CN112797079B - Oil deflector ring in airplane wheel and oil deflector ring assembly thereof - Google Patents
Oil deflector ring in airplane wheel and oil deflector ring assembly thereof Download PDFInfo
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- CN112797079B CN112797079B CN202110126024.1A CN202110126024A CN112797079B CN 112797079 B CN112797079 B CN 112797079B CN 202110126024 A CN202110126024 A CN 202110126024A CN 112797079 B CN112797079 B CN 112797079B
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- ring
- wheel
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- sealing ring
- static
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/72—Sealings
- F16C33/76—Sealings of ball or roller bearings
- F16C33/78—Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members
- F16C33/7803—Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members suited for particular types of rolling bearings
- F16C33/7813—Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members suited for particular types of rolling bearings for tapered roller bearings
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/72—Sealings
- F16C33/76—Sealings of ball or roller bearings
- F16C33/78—Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members
- F16C33/7816—Details of the sealing or parts thereof, e.g. geometry, material
- F16C33/782—Details of the sealing or parts thereof, e.g. geometry, material of the sealing region
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/72—Sealings
- F16C33/76—Sealings of ball or roller bearings
- F16C33/78—Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members
- F16C33/7816—Details of the sealing or parts thereof, e.g. geometry, material
- F16C33/783—Details of the sealing or parts thereof, e.g. geometry, material of the mounting region
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/72—Sealings
- F16C33/76—Sealings of ball or roller bearings
- F16C33/80—Labyrinth sealings
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- 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
- F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
- F16J9/12—Details
- F16J9/20—Rings with special cross-section; Oil-scraping rings
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- 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
- F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
- F16J9/26—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction characterised by the use of particular materials
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention discloses an oil deflector ring in an airplane wheel of an airplane and an oil deflector ring assembly thereof, wherein the oil deflector ring comprises a metal skeleton ring, a movable sealing ring and a static sealing ring, the movable sealing ring is detachably arranged on the outer diameter side of the metal skeleton ring, and the static sealing ring is detachably arranged on the outer end face of the metal skeleton ring; the dynamic seal ring is in dynamic seal with the inner diameter side of the airplane wheel, and the static seal ring is in static seal with the bearing inner ring of the tapered roller bearing; the oil retainer ring assembly comprises an inner oil retainer ring and an outer oil retainer ring, and the inner oil retainer ring and the outer oil retainer ring are respectively arranged on the inner side and the outer side of the tapered roller bearing; according to the invention, the movable sealing ring and the static sealing ring are detachably arranged on the metal framework ring, the movable sealing ring realizes the movable sealing with the inner diameter side of the airplane wheel, the static sealing ring realizes the static sealing with the inner ring of the tapered roller bearing, and the static sealing ring and the movable sealing ring can adopt different structures or materials, so that a better sealing effect is achieved.
Description
Technical Field
The invention relates to the field of airplane wheels, in particular to an oil retainer ring in an airplane wheel and an oil retainer ring assembly thereof.
Background
A tapered roller bearing is arranged between the airplane wheel and the landing gear shaft, and the relative rotation of the airplane wheel and the landing gear shaft is realized through the tapered roller bearing. The tapered roller bearing can be divided into an outer ring and an inner ring, a roller and a retainer are arranged between the outer ring and the inner ring, the roller and the retainer are integrated into a whole, so that the tapered roller bearing is convenient to mount and dismount; the outer ring is mounted in the wheel bearing bore by interference fit and the inner ring is mounted on the landing gear shaft, i.e. when rotating, the outer ring and the wheel rotate while the inner ring and the landing gear shaft do not rotate.
When the tapered roller bearing is used, a large amount of grease (3/4 for a bearing clearance) needs to be applied. When the airplane wheel rotates at a high speed, the lubricating grease can be thrown out to the outer side and the inner side due to the action of centrifugal force; when the lubricating grease of the tapered roller bearing is reduced, the roller is in direct contact with the rolling surfaces of the inner ring and the outer ring, the contact surface becomes rough after long-term use, the roller and the rolling surface are abraded, rust spots are formed after abrasion, the bearing capacity and the service life of the bearing are influenced, and the roller is separated from the retainer when serious, so that the wheel loses the rotation capacity. At present, the outer oil retaining ring is basically installed on the airplane, but the inner oil retaining ring is not installed on some airplane wheels, because the grease thrown inwards is only discovered when the airplane is disassembled and assembled, or because the grease thrown inwards is not much, the attention is not paid.
