CN113236425A - Sealing structure of bearing cavity of aero-engine - Google Patents
Sealing structure of bearing cavity of aero-engine Download PDFInfo
- Publication number
- CN113236425A CN113236425A CN202110491307.6A CN202110491307A CN113236425A CN 113236425 A CN113236425 A CN 113236425A CN 202110491307 A CN202110491307 A CN 202110491307A CN 113236425 A CN113236425 A CN 113236425A
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- China
- Prior art keywords
- sealing
- mounting edge
- shell
- seal
- bearing cavity
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- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
- F01D25/186—Sealing means for sliding contact bearing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Devices (AREA)
- Sealing Of Bearings (AREA)
Abstract
The application provides an aeroengine bearing chamber seal structure includes: the bearing, the distance sleeve and the sealing track are arranged on the rotating shaft; a central transmission shell mounting edge matched with the bearing through a connecting piece; the sealing device is arranged on the outer side of the sealing runway; one end of the sealing shell is connected with the mounting edge of the intermediary casing, and the other end of the sealing shell is connected with the sealing device; the main body part of the sealing shell is in fillet or obtuse angle transition, an air guide channel is arranged along the main body part of the sealing shell, one end of the air guide channel is communicated with an air inlet on the mounting edge of the central transmission shell through a vent pipe mounted in the mounting edge of the intermediate casing, and the other end of the air guide channel is communicated to the end face of the sealing runway through a sealing device. The utility model provides an aeroengine bearing chamber seal structure sets the great fillet transition through the turning with seal housing, can reduce sealed bleed pressure loss to guarantee the bearing chamber effect of obturating effectively.
Description
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to an aero-engine bearing cavity sealing structure.
Background
As shown in fig. 1, the seal housing 11 is a support member of the main shaft seal device of the aircraft engine, and provides a mounting edge interface for connecting components such as the seal device. The lubricating oil cavity 13 is isolated from an external air cavity by a sealing shell of a bearing cavity of the aeroengine, so that the purpose of sealing the lubricating oil cavity 13 is achieved, a sealing air-entraining channel is generally integrated in the sealing shell 11, and meanwhile, the inner wall surface 12 of the sealing shell 11 is an important oil return channel for cooling and lubricating oil for a rotating part of the bearing cavity. The structure of the seal housing 11 directly affects the performance of the bearings, seals and overall engine.
In the prior art, the sealing shell 11 is usually in right-angle connection at the connection position, the inner wall surface 12 has a small-angle inclined wall, the outer wall surface has no inclined wall, the right side of the sealing shell is provided with a clamping ring groove, and the sealing shell and the sealing device 15 are positioned through a clamping ring 14.
However, the sealing shell of the existing structure has poor oil return capacity, the sealing bleed air pressure loss of the bleed air channel in the sealing shell is large, the assembly and the disassembly of the retainer ring 14 are difficult, the maintainability is poor, and the axial positioning is unstable.
Disclosure of Invention
It is an object of the present application to provide an aeroengine bearing cavity seal arrangement to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: an aeroengine bearing cavity seal structure comprising:
the bearing, the distance sleeve and the sealing track are arranged on the rotating shaft;
a central transmission shell mounting edge matched with the bearing through a connecting piece;
the sealing device is arranged on the outer side of the sealing runway; and
one end of the sealing shell is connected with the mounting edge of the intermediary casing, and the other end of the sealing shell is connected with the sealing device;
the main body part of the sealing shell is in fillet or obtuse angle transition, an air guide channel is arranged along the main body part of the sealing shell, one end of the air guide channel is communicated with an air inlet on the mounting edge of the central transmission shell through a vent pipe mounted in the mounting edge of the intermediate casing, and the other end of the air guide channel is communicated to the end face of the sealing runway through a sealing device and used for sealing.
In the preferred embodiment of the present application, the rounded or obtuse angle of the seal housing body portion is preferably as large as the structure allows.
Furthermore, a first sealing ring is arranged at the connecting part of the vent pipe, the central transmission shell mounting edge and the sealing shell.
Furthermore, a second sealing ring is arranged at the connecting part of the sealing shell and the mounting edge of the intermediate casing.
Furthermore, a third sealing ring is arranged at the connecting part of the sealing shell and the sealing device.
Furthermore, a fourth sealing ring is arranged at the connecting part of the sealing runway and the rotating shaft.
Further, the sealing shell and the sealing device are fixedly connected through a connecting piece arranged in the axial direction.
