A bearing cavity sealing structure and an aircraft engine

Abstract

The invention discloses a bearing cavity sealing structure and an aero-engine, wherein the sealing structure comprises a casing, a rotating shaft is arranged in the casing, a channel for high-pressure gas to be filled is arranged in the rotating shaft; a vent hole connected to the channel is formed through the rotating shaft in the radial direction; a grate ring rotating with the rotating shaft is arranged on the rotating shaft; a through-hole is formed through the grate ring in the radial direction at the position corresponding to the vent hole; a sealing ring is matched with the outer clearance of the outer periphery of the grate ring, the sealing ring is fixedly connected in the casing, and the interior of the casing is divided into a flow channel cavity and a lubricating oil cavity from left to right along the axial direction; a bearing is arranged in the lubricating oil cavity, and the rotating shaft is rotatably connected in the bearing; an oil-slinging plate is arranged between the sealing ring and the bearing, and the oil-slinging plate is used to throw the lubricating oil into the lubricating oil cavity; an air cavity is surrounded between the oil-slinging plate and the sealing ring, and the outlet of the air cavity is arranged away from the bearing in the axial direction and connected to the lubricating oil cavity. The invention can avoid the impact of high-pressure gas on the bearing, and ensure that the lubricating oil thrown out by the oil-slinging plate fully lubricates the bearing.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to a bearing cavity sealing structure and an aeroengine. Background Art

[0002] Aircraft engines need to generate work through the rotation of rotor blades. The rotor needs to be supported by bearings in the casing to facilitate flexible rotation of the rotor. When the bearings are working normally, lubricating oil is required to reduce the friction of the mechanical joint surfaces. To prevent the lubricating oil from entering the flow path, the engine is usually designed with a sealing structure for the bearing cavity to avoid leakage of lubricating oil, increased fuel consumption, and lubricating oil contamination of the flow path gas.

[0003] Most of the existing bearing cavity sealing structures use the mutual engagement of two comb teeth to achieve sealing, and introduce high-pressure gas as sealing gas to exert extrusion force, so that the tooth surfaces of the comb teeth engage more tightly and improve the sealing effect. However, when the high-pressure gas is introduced into the existing bearing cavity sealing structure, it will flow directly to the bearing, causing impact on the bearing, resulting in insufficient bearing lubrication, deteriorating the bearing working environment and reducing the bearing service life. Summary of the invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the sealing structure of the bearing cavity used in the aircraft engine in the prior art will produce impact on the bearing when the high-pressure gas is introduced, resulting in insufficient bearing lubrication, deteriorating the bearing working environment and reducing the service life of the bearing, thereby providing a bearing cavity sealing structure and an aircraft engine.

[0005] According to a first aspect of the present invention, a bearing cavity sealing structure is provided, comprising:

[0006] Receiver;

[0007] A rotating shaft is axially arranged in the casing, a channel is provided in the rotating shaft, and the channel is used for high-pressure gas to be filled; a vent hole is formed radially through the rotating shaft and communicated with the channel;

[0008] A grate ring is arranged on the rotating shaft and rotates together with the rotating shaft; a through hole is formed through the grate ring in the radial direction at a position corresponding to the vent hole;

[0009] A sealing ring is provided outside the outer periphery of the comb ring with a clearance fit; the sealing ring is fixedly connected in the casing and divides the interior of the casing into a flow channel cavity and a lubricating oil cavity from left to right along the axial direction;

[0010] A bearing is disposed in the lubricating oil cavity, and the rotating shaft is rotatably connected in the bearing;

[0011] An oil-slinging plate is arranged between the sealing ring and the bearing and is used to throw the lubricating oil into the lubricating oil cavity; an air cavity is formed between the oil-slinging plate and the sealing ring, and an outlet of the air cavity is arranged axially away from the bearing and is connected to the lubricating oil cavity.