The application publication number is CN 102966672A's chinese patent discloses an oil slinger subassembly of aircraft wheel, interior oil slinger is located the one end of wheel hub bearing, in the recess on interior oil slinger embedding wheel hub inner wall, realize that this interior oil slinger is along aircraft wheel axial and annular fixed, prevent the interior lubricating grease of hub bearing through interior oil slinger and flow out, however, the interior oil slinger in this scheme does not distinguish static seal structure and moving seal structure, do not have corresponding setting that carries out moving seal and static seal yet, sealed effect is not good.
Disclosure of Invention
The invention aims to provide an oil retainer ring in an airplane wheel of an airplane and an oil retainer ring assembly thereof, which are used for solving the problems in the prior art.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides an oil retainer ring in an airplane wheel of an airplane, which comprises a metal framework ring, a movable sealing ring and a static sealing ring, wherein the movable sealing ring is detachably arranged on the outer diameter side of the metal framework ring; the dynamic seal ring is dynamically sealed with the inner diameter side of the airplane wheel, and the static seal ring is statically sealed with the bearing inner ring of the tapered roller bearing.
Preferably, the metal framework ring is provided with a mounting hole and an annular mounting groove; the movable sealing ring is provided with a plurality of radially extending mounting columns along the circumferential direction, and the mounting columns are mounted in the mounting holes; the static sealing ring is arranged in the annular mounting groove.
Preferably, the metal skeleton ring comprises an axial boss and a radial flange, the annular mounting groove is arranged on the axial boss, and the mounting hole is arranged on the radial flange; the movable sealing ring is provided with an axial groove, and the mounting column is arranged on the inner bottom surface of the groove.
Preferably, the end part of the outer diameter side of the dynamic sealing ring is provided with a guide angle which is 20-30 degrees.
Preferably, the dynamic seal ring is attached to the metal skeleton ring by vulcanization.
Preferably, the outer diameter side of the dynamic seal ring is provided with a spiral labyrinth groove, and the spiral direction of the spiral labyrinth groove is opposite to the rotation direction of the wheel.
Preferably, the dynamic seal ring is provided with a backflow hole communicated with the spiral labyrinth groove, and the backflow hole is communicated to one side of the tapered roller bearing.
The invention also provides an airplane wheel oil retainer ring assembly, which comprises the airplane wheel inner oil retainer ring and an outer oil retainer ring, wherein the inner oil retainer ring and the outer oil retainer ring are respectively arranged on the inner side and the outer side of the tapered roller bearing.
Preferably, the outer diameter of the metal skeleton ring is smaller than the minimum inner diameter of a bearing outer ring of the tapered roller bearing.
Preferably, an axial inner end face of the inner oil deflector ring is provided with a spacing bush assembly which abuts against the metal skeleton ring.
Compared with the prior art, the invention has the following technical effects:
(1) according to the invention, the movable sealing ring and the static sealing ring are detachably arranged on the metal framework ring, the movable sealing ring is used for realizing the movable sealing with the inner diameter side of the airplane wheel, the static sealing ring is used for realizing the static sealing with the inner ring of the tapered roller bearing, the static sealing ring and the movable sealing ring can adopt different structures or materials, so that a better sealing effect is achieved, and the metal framework ring is used for supporting, so that the bonding effect of the movable sealing ring and the static sealing ring can be further improved, and the sealing effect is further improved;
(2) the movable sealing ring is arranged in the mounting hole in the metal framework ring through the mounting column, and the movable sealing ring and the inner diameter side of the airplane wheel rotate relatively, so that the movable sealing ring can be limited by the structures of the mounting column and the mounting hole, and the movable sealing ring is prevented from rotating together with the airplane wheel, and the movable sealing effect is ensured; the static sealing ring is arranged in an annular mounting groove on the metal framework ring, and the static sealing ring and the bearing inner ring of the tapered roller bearing are extruded and static to realize static sealing, so that the annular mounting groove can limit the further deformation of the static sealing ring, the extrusion contact effect with the bearing inner ring is improved, and the static sealing effect is further improved;
