaped structure, and the accommodating groove is opened at the other side symmetrical to the radial wall;
the static ring (4) is arranged in the accommodating groove, a wave spring (1) is arranged between one end of the static ring (4) and a radial wall in the accommodating groove, a part of the other end of the static ring (4) extends out of an opening of the accommodating groove and abuts against a movable ring (7), and the movable ring (7) is arranged on a spring shaft of the motor;
wherein, the containing groove is internally provided with a limiting bulge, and the static ring (4) can be abutted to the ring surface formed by the limiting bulge in the process of compressing the wave spring (1).
2. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
the static ring (4) is a graphite ring.
3. The mechanical seal structure for the aviation oil-cooled motor according to claim 2, characterized in that:
the moving ring (7) and the elastic shaft of the motor are designed integrally.
4. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
the wave spring (1) and be provided with packing ring (2) between quiet ring (4), packing ring (2) along with quiet ring (4) can support to on compressing wave spring (1) the anchor ring that spacing arch formed.
5. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
the limiting protrusion is arranged as an annular protrusion extending from the inside of the containing groove of the static ring (4).
6. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
the limiting protrusions are arranged into a step structure, the step structure is arranged between the radial wall and the top wall in the containing groove, the supporting ring (3) is divided into a containing groove part with a smaller inner diameter and a containing groove part with a larger inner diameter by the step structure, the wave spring (1) is arranged in the containing groove part with the smaller inner diameter, and the static ring (4) is arranged in the containing groove part with the larger inner diameter.
7. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
an O-shaped sealing ring (5) is arranged between the static ring (2) and the axial wall of the containing groove.
8. The mechanical seal structure for the aviation oil-cooled motor according to claim 1, characterized in that:
the top wall of the containing groove is provided with an annular groove at a position close to the opening, a clamping ring (6) is accommodated in the annular groove in a matching mode, and the clamping ring (6) is used for limiting the part, protruding in the annular groove, of the static ring (4) to be separated from the containing groove along the axial direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011506402.0A CN112610697A (en) | 2020-12-18 | 2020-12-18 | Mechanical seal structure for aviation oil-cooled motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011506402.0A CN112610697A (en) | 2020-12-18 | 2020-12-18 | Mechanical seal structure for aviation oil-cooled motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112610697A true CN112610697A (en) | 2021-04-06 |
Family
ID=75240594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011506402.0A Pending CN112610697A (en) | 2020-12-18 | 2020-12-18 | Mechanical seal structure for aviation oil-cooled motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112610697A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB766717A (en) * | 1954-08-20 | 1957-01-23 | Crane Packing Co | Improvements in or relating to sealing devices |
| CN203836210U (en) * | 2014-05-14 | 2014-09-17 | 宁波东联密封件有限公司 | Sealing structure of water pump |
| CN209654612U (en) * | 2019-03-19 | 2019-11-19 | 成都化新密封有限公司 | A kind of mechanical seal for high revolving speed equipment oil side |
| CN110906007A (en) * | 2019-12-08 | 2020-03-24 | 陕西航空电气有限责任公司 | Mechanical seal structure for aviation oil-cooled generator |
-
2020
- 2020-12-18 CN CN202011506402.0A patent/CN112610697A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB766717A (en) * | 1954-08-20 | 1957-01-23 | Crane Packing Co | Improvements in or relating to sealing devices |
| CN203836210U (en) * | 2014-05-14 | 2014-09-17 | 宁波东联密封件有限公司 | Sealing structure of water pump |
| CN209654612U (en) * | 2019-03-19 | 2019-11-19 | 成都化新密封有限公司 | A kind of mechanical seal for high revolving speed equipment oil side |
| CN110906007A (en) * | 2019-12-08 | 2020-03-24 | 陕西航空电气有限责任公司 | Mechanical seal structure for aviation oil-cooled generator |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20210406 |