CN117967452A - Bearing cavity sealing air-entraining structure and aeroengine - Google Patents

Abstract

The invention discloses a sealing and air-entraining structure of a bearing cavity, which comprises a sealing ring casing, a bearing seat arranged in the sealing ring casing, a rotating bearing arranged in the bearing seat, a rotor assembly arranged in the sealing ring casing and a sealing comb ring sleeved outside the rotor assembly, wherein the sealing ring casing and the bearing seat are enclosed to form a first containing cavity, the sealing ring casing and the sealing comb ring are enclosed to form an air-entraining channel which is arranged opposite to the rotating bearing in the axial direction and is used for introducing sealing air, an air-inlet channel which is respectively communicated with the first containing cavity and the air-entraining channel is arranged between the sealing ring casing and the rotating bearing, the bearing seat comprises a second containing cavity which is communicated with the inner cavity of the rotating bearing and is used for containing vaporific lubricating oil, and a backflow channel which is respectively communicated with the first containing cavity and the second containing cavity, and a diversion component which is used for guiding the sealing air into the air-inlet channel is arranged at the end part, close to the rotating bearing, in the air-entraining channel.

Description

Bearing cavity sealing air-entraining structure and aeroengine

Technical Field

The invention relates to the technical field of aeroengines, in particular to a bearing cavity sealing air-entraining structure. In addition, the invention also relates to an aeroengine comprising the bearing cavity sealing air-entraining structure.

Background

The lubricating oil interruption test requirements of the aeroengine are as follows: under the condition that the main lubricating oil system is interrupted and the lubricating oil supply is carried out, the aero-engine can work for 30 seconds according to the set power, and during the period of lubricating oil interruption and the subsequent normal working period, no adverse effect is caused on the aero-engine, and under the condition that the internal bearing is not lubricated, the aero-engine can work for at least 6 minutes in a 75% maximum continuous state, and then after the internal bearing is restored to be lubricated, the aero-engine can work for 30 minutes in a 75% maximum continuous power state, and meanwhile, the internal bearing cannot be subjected to the phenomenon of seizing.

At present, in order to meet the requirements of an oil interruption test of an aeroengine, an emergency lubricating system is additionally arranged in the aeroengine, and particularly, an emergency oil tank is installed in an oil pool of an inner cavity of a bearing seat to store oil, an oil nozzle is installed at the top of the emergency oil tank, the oil nozzle comprises an oil way and an air way, the oil way is communicated with the emergency oil tank, the air way is communicated with a sealing pressurizing cavity of the aeroengine, and after oil supply of a main oil system is interrupted, the oil in the emergency oil tank is sucked into mist under the injection of air flow and is injected into a bearing.

However, because the aero-engine is complex in structure and limited in internal space, the design difficulty of the bearing seat and related structures in the aero-engine can be greatly increased due to the additional arrangement of the emergency lubrication system, and only part of the bearing seat can meet the installation requirements of the oil tank and the lubricating oil nozzle, so that the applicability is poor.

Disclosure of Invention

The invention provides a bearing cavity sealing air-entraining structure and an aeroengine, which are used for solving the technical problem that the design difficulty of a bearing seat and related structures is high because the existing aeroengine meets the requirements of lubricating oil interruption tests.

According to one aspect of the invention, a bearing cavity sealing air-entraining structure is provided, which comprises a sealing ring casing, a bearing seat arranged in the sealing ring casing, a rotating bearing arranged in the bearing seat, a rotor assembly arranged in the sealing ring casing and a sealing comb ring sleeved outside the rotor assembly, wherein the sealing ring casing and the bearing seat enclose to form a first containing cavity, the sealing ring casing and the sealing comb ring enclose to form an air-entraining channel which is arranged opposite to the rotating bearing in the axial direction and is used for introducing sealing air, an air-inlet channel which is respectively communicated with the first containing cavity and the air-entraining channel is arranged between the sealing ring casing and the rotating bearing, the bearing seat comprises a second containing cavity which is respectively communicated with an inner cavity of the rotating bearing and is used for containing vaporific lubricating oil, and a backflow channel which is respectively communicated with the first containing cavity and the second containing cavity, and a flow guide assembly which is used for guiding the sealing air into the air-entraining channel is arranged at the end part, close to the rotating bearing, in the air-entraining channel.