[0012] A bearing cavity sealing structure according to the present invention has at least the following technical effects:

[0013] By fitting the sealing ring in the grate ring with a gap, a space for high-pressure gas to flow through is formed between the sealing ring and the grate ring, and an air cavity is formed between the oil-slinging plate and the sealing ring, and the outlet of the air cavity is arranged axially away from the bearing. When the aircraft engine equipped with the bearing cavity sealing structure is in normal use, the high-pressure gas enters through the channel of the rotating shaft, and after passing through the air vents and the air-through holes in turn, it is divided into two air flows flowing axially to the left and axially to the right. The air flow flowing axially to the left flows through the gap space between the sealing ring and the grate ring and flows into the flow channel cavity. At the same time, the air flow flowing axially to the right flows through the gap space between the sealing ring and the grate ring and enters the air cavity and then flows into the lubricating oil cavity, thereby achieving the goal of delivering the high-pressure gas to the flow channel cavity while also delivering the high-pressure gas to the lubricating oil cavity to improve the sealing effect and efficiency. At the same time, when the high-pressure gas flows from the air cavity into the lubricating oil cavity During the process, because the outlet of the air cavity is arranged axially away from the bearing, the high-pressure gas flowing into the lubricating oil cavity from the air cavity will not directly flow to the ball and inner ring of the bearing, which can effectively avoid impact on the bearing, resulting in insufficient lubrication of the bearing, deteriorating the working environment of the bearing and reducing the service life of the bearing; and an oil-slinging plate is provided at the end where the airflow flowing axially to the right flows through the gap space between the sealing ring and the grate ring and flows out. The oil-slinging plate can effectively block the high-pressure gas flowing axially to the right and flowing out through the gap space between the sealing ring and the grate ring from directly flowing to the ball and inner ring of the bearing while realizing the oil-slinging function, which can more effectively avoid impact on the bearing, ensure that the lubricating oil thrown out by the oil-slinging plate fully lubricates the bearing, improves the working environment of the bearing, prolongs the service life of the bearing, and thus prolongs the service life of the aircraft engine equipped with the bearing cavity sealing structure.

[0014] Preferably, the relatively left part of the comb tooth ring located in the axial direction with respect to the air through hole is set as the first comb tooth part; and the relatively right part of the comb tooth ring located in the axial direction with respect to the air through hole is set as the second comb tooth part; the gap between the tooth tip of the first comb tooth part and the sealing ring is connected to the flow channel cavity; the gap between the tooth tip of the second comb tooth part and the sealing ring is connected to the air cavity; the outer diameter of the first comb tooth part is larger than the outer diameter of the second comb tooth part to form a stepped structure.

[0015] Preferably, the oil-slinging plate is provided with a horizontal ring protruding from one side axially toward the sealing ring, the horizontal ring covers the end of the sealing ring facing the oil-slinging plate, and the inner wall surface of the horizontal ring and the outer peripheral surface of the sealing ring form the outlet of the air cavity.

[0016] Preferably, a boss is provided on the outer peripheral surface of the portion of the sealing ring located inside the horizontal ring, and the outer side wall of the boss and the inner wall surface of the horizontal ring form an outlet of the air cavity; the boss is inclinedly arranged at one end surface axially away from the oil-slinging plate, and is arranged gradually approaching the oil-slinging plate in a direction radially away from the center of the sealing ring;

[0017] And / or, the outer diameter of the horizontal ring is not less than the outer ring diameter of the raceway in the bearing for placing the balls.

[0018] Preferably, one end of the oil slinger plate axially facing the bearing is arranged as an inclined surface, and the inclined surface is arranged gradually away from the bearing in a direction radially away from the center of the oil slinger plate.

[0019] Preferably, the outer peripheral surface of the sealing ring is fixedly connected to the casing via a connecting portion; the connecting portion is arranged obliquely and gradually approaches the bearing arrangement in a radial direction away from the center of the sealing ring.

[0020] Preferably, the sealing ring and the connecting portion are integrally formed to form an integral structure.

[0021] Preferably, a guide arc groove is recessed on the inner wall of the sealing ring at a position corresponding to the air-through hole, and the guide arc groove surrounds the inner wall in the circumferential direction.

[0022] Preferably, the inner diameter of the ventilation hole is larger than the inner diameter of the through-hole, and the size of the ventilation hole is smaller than the size of the arc guide groove.

[0023] According to a second aspect of the present invention, an aircraft engine is provided, comprising the bearing cavity sealing structure provided by the first aspect.