The utility model provides an aeroengine bearing chamber seal structure sets big fillet transition through the turning with seal housing, can reduce sealed bleed pressure loss, thereby guarantee the bearing chamber effect of obturating effectively, can also effectively guarantee in addition that the oil return of lubricating oil along the skew wall flows unobstructed, can not produce the lubricating oil and gather when the lubricating oil is more in the bearing chamber, guarantee the lubricated cooling effect of rotatory heat generation spare such as bearing sealing device, improve the performance and the life-span of high-speed rotating member.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of a prior art aeroengine bearing cavity seal structure.
FIG. 2 is a schematic view of an aircraft engine bearing cavity seal arrangement of the present application.
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 drawings in the embodiments of the present application.
In order to overcome the sealed bleed air pressure reduction, the smooth and easy scheduling problem of lubricating oil backward flow that the bearing chamber seal structure among the prior art exists, this application provides the aeroengine bearing chamber seal structure of a novel structure.
As shown in fig. 2, the aeroengine bearing cavity sealing structure provided by the present application includes: the rotary shaft 21, the bearing 22, the central transmission shell installation edge 23, the vent pipe 24, the sealing shell 25, the intermediate casing installation edge 26, the distance sleeve 27, the sealing runway 28 and the sealing device 29. The bearing 22, distance sleeve 27 and sealing track 28 are mounted on the shaft 21. The bearing 22 (or mounting edge of the bearing mount) is mounted on the central drive housing mounting edge 23 by a bolt connection assembly 311. The sealing device 29 is arranged on the outer side of the sealing track 28 with a small gap, the sealing device 29 is mounted on the sealing shell 25 through a screw assembly 313, the other end of the sealing shell 25 is connected or overlapped with the intermediate mounting edge 26, and the intermediate mounting edge 26 is connected with the central transmission shell mounting edge 23 through a bolt connection assembly 312. Wherein, the main body of the sealing housing 25 is in a round angle or obtuse angle transition, and has an air guiding channel 251 along the extending direction of the main body of the sealing housing 25, one end of the air guiding channel 251 is connected to the air inlet on the central transmission housing mounting edge 23 through the air pipe 24 installed in the intermediate casing mounting edge 26, and the other end of the air channel 251 is connected to the end surface of the sealing runway 28 through the sealing device 29
The sealing gas flowing in from the air inlet of the central transmission housing mounting edge 23 seals the end surface of the runway 28 along the vent pipe 24, the air guide channel 251 of the sealing housing 25 and the flow channel of the sealing device 29, so that the oil side and the air side of the bearing cavity are isolated, and the sealing of the bearing cavity is realized.
In the preferred embodiment of the application, the fillet or obtuse structural parameter of the main body part of the sealing shell (25) is as large as possible, so that the loss of the bleed air pressure can be reduced as much as possible, and the lubricating oil in the bearing cavity can return along the inner wall of the sealing shell 25, thereby improving the oil return effect.
In some preferred embodiments of the present application, a first sealing ring 321 is provided at the connection portion of the vent pipe 24, the central transmission housing mounting edge 23 and the seal housing 25, and the first sealing ring 321 is used for realizing air passage sealing. A second sealing ring 322 is arranged at the connecting part of the sealing shell 25 and the intermediate casing mounting edge 26, a third sealing ring 323 is arranged at the connecting part of the sealing shell 25 and the sealing device 29, a fourth sealing ring 324 is arranged at the connecting part of the sealing runway 27 and the rotating shaft 21, and the second sealing ring 322, the third sealing ring 323 and the fourth sealing ring 324 are used for realizing oil path sealing.
Finally, in the present application, the seal housing 25 and the seal 29 can be fixedly connected by an axially arranged connection, so that maintenance is improved.
The sealing structure of the bearing cavity of the aero-engine has the following advantages:
1) aiming at the defects of the prior art, the transfer section of the sealing shell 25 is changed into large fillet or chamfer angle transfer from right angle transfer, so that the loss of sealing bleed pressure is greatly reduced, and the sealing effect of the bearing cavity can be effectively ensured;
2) because the lubricating oil for lubricating and cooling the bearing 22 and the sealing runway 28 is accumulated in the oil return channel/oil return cavity, when the lubricating oil flows to the oil return low point through the inner wall surface of the sealing shell 25, the inner wall surface of the sealing shell 25 is a large-angle inclined wall by adopting the design of the sealing shell 25, so that smooth oil return flow of the lubricating oil along the inclined wall can be effectively ensured, the lubricating oil accumulation cannot be generated when the lubricating oil in the bearing cavity is more, the lubricating and cooling effects of rotary heat-generating parts such as the bearing, a sealing device and the like are ensured, and the service performance and the service life of a high-speed rotary part are improved;
3) through screw assembly location and connection between sealing device and the seal housing, compare current rand location structure, axial positioning is more stable, guarantees the axial positioning effect, and the assembly decomposes easily, and the maintainability is showing and is improving.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. An aeroengine bearing cavity seal structure, characterized by, includes:
a bearing (22), a distance sleeve (27) and a sealing track (28) which are arranged on the rotating shaft (21);
a central transmission housing mounting edge (23) which is matched with the bearing (22) through a connecting piece;
a sealing device (29) arranged outside the sealing track (28); and
a sealing shell (25) with one end connected with the intermediate casing mounting edge (26) and the other end connected with a sealing device (29);
the main body part of the sealing shell (25) is in round angle or obtuse angle transition, an air guide channel (251) is arranged along the main body part of the sealing shell (25), one end of the air guide channel (251) is communicated with an air inlet on the central transmission shell mounting edge (23) through a vent pipe (24) mounted in the intermediate casing mounting edge (26), and the other end of the air channel (251) is communicated to the end face of the sealing runway (28) through a sealing device (29) for sealing.