(3) according to the invention, a lubricating grease containing cavity for storing lubricating grease can be formed among the axial boss and the radial flange of the metal framework ring and the groove of the dynamic sealing ring, so that even if a small amount of lubricating grease is lost, the supply of the lubricating grease can be ensured when the tapered roller bearing rotates, and the lubricating effect of the tapered roller bearing can be further ensured;
(4) according to the invention, the spiral labyrinth grooves and the backflow holes on the dynamic seal ring can enable the lubricating grease to be thrown back or flow back into the lubricating grease space of the tapered roller bearing, namely, the lubricating grease is provided with power flowing to the lubricating grease space, so that the loss of the lubricating grease can be better avoided, and the lubricating effect of the tapered roller bearing is ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of the overall mounting structure of the present invention;
FIG. 2 is a partial view of I of FIG. 1;
FIG. 3 is a schematic view of the structure of an internal oil deflector ring;
FIG. 4 is a cross-sectional view A-A of FIG. 3;
FIG. 5 is a schematic structural view of a dynamic seal ring;
FIG. 6 is a cross-sectional view taken along line A-A of FIG. 5;
FIG. 7 is a schematic view of a metal cage ring structure;
FIG. 8 is a cross-sectional view taken along line A-A of FIG. 7;
FIG. 9 is a schematic structural view of a static seal ring;
wherein, 1, a wheel; 2. a bearing outer ring; 3. an outer oil deflector ring; 4. a bearing inner ring; 5. an inner oil retainer ring; 51. a movable sealing ring; 511. a spiral labyrinth groove; 512. a return orifice; 513. mounting a column; 514. a lead-in angle; 52. a metal skeleton ring; 521. mounting holes; 522. an axial boss; 523. an annular mounting groove; 524. a radial flange; 53. and a static sealing ring.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an oil deflector ring in an airplane wheel of an airplane and an oil deflector ring assembly thereof, aiming at solving the problems in the prior art, a movable sealing ring and a static sealing ring are detachably arranged on a metal framework ring, the movable sealing ring realizes the movable sealing with the inner diameter side of the airplane wheel, the static sealing ring realizes the static sealing with the inner ring of a tapered roller bearing, and the static sealing ring and the movable sealing ring can adopt different structures or materials to achieve better sealing effect.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 1 to 4, the present invention provides an internal oil slinger 5 for an airplane wheel, wherein the internal oil slinger 5 is installed on the inner side of a tapered roller bearing, namely, in the direction close to the airplane wheel 1, for baffling grease lubricating the tapered roller bearing from being thrown to the inner side; the inner oil retainer ring 5 comprises a metal skeleton ring 52, a dynamic seal ring 51 and a static seal ring 53, wherein the metal skeleton ring 52 can be made of 20# steel and mainly plays a supporting role, and the dynamic seal ring 51 and the static seal ring 53 play a dynamic seal and static seal role; the movable sealing ring 51 is annular, the material of the movable sealing ring 51 can be 5080 rubber which is wear-resistant and has enough elasticity, the movable sealing ring 51 can be detachably arranged on the outer diameter side of the metal framework ring 52, the detachable mode refers to that different component assembling modes are adopted due to different materials of the movable sealing ring 51 and the metal framework ring 52, specifically, the detachable mode can be a clamping connection mode, an adhesion mode, a vulcanization mode or a combination mode of the clamping connection mode, the adhesion mode and the vulcanization mode, in addition, the movable sealing ring 51 is arranged on the outer diameter side of the metal framework ring 52 and is not connected on the outer diameter side, the movable sealing ring 51 can play a role on the outer diameter side of the metal framework ring 52 after being connected, and the connecting position can be on the outer diameter or the end surface; the static seal ring 53 is detachably arranged on the outer end face of the metal framework ring 52, wherein the outer end face refers to a direction close to the tapered roller bearing, so that the static seal ring 53 can be attached to the end face of the bearing inner ring 4 of the tapered roller bearing, the static seal ring 53 can be clamped in a groove when being installed, a shaft shoulder can also be arranged on the metal framework ring 52, and the static seal ring 53 is placed at the shaft shoulder; the dynamic sealing ring 51 and the inner diameter side of the airplane wheel 1 can be dynamically sealed through the position of the dynamic sealing ring 51 and the static sealing ring 53 which are arranged on the metal framework ring 52, and the static sealing ring 53 and the bearing inner ring 4 of the tapered roller bearing are statically sealed; the static sealing ring 53 and the dynamic sealing ring 51 can be made of different structures or materials to achieve better sealing effect.