[0024] An aircraft engine according to the present invention has at least the following technical effects:

[0025] The bearing cavity sealing structure is achieved by fitting the sealing ring into the grate ring with a gap, so that a space for high-pressure gas to flow through is formed between the sealing ring and the grate ring, and an air cavity is formed between the oil-slinging plate and the sealing ring, and the outlet of the air cavity is arranged axially away from the bearing; when the aircraft engine is in normal use, the high-pressure gas enters through the channel of the rotating shaft, and after passing through the air vents and the air-through holes in turn, it is divided into two air flows flowing axially to the left and axially to the right, wherein the air flow flowing axially to the left flows through the gap space between the sealing ring and the grate ring and flows into the flow channel cavity, while the air flow flowing axially to the right flows through the gap space between the sealing ring and the grate ring and enters the air cavity and then flows into the lubricating oil cavity, thereby achieving the goal of delivering the high-pressure gas to the flow channel cavity while also delivering the high-pressure gas to the lubricating oil cavity to improve the sealing effect and efficiency; at the same time, when the high-pressure gas flows into the air cavity from the air cavity During the lubrication of the oil chamber, because the outlet of the air chamber is arranged axially away from the bearing, the high-pressure gas flowing into the lubrication chamber from the air chamber will not directly flow to the ball and inner ring of the bearing, which can effectively avoid the impact on the bearing, resulting in insufficient bearing lubrication, deterioration of the bearing working environment and reduced bearing service life; and an oil-slinging plate is provided at one end where the airflow flowing axially to the right flows through the gap space between the sealing ring and the grate ring and flows out. The oil-slinging plate can effectively block the high-pressure gas flowing axially to the right and flowing through the gap space between the sealing ring and the grate ring from directly flowing to the ball and inner ring of the bearing while realizing the oil-slinging function, which can more effectively avoid the impact on the bearing, ensure that the lubricating oil thrown out by the oil-slinging plate fully lubricates the bearing, improves the bearing working environment, extends the bearing service life, and thus extends the service life of the aircraft engine.

[0026] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0028] Figure 1 A schematic diagram of a cross-section of a bearing cavity sealing structure of the present embodiment;

[0029] Figure 2 for Figure 1 The enlarged schematic diagram of point A in the middle;

[0030] Figure 3 for Figure 1 The enlarged schematic diagram of point B in the middle;

[0031] Figure 4 for Figure 1 Schematic diagram of the structure with air bleed direction;

[0032] Figure 5 for Figure 1 Schematic diagram of the structure with oil slinging direction.

[0033] Description of reference numerals:

[0034] 1- casing, 11- flow channel cavity, 12- lubricating oil cavity;

[0035] 2-rotating shaft, 21-channel, 22-vent;

[0036] 3-comb tooth ring, 31-air hole, 32-first comb tooth part, 33-second comb tooth part;

[0037] 4-sealing ring, 41-boss, 42-connecting part, 43-guiding arc groove;

[0038] 5-Bearing;

[0039] 6- oil-slinging plate, 61- air cavity, 62- horizontal ring, 63- inclined surface. DETAILED DESCRIPTION

[0040] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0042] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0044] Embodiment 1

[0045] like Figures 1 to 3 The present embodiment shows a bearing cavity sealing structure, comprising a casing 1, wherein a rotating shaft 2 is axially arranged in the casing 1, a channel 21 is provided in the rotating shaft 2, one end of the channel 21 penetrates the rotating shaft 2 in the axial direction and is used for high-pressure gas to be filled; a vent hole 22 is formed radially through the rotating shaft 2 and is connected to the channel 21; a grate ring 3 is provided on the rotating shaft 2 and rotates together with the rotating shaft 2; a through-hole 31 is formed radially through the grate ring 3 at a position corresponding to the vent hole 22; a sealing ring 4 is provided in the outer clearance of the outer periphery of the grate ring 3, and the sealing ring 4 is fixedly connected to the The casing 1 is inside, and the interior of the casing 1 is divided into a flow channel cavity 11 and a lubricating oil cavity 12 in sequence from left to right along the axial direction; a bearing 5 is provided in the lubricating oil cavity 12, and the rotating shaft 2 is rotatably connected in the bearing 5; an oil-slinging plate 6 is provided between the sealing ring 4 and the bearing 5, and the oil-slinging plate 6 is used to throw the lubricating oil into the lubricating oil cavity 12; an air cavity 61 is formed between the oil-slinging plate 6, the sealing ring 4 and the comb ring 3, and the air cavity 61 is connected to the gap space between the sealing ring 4 and the comb ring 3, and the outlet of the air cavity 61 is arranged axially away from the bearing 5 and is connected to the lubricating oil cavity 12. It can be understood that the axial direction described in this embodiment refers to Figure 1 The axial direction, axial left and axial right are based on Figure 1 described from the perspective of .