As a further improvement of the above technical scheme:

Further, the sealing ring case comprises a comb tooth sealing part which is in butt joint with the sealing comb tooth ring and is used for preventing oil from leaking from the air entraining channel, and an oil mist separating part which forms an air inlet channel by surrounding with the rotating bearing, wherein the comb tooth sealing part and the oil mist separating part form the air entraining channel by surrounding with the sealing comb tooth ring, and oil mist separating holes which are respectively communicated with the air entraining channel and the first containing cavity are formed in the oil mist separating part along the radial direction.

Further, the oil mist separation holes are provided in plurality, and the plurality of oil mist separation holes are arranged on the oil mist separation part at intervals along the axial direction and/or the circumferential direction.

Further, the flow guiding assembly comprises a first flow guiding boss formed by extending the oil mist separating part along the radial direction towards the direction close to the sealing comb tooth ring and a second flow guiding boss formed by extending the sealing comb tooth ring along the radial direction towards the direction close to the oil mist separating part, and the axial distance between the first flow guiding boss and the rotating bearing is larger than the axial distance between the second flow guiding boss and the rotating bearing.

Further, a collision and grinding layer is arranged on the end face of the sealing part of the comb teeth, facing the sealing part of the comb teeth, of the sealing comb teeth, and sealing comb teeth which are in butt fit with the collision and grinding layer are arranged on the end face of the sealing part of the comb teeth, facing the sealing part of the comb teeth.

Further, an axial abutment portion for axially abutting against the rotary bearing to axially position the rotary bearing is provided on an axial end portion of the oil mist separation portion toward the rotary bearing.

Further, the axial abutting portion is provided in plurality, and the plurality of axial abutting portions are arranged on the axial end portion of the oil mist separation portion, which faces the rotating bearing, at intervals in the circumferential direction.

Further, the rotary bearing comprises a bearing outer ring, a bearing inner ring and a bearing retainer arranged between the bearing outer ring and the bearing inner ring, a first opening communicated with the second containing cavity is arranged between the bearing retainer and the bearing outer ring, and a second opening communicated with the second containing cavity is arranged between the bearing retainer and the bearing inner ring.

Further, an oil return tank and an oil nozzle for injecting oil to the rotating bearing are arranged in the second containing cavity, and an oil return hole communicated with the oil return tank is arranged in the first containing cavity.

According to another aspect of the invention, there is also provided an aeroengine comprising the bearing cavity seal bleed air structure described above.

The invention has the following beneficial effects:

According to the bearing cavity sealing air-entraining structure, when the lubricating oil interruption test is carried out on the aeroengine, sealing air entering the air-entraining channel no longer supplies lubricating oil to the rotating bearing, the sealing air flows into the first container through the air inlet channel under the guiding effect of the guide component, so that the sealing air is prevented from directly impacting the rotating bearing, and then flows into the second containing cavity through the backflow channel, so that the air in the second containing cavity flows back, and further the vaporific lubricating oil is driven to enter the rotating bearing for lubrication, the running time of the rotating bearing during the lubricating oil interruption period is prolonged, the rotating bearing is prevented from holding a shaft, the aeroengine meets the lubricating oil interruption test requirement, the guide component is arranged in the air-entraining channel to guide the sealing air for preventing the lubricating oil leakage, so that the sealing air is fully utilized to guide the air in the second containing cavity, and the vaporific lubricating oil is driven to lubricate the rotating bearing.

In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:

FIG. 1 is a schematic view of a bearing cavity seal bleed air structure according to a preferred embodiment of the present invention;

fig. 2 is a simplified schematic of the bearing cavity seal bleed air structure of the preferred embodiment of the present invention.

Legend description:

100. Sealing the ring case; 110. a comb tooth sealing part; 120. an oil mist separation unit; 121. a first flow directing boss; 130. an oil mist separation hole; 200. a bearing seat; 210. a second cavity; 220. a lubricating oil nozzle; 300. a rotating bearing; 310. a bearing holder; 320. a first opening; 330. a second opening; 400. a rotor assembly; 500. sealing the comb ring; 510. a second flow directing boss; 600. a first cavity; 700. a bleed air passage; 800. an air intake passage; 900. and a return passage.