As shown in fig. 3 to 8, the metal skeleton ring 52 is provided with a mounting hole 521 and an annular mounting groove 523, wherein the mounting hole 521 may be radially or axially disposed and needs to be installed in cooperation with the dynamic seal ring 51, and a plurality of mounting holes 521 may be circumferentially disposed to ensure firm installation; the dynamic seal ring 51 is provided with a plurality of mounting columns 513 extending in the radial direction along the circumferential direction, the mounting columns 513 are mounted in the mounting holes 521, at the moment, the mounting holes 821 are arranged in the axial direction, the length of the mounting columns 513 can be equal to the depth of the mounting holes 521, and the dynamic seal ring 51 can be limited by the structures of the mounting columns 513 and the mounting holes 521 due to the relative rotation between the dynamic seal ring 51 and the inner diameter side of the wheel 1, so that the dynamic seal ring 51 is prevented from rotating together with the wheel 1, and the dynamic sealing effect is ensured; the static sealing ring 53 can be a conventional O-shaped sealing ring made of 5080 rubber, the compression rate is about 20%, the static sealing ring is installed in the annular installation groove 523, static sealing is realized by the static extrusion of the static sealing ring 53 and the bearing inner ring 4 of the tapered roller bearing, and the annular installation groove 523 can limit further deformation of the static sealing ring 53, so that the extrusion contact effect with the bearing inner ring 4 is improved, and the static sealing effect is further improved.
As shown in fig. 5 to 8, the metal skeleton ring 52 may include an axial boss 522 and a radial flange 524, the axial cross section of the metal skeleton ring 52 is T-shaped, an annular mounting groove 523 is disposed on the axial boss 522 and is capable of clamping the static seal ring 53, and the depth of the annular mounting groove 523 is smaller than the width of the static seal ring 53, so that the static seal ring 53 can be attached to the bearing inner ring 4 after being mounted; the mounting hole 521 is arranged on the radial flange 524, and the mounting hole 521 is arranged along the circumferential direction and is axially opened; the movable sealing ring 51 is provided with an axial groove, the mounting column 513 is arranged on the inner bottom surface of the groove, the axial section of the movable sealing ring 51 is also T-shaped, and after the movable sealing ring is mounted on the metal framework ring 52, a lubricating grease containing cavity for storing lubricating grease can be formed among the axial boss 522, the radial flange 524 and the groove of the movable sealing ring 51 of the metal framework ring 52, so that even if a small amount of lubricating grease is lost, the supply of the lubricating grease can be ensured when the tapered roller bearing rotates, and the lubricating effect of the tapered roller bearing can be further ensured.
As shown in fig. 6, the end of the dynamic seal ring 51 on the outer diameter side is provided with a lead-in angle 514, the lead-in angle 514 is 20 to 30 degrees, and the dynamic seal ring 51 can be conveniently mounted and dismounted on the inner diameter side of the wheel 1.
The movable seal ring 51 is mounted in the mounting hole 521 through the mounting column 513 to connect the movable seal ring 51 and the metal skeleton ring 52, and is further attached to the metal skeleton ring 52 through vulcanization, so that the mounting and fixing effects are further improved, and the movable seal ring 51 is prevented from falling off from the metal skeleton ring 52 after long-term operation.
As shown in fig. 5 to 6, the outer diameter side of the dynamic seal 51 may be provided with a spiral labyrinth groove 511 having a spiral direction opposite to the rotation direction of the wheel 1, and the spiral labyrinth groove 511 of the dynamic seal 51 may be provided with two turns having a spiral direction opposite to the rotation direction of the wheel 1, so that when the wheel 1 rotates, grease is prevented from being thrown into the inner side of the wheel 1, and grease accumulated in the spiral labyrinth groove 511 can be thrown back into the grease reservoir.
Furthermore, the dynamic seal ring 51 may further be provided with a backflow hole 512 communicating with the spiral labyrinth groove 511, and the backflow hole 512 leads to one side of the tapered roller bearing, so that the grease accumulated in the spiral labyrinth groove 511 can be more easily thrown back to the grease accommodating chamber.