2. The aeroengine bearing cavity seal structure of claim 1, wherein the fillet or obtuse angle of the seal housing (25) body portion is of greater dimension to the extent structurally permissible as well.
3. The aeroengine bearing cavity seal structure of claim 1, wherein the connection of said vent tube (24) to the central transmission housing mounting edge (23) and the seal housing (25) is provided with a first seal ring (321).
4. The aeroengine bearing cavity seal structure of claim 1, wherein a second seal ring (322) is provided at a connection portion of said seal housing (25) and said intermediate casing mounting edge (26).
5. The aeroengine bearing cavity sealing structure of claim 1, wherein a third sealing ring (323) is provided at a connecting portion of the seal housing (25) and the sealing device (29).
6. The aeroengine bearing cavity sealing structure according to claim 1, characterized in that a fourth sealing ring (324) is arranged at the connecting part of the sealing runway (27) and the rotating shaft (21).
7. An aeroengine bearing cavity seal according to any one of claims 1 to 6, wherein said seal housing (25) is fixedly connected to said seal means (29) by an axially disposed connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491307.6A CN113236425A (en) | 2021-05-06 | 2021-05-06 | Sealing structure of bearing cavity of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491307.6A CN113236425A (en) | 2021-05-06 | 2021-05-06 | Sealing structure of bearing cavity of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113236425A true CN113236425A (en) | 2021-08-10 |
Family
ID=77132093
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110491307.6A Pending CN113236425A (en) | 2021-05-06 | 2021-05-06 | Sealing structure of bearing cavity of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113236425A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114738120A (en) * | 2022-04-18 | 2022-07-12 | 中国航发沈阳发动机研究所 | Aeroengine bearing cavity sealing and air entraining structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203614232U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Peripheral sealing cooling structure and aero-engine |
| US20140144121A1 (en) * | 2012-11-28 | 2014-05-29 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing oil leak recuperation system |
| CN106224100A (en) * | 2016-09-02 | 2016-12-14 | 中国科学院工程热物理研究所 | The collar |
| CN106838010A (en) * | 2017-02-08 | 2017-06-13 | 中国航发沈阳发动机研究所 | The base bearing holding meanss component and aero-engine of a kind of aero-engine |
| CN107084845A (en) * | 2017-04-21 | 2017-08-22 | 中国航发沈阳发动机研究所 | A kind of bearing bore of aero-engine high supercharging pressure level Fan Rig obturages system |
-
2021
- 2021-05-06 CN CN202110491307.6A patent/CN113236425A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140144121A1 (en) * | 2012-11-28 | 2014-05-29 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing oil leak recuperation system |
| CN203614232U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Peripheral sealing cooling structure and aero-engine |
| CN106224100A (en) * | 2016-09-02 | 2016-12-14 | 中国科学院工程热物理研究所 | The collar |
| CN106838010A (en) * | 2017-02-08 | 2017-06-13 | 中国航发沈阳发动机研究所 | The base bearing holding meanss component and aero-engine of a kind of aero-engine |
| CN107084845A (en) * | 2017-04-21 | 2017-08-22 | 中国航发沈阳发动机研究所 | A kind of bearing bore of aero-engine high supercharging pressure level Fan Rig obturages system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114738120A (en) * | 2022-04-18 | 2022-07-12 | 中国航发沈阳发动机研究所 | Aeroengine bearing cavity sealing and air entraining structure |
| CN114738120B (en) * | 2022-04-18 | 2024-01-30 | 中国航发沈阳发动机研究所 | Aeroengine bearing cavity sealing air-entraining structure |
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| PB01 | Publication | ||
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Application publication date: 20210810 |