Detailed Description

Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.

FIG. 1 is a schematic view of a bearing cavity seal bleed air structure according to a preferred embodiment of the present invention; fig. 2 is a simplified schematic of the bearing cavity seal bleed air structure of the preferred embodiment of the present invention.

As shown in fig. 1 and 2, the bearing cavity sealing air-entraining structure of the present embodiment includes a sealing ring casing 100, a bearing seat 200 disposed in the sealing ring casing 100, a rotary bearing 300 disposed in the bearing seat 200, a rotor assembly 400 disposed in the sealing ring casing 100, and a sealing comb ring 500 sleeved outside the rotor assembly 400, wherein the sealing ring casing 100 and the bearing seat 200 enclose to form a first cavity 600, the sealing ring casing 100 and the sealing comb ring 500 enclose to form an air-entraining channel 700 disposed opposite to the rotary bearing 300 in an axial direction for introducing sealing air, an air-intake channel 800 communicating with the first cavity 600 and the air-entraining channel 700 respectively is disposed between the sealing ring casing 100 and the rotary bearing 300, the bearing seat 200 includes a second cavity 210 communicating with an inner cavity of the rotary bearing 300 for accommodating mist-like lubricant and a backflow channel 900 communicating with the first cavity 600 and the second cavity 210 respectively, and an end portion of the air-entraining channel 700 adjacent to the rotary bearing 300 is provided with an air-intake channel 800 for guiding sealing air. Specifically, in the bearing cavity seal air-entraining structure of the present invention, when the air-vehicle engine performs the lubricating oil interruption test, the seal air entering the air-entraining channel 700 flows into the first container through the air inlet channel 800 under the guiding action of the guiding component when the lubricating oil is not supplied to the rotating bearing 300, so as to prevent the seal air from directly impacting the rotating bearing 300, and the seal air flows into the second container 210 through the backflow channel 900, so that the air in the second container 210 flows back, and further drives the atomized lubricating oil to enter the rotating bearing 300 for lubrication, thereby prolonging the running time of the rotating bearing 300 during the lubricating oil interruption, preventing the rotating bearing 300 from seizing, so that the air-vehicle engine meets the lubricating oil interruption test requirement. It should be appreciated that the seal gas is drawn from the interior cavity of the rotor assembly 400 and flows into the bleed air passage 700. Alternatively, rotor assembly 400 is a compressor rotor. It should be understood that the radial, axial and circumferential directions are all referenced to the rotor assembly.

As shown in fig. 1, in the present embodiment, the seal ring case 100 includes a seal portion 110 of a grate for preventing oil from leaking from the bleed air channel 700, which is in abutting engagement with the seal grate ring 500, and an oil mist separation portion 120 of an air intake channel 800, which is surrounded by the seal portion 110 and the oil mist separation portion 120, which are surrounded by the seal grate ring 500, and an oil mist separation hole 130, which is respectively communicated with the bleed air channel 700 and the first cavity 600, is opened in the oil mist separation portion 120 in the radial direction. Specifically, the present invention relates to a method for manufacturing a semiconductor device. The sealing part 110 of the comb teeth is in abutting fit with the sealing comb teeth ring 500 to further prevent the oil from leaking from the air entraining channel 700, the oil mist separation part 120 and the rotating bearing 300 are enclosed to form the air inlet channel 800 to guide sealing gas into the first accommodating cavity 600, and the oil accumulated in the air entraining channel 700 is discharged through the oil mist separation hole 130, so that the oil in the air entraining channel 700 flows into the first accommodating cavity 600 under the centrifugal action to leak from the air entraining channel 700.

As shown in fig. 2, in the present embodiment, a plurality of oil mist separation holes 130 are provided, and the plurality of oil mist separation holes 130 are arranged on the oil mist separation part 120 at intervals in the axial direction and/or the circumferential direction. Specifically, the plurality of oil mist separation holes 130 are arranged on the oil mist separation part 120 at intervals along the axial direction and/or the circumferential direction, so that the oil in the air entraining channel 700 is discharged in an omnibearing manner, and the leakage of the oil is avoided to the greatest extent.