As shown in fig. 1-2, the invention further provides an aircraft wheel retainer oil ring assembly, which comprises the aforementioned inner oil retainer ring 5 and an outer oil retainer ring 3, wherein the outer oil retainer ring 3 can adopt the existing conventional outer oil retainer ring 3 and is fixedly installed through a retainer ring, the inner oil retainer ring 5 and the outer oil retainer ring 3 are respectively arranged on the inner side and the outer side of the tapered roller bearing, wherein the outer diameter of a movable seal ring 51 of the inner oil retainer ring 5 is matched with the inner diameter of the aircraft wheel 1, and a rotary seal can be formed by clearance fit or interference fit, so that lubricating grease is prevented from flowing out from a gap between the inner cavity of the aircraft wheel 1 and the inner oil retainer ring 5; when the clearance fit is adopted, the clearance between the outer diameter of the movable sealing ring 51 and the inner diameter of the airplane wheel 1 is 0.1-0.3 mm; when the interference fit is adopted, the clearance between the outer diameter of the dynamic seal ring 51 and the inner diameter of the airplane wheel 1 is 0.2 mm-0.3 mm, and the dynamic seal ring 51 needs to have certain wear resistance; therefore, the oil slinger assembly can prevent the lubricating grease from being thrown to the inner side of the wheel 1 and the outer side of the wheel 1, and in short, the lubricating grease can be stored and applied in the tapered roller bearing or the lubricating grease accommodating cavity so as to ensure the lubricating effect on the tapered roller bearing.
When the inner oil retainer ring 5 is installed, the bearing outer ring 2 of the tapered roller bearing is installed in the airplane wheel 1, and the inner oil retainer ring 5 can enter the inner diameter side of the airplane wheel 1 only after penetrating through the bearing outer ring 2; in order to facilitate the disassembly of the bearing outer ring 2, the inner diameter of the airplane wheel 1 is larger than the minimum inner diameter of the bearing outer ring 2; however, the outer diameter of the inner oil retainer ring 5 is equivalent to the inner diameter of the wheel 1, so that the movable seal ring 51 has a certain deformation when the inner oil retainer ring 5 is installed, and after the installation is completed, the movable seal ring 51 of the inner oil retainer ring 5 has elasticity and can bear a certain deformation, so that the initial shape can be restored after the installation is completed, and it should be noted that the outer diameter of the metal skeleton ring 52 is smaller than the minimum inner diameter of the bearing outer ring 2 of the tapered roller bearing, otherwise, the inner oil retainer ring 5 cannot be installed after the bearing outer ring 2 is installed because the metal skeleton ring 52 is not easily deformed.
The inner end face of the inner oil retainer ring 5 in the axial direction is provided with a spacing bush assembly 6, the spacing bush assembly 6 abuts against the metal skeleton ring 52, the metal skeleton ring 52 is fixed through the spacing bush assembly 6, and then the inner oil retainer ring 5 is axially compressed and fixed.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (7)
1. The utility model provides an aircraft wheel inner oil scraper ring which characterized in that: the movable sealing ring is detachably arranged on the outer diameter side of the metal framework ring, and the static sealing ring is detachably arranged on the outer end face of the metal framework ring; the dynamic seal ring is in dynamic seal with the inner diameter side of the airplane wheel, and the static seal ring is in static seal with the bearing inner ring of the tapered roller bearing; the metal framework ring is provided with a mounting hole and an annular mounting groove; the movable sealing ring is provided with a plurality of radially extending mounting columns along the circumferential direction, and the mounting columns are mounted in the mounting holes; the static sealing ring is arranged in the annular mounting groove; the metal framework ring comprises an axial boss and a radial flange, the annular mounting groove is arranged on the axial boss, and the mounting hole is arranged on the radial flange; the movable sealing ring is provided with an axial groove, and the mounting column is arranged on the inner bottom surface of the groove; the end part of the outer diameter side of the dynamic sealing ring is provided with a guide angle which is 20-30 degrees.
2. An aircraft in-wheel oil deflector ring according to claim 1, characterized in that: the dynamic seal ring is attached to the metal skeleton ring through vulcanization.
3. An aircraft in-wheel oil deflector ring according to claim 2, characterized in that: and a spiral labyrinth groove is arranged on the outer diameter side of the dynamic seal ring, and the spiral direction of the spiral labyrinth groove is opposite to the rotating direction of the airplane wheel.
4. An aircraft in-wheel oil deflector ring according to claim 3, characterized in that: and the dynamic seal ring is provided with a backflow hole communicated with the spiral labyrinth groove, and the backflow hole is communicated to one side of the tapered roller bearing.
5. The utility model provides an aircraft wheel fender oil ring subassembly which characterized in that: the airplane wheel inner oil retainer ring of any one of claims 1 to 4 is included, and further comprises an outer oil retainer ring, wherein the inner oil retainer ring and the outer oil retainer ring are respectively arranged on the inner side and the outer side of the tapered roller bearing.
6. An aircraft wheel splash ring assembly as claimed in claim 5, wherein: the outer diameter of the metal skeleton ring is smaller than the minimum inner diameter of a bearing outer ring of the tapered roller bearing.
7. An aircraft wheel splash ring assembly as claimed in claim 6, wherein: and the axial inner end face of the inner oil retainer ring is provided with a spacing bush assembly which is abutted against the metal framework ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110126024.1A CN112797079B (en) | 2021-01-29 | 2021-01-29 | Oil deflector ring in airplane wheel and oil deflector ring assembly thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110126024.1A CN112797079B (en) | 2021-01-29 | 2021-01-29 | Oil deflector ring in airplane wheel and oil deflector ring assembly thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112797079A CN112797079A (en) | 2021-05-14 |
| CN112797079B true CN112797079B (en) | 2022-06-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110126024.1A Active CN112797079B (en) | 2021-01-29 | 2021-01-29 | Oil deflector ring in airplane wheel and oil deflector ring assembly thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112797079B (en) |
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|---|---|---|---|---|
| US5044782A (en) * | 1990-09-14 | 1991-09-03 | Allied-Signal Inc. | Sealed tapered roller bearing assembly for aircraft wheel bearing system |
| US5711616A (en) * | 1995-04-10 | 1998-01-27 | The Timken Company | Bearing seal for providing static and dynamic barriers |
| CN201110379Y (en) * | 2007-12-05 | 2008-09-03 | 孙乐宁 | Combined oil seal for rotational shaft |
| CN102628338A (en) * | 2011-06-20 | 2012-08-08 | 成都盛帮密封件股份有限公司 | Novel roller bit sealing ring |
| CN102966672A (en) * | 2012-11-28 | 2013-03-13 | 西安航空制动科技有限公司 | Oil retainer component of airplane wheel |
| CN205859103U (en) * | 2016-08-15 | 2017-01-04 | 山东黄金矿业(莱州)有限公司三山岛金矿 | The hydraulic prop chassis rock drill hermetically sealed assembly pulley of haulage cable single cavity |
| CN107327573A (en) * | 2017-08-11 | 2017-11-07 | 昆山健博密封件科技有限公司 | A kind of combined anti-dust seal device |
| CN206786003U (en) * | 2017-05-10 | 2017-12-22 | 新能能源有限公司 | A kind of shaft seal structure with quiet dynamic double containment |
-
2021
- 2021-01-29 CN CN202110126024.1A patent/CN112797079B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5044782A (en) * | 1990-09-14 | 1991-09-03 | Allied-Signal Inc. | Sealed tapered roller bearing assembly for aircraft wheel bearing system |
| US5711616A (en) * | 1995-04-10 | 1998-01-27 | The Timken Company | Bearing seal for providing static and dynamic barriers |
| CN201110379Y (en) * | 2007-12-05 | 2008-09-03 | 孙乐宁 | Combined oil seal for rotational shaft |
| CN102628338A (en) * | 2011-06-20 | 2012-08-08 | 成都盛帮密封件股份有限公司 | Novel roller bit sealing ring |
| CN102966672A (en) * | 2012-11-28 | 2013-03-13 | 西安航空制动科技有限公司 | Oil retainer component of airplane wheel |
| CN205859103U (en) * | 2016-08-15 | 2017-01-04 | 山东黄金矿业(莱州)有限公司三山岛金矿 | The hydraulic prop chassis rock drill hermetically sealed assembly pulley of haulage cable single cavity |
| CN206786003U (en) * | 2017-05-10 | 2017-12-22 | 新能能源有限公司 | A kind of shaft seal structure with quiet dynamic double containment |
| CN107327573A (en) * | 2017-08-11 | 2017-11-07 | 昆山健博密封件科技有限公司 | A kind of combined anti-dust seal device |
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