As shown in fig. 2, in the present embodiment, the flow guiding assembly includes a first flow guiding boss 121 formed by extending the oil mist separating portion 120 in a radial direction toward the sealing comb ring 500 and a second flow guiding boss 510 formed by extending the sealing comb ring 500 in a radial direction toward the oil mist separating portion 120, and an axial distance between the first flow guiding boss 121 and the rotating bearing 300 is greater than an axial distance between the second flow guiding boss 510 and the rotating bearing 300. Specifically, the first guide boss 121 and the second guide boss 510 cooperate to prevent the seal gas from directly striking the rolling bearing 300, and by making the axial distance between the first guide boss 121 and the rolling bearing 300 greater than the axial distance between the second guide boss 510 and the rolling bearing 300, a guide gap is formed between the first guide boss 121 and the second guide boss 510 toward the air inlet channel 800 to guide the seal gas into the first accommodating chamber 600 through the air inlet channel 800.

As shown in fig. 1, in this embodiment, a rubbing layer is disposed on an end face of the sealing part 110 facing the sealing ring 500, and sealing teeth in contact with the rubbing layer are disposed on an end face of the sealing ring 500 facing the sealing part 110. Specifically, through the butt cooperation of the comb tooth of sealing and bump grinding layer to prevent that the lubricating oil from leaking, and reduce the bump wearing and tearing between the comb tooth of sealing and the bump grinding layer through bump grinding layer. Optionally, the rubbing layer is made of graphite or aluminum silicon.

In the present embodiment, an axial abutment portion for axially abutting the rotary bearing 300 to axially position the rotary bearing 300 is provided on an axial end portion of the oil mist separation portion 120 facing the rotary bearing 300. Specifically, the axial positioning of the rolling bearing 300 is achieved by the axial abutment portion abutting the rolling bearing 300 in the axial direction to cooperate with the bearing housing 200.

In this embodiment, a plurality of axial abutting portions are provided, and the plurality of axial abutting portions are circumferentially arranged at intervals on an axial end portion of the oil mist separation portion 120 toward the rolling bearing 300. Specifically, the rotational bearing 300 is simultaneously axially abutted by a plurality of axial abutment portions to ensure reliable axial positioning of the rotational bearing 300. Optionally, the axial abutment is arranged in a claw shape.

As shown in fig. 2, in the present embodiment, the rotary bearing 300 includes an outer bearing ring, an inner bearing ring, and a bearing holder 310 disposed between the outer bearing ring and the inner bearing ring, a first opening 320 communicating with the second cavity 210 is provided between the bearing holder 310 and the outer bearing ring, and a second opening 330 communicating with the second cavity 210 is provided between the bearing holder 310 and the inner bearing ring. Specifically, the mist-like oil in the second cavity 210 enters the rolling bearing 300 through the first opening 320 and the second opening 330 to lubricate the rolling bearing 300, and prolong the normal working time of the rolling bearing 300 after the mist-like oil is interrupted.

As shown in fig. 1, in the present embodiment, an oil return tank and an oil nozzle 220 for injecting oil into the rolling bearing 300 are disposed in the second chamber 210, and an oil return hole communicating with the oil return tank is disposed in the first chamber 600. Specifically, when the aeroengine works normally, the lubricating oil is sprayed to the rotating bearing 300 through the lubricating oil nozzle 220 to lubricate the rotating bearing 300, then the lubricating oil in the second containing cavity 210 is collected through the oil return pool, and the lubricating oil in the first containing cavity 600 is collected through the oil return hole, so that after the lubricating oil nozzle 220 does not spray the lubricating oil any more, the lubricating oil in the second containing cavity 210 is atomized, and the atomized lubricating oil can lubricate the rotating bearing 300.

The aeroengine of this embodiment includes foretell bearing chamber seal bleed air structure. Specifically, the bearing cavity sealing air-entraining structure is adopted in the aeroengine, so that the requirements of lubricating oil interruption test are met while the design difficulty and the assembly difficulty of the bearing seat 200 and related structures in the aeroengine are reduced, and the aeroengine bearing cavity sealing air-entraining structure is high in practicability and suitable for wide popularization and application.

The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. The utility model provides a seal bleed structure in bearing chamber, a serial communication port, including seal ring cartridge receiver (100), lay in bearing frame (200) in seal ring cartridge receiver (100), lay in rotation bearing (300) in bearing frame (200), lay in rotor subassembly (400) and the outer seal comb ring (500) of rotor subassembly (400) are located to cover in seal ring cartridge receiver (100), seal ring cartridge receiver (100) and bearing frame (200) enclose and form first appearance chamber (600), seal ring cartridge receiver (100) and seal comb ring (500) enclose and form the relative air bleed passageway (700) that are used for introducing seal gas that lay with rotation bearing (300) in axial direction, be equipped with between seal ring cartridge receiver (100) and rotation bearing (300) respectively with first appearance chamber (600) and bleed passageway (700) intercommunication air inlet passageway (800), bearing frame (200) include with the outer second appearance chamber (210) that are used for holding the lubricating oil of inner chamber intercommunication of rotation bearing (300) and be equipped with respectively with seal ring cartridge receiver (100) and bleed passageway (700) and be close to guide passageway (900) that seal ring cartridge receiver (300) are equipped with the air bleed passageway (700) of air.

2. The bearing cavity seal bleed air structure according to claim 1, wherein the seal ring case (100) comprises a seal comb tooth seal part (110) which is in abutting fit with the seal comb tooth ring (500) and is used for preventing lubricating oil from leaking from the bleed air channel (700), and an oil mist separation part (120) which is enclosed with the rotary bearing (300) to form an air inlet channel (800), the seal comb tooth seal part (110) and the oil mist separation part (120) are enclosed with the seal comb tooth ring (500) to form the bleed air channel (700), and oil mist separation holes (130) which are respectively communicated with the bleed air channel (700) and the first containing cavity (600) are formed in the oil mist separation part (120) along the radial direction.

3. The bearing cavity seal bleed air structure according to claim 2, wherein a plurality of oil mist separation holes (130) are provided, and the plurality of oil mist separation holes (130) are arranged on the oil mist separation part (120) at intervals in the axial direction and/or the circumferential direction.

4. The bearing cavity seal bleed air structure of claim 2, wherein the deflector assembly comprises a first deflector boss (121) formed by extending the oil mist separation portion (120) in a radial direction toward the seal comb ring (500) and a second deflector boss (510) formed by extending the seal comb ring (500) in a radial direction toward the oil mist separation portion (120), and an axial distance between the first deflector boss (121) and the rotary bearing (300) is greater than an axial distance between the second deflector boss (510) and the rotary bearing (300).

5. The bearing cavity sealing and air entraining structure according to claim 2, characterized in that a bump grinding layer is arranged on the end face of the sealing comb tooth sealing part (110) facing the sealing comb tooth ring (500), and a sealing comb tooth in butt fit with the bump grinding layer is arranged on the end face of the sealing comb tooth ring (500) facing the comb tooth sealing part (110).

6. The bearing cavity seal bleed air structure according to claim 2, characterized in that an axial abutment portion for axially abutting against the rotary bearing (300) to axially position the rotary bearing (300) is provided on an axial end portion of the oil mist separating portion (120) toward the rotary bearing (300).

7. The bearing cavity seal bleed air structure according to claim 6, wherein a plurality of axial abutment portions are provided, the plurality of axial abutment portions being circumferentially spaced apart on an axial end portion of the oil mist separation portion (120) toward the rolling bearing (300).

8. The bearing cavity seal bleed air structure of any of claims 1-7, wherein the rotary bearing (300) comprises an outer bearing ring, an inner bearing ring, and a bearing retainer (310) disposed between the outer bearing ring and the inner bearing ring, a first opening (320) communicating with the second cavity (210) is provided between the bearing retainer (310) and the outer bearing ring, and a second opening (330) communicating with the second cavity (210) is provided between the bearing retainer (310) and the inner bearing ring.

9. The bearing cavity seal bleed air structure according to any one of claims 1-7, characterized in that an oil return tank and an oil jet nozzle (220) for jetting oil to the rotating bearing (300) are arranged in the second containing cavity (210), and an oil return hole communicated with the oil return tank is arranged in the first containing cavity (600).

10. An aircraft engine comprising a bearing cavity seal bleed air structure as claimed in any one of claims 1 to 9.