[0046] The bearing cavity sealing structure of this embodiment is formed by sleeve-fitting the sealing ring 4 into the grate ring 3 with clearance, so that a space for high-pressure gas to flow through is formed between the sealing ring 4 and the grate ring 3, and an air cavity 61 is formed between the oil-slinging plate 6 and the sealing ring 4, and the outlet of the air cavity 61 is arranged axially away from the bearing 5; Figure 4As shown, when the aircraft engine equipped with the bearing cavity sealing structure of this embodiment is in normal use, high-pressure gas enters through the channel 21 of the rotating shaft 2, and after passing through the vent hole 22 and the air hole 31 in turn, it is divided into two air flows, one flowing axially to the left and the other flowing axially to the right. The air flow flowing axially to the left passes through the gap space between the sealing ring 4 and the comb ring 3 and flows into the flow channel cavity 11. At the same time, the air flow flowing axially to the right passes through the gap space between the sealing ring 4 and the comb ring 3 and enters the air cavity 61 and then flows into the lubricating oil cavity 12, so that the high-pressure gas is delivered to the flow channel cavity 11 and the lubricating oil cavity 12 at the same time, which improves the sealing effect and efficiency. At the same time, in the process of high-pressure gas flowing from the air cavity 61 into the lubricating oil cavity 12, because the outlet of the air cavity 61 is arranged axially away from the bearing 5, the lubricating oil flowing from the air cavity 61 The high-pressure gas in the cavity 12 will not flow directly to the ball and inner ring of the bearing 5, which can effectively avoid the impact on the bearing 5, resulting in insufficient lubrication of the bearing 5, deteriorating the working environment of the bearing 5 and reducing the service life of the bearing 5; and an oil-slinging plate 6 is provided at one end where the airflow flowing axially to the right flows through the gap space between the sealing ring 4 and the comb ring 3. The oil-slinging plate 6 can effectively block the high-pressure gas flowing axially to the right and flowing through the gap space between the sealing ring 4 and the comb ring 3 from flowing directly to the ball and inner ring of the bearing 5 while realizing the oil-slinging function, so as to more effectively avoid the impact on the bearing 5, ensure that the lubricating oil thrown out by the oil-slinging plate 6 fully lubricates the bearing 5, improve the working environment of the bearing 5, and extend the service life of the bearing 5, thereby extending the service life of the aircraft engine equipped with the bearing cavity sealing structure of this embodiment.

[0047] The air cavity 61 formed between the oil slinger plate 6 and the sealing ring 4 can also rectify the airflow flowing in through the gap outlet between the sealing ring 4 and the grate ring 3, making the airflow flowing into the lubricating oil cavity 12 more uniform, further improving the sealing efficiency.

[0048] like Figure 1 and Figure 2As shown, optionally, the relatively left part of the comb tooth ring 3 located in the axial direction with respect to the air hole 31 is set as the first comb tooth part 32; and the relatively right part of the air hole 31 located in the axial direction is set as the second comb tooth part 33; the gap between the tooth tip of the first comb tooth part 32 and the sealing ring 4 is connected to the flow channel cavity 11; the gap between the tooth tip of the second comb tooth part 33 and the sealing ring 4 is connected to the air cavity 61; the outer diameter of the first comb tooth part 32 is larger than the outer diameter of the second comb tooth part 33 to form a stepped structure. The high-pressure gas flowing out through the air hole 31 is divided into two air flows, one flowing axially to the left and the other flowing axially to the right. The air flow flowing axially to the left flows through the gap space between the sealing ring 4 and the first comb tooth portion 32 and flows into the flow channel cavity 11. At the same time, the air flow flowing axially to the right flows through the gap space between the sealing ring 4 and the second comb tooth portion 33 and enters the air cavity 61 and then flows into the lubricating oil cavity 12, so that the high-pressure gas is delivered to the flow channel cavity 11 and the lubricating oil cavity 12 at the same time, which improves the sealing effect and efficiency. At the same time, because there is a non-zero spacing between the gap space between the sealing ring 4 and the first comb tooth portion 32 and the gap space between the sealing ring 4 and the second comb tooth portion 33 in the radial direction, that is, the two are not aligned in the axial direction, the gap space between the sealing ring 4 and the first comb tooth portion 32 and the gap space between the sealing ring 4 and the second comb tooth portion 33 form a step-shaped blocking structure at the connection point, which can effectively prevent the lubricating oil from flowing from the lubricating oil cavity 12 into the flow channel cavity 11 to cause pollution, and can also avoid the convection between the two that causes the high-pressure gas flow rate to slow down.

[0049] In order to better realize the high pressure gas delivery to the flow channel cavity 11 and the high pressure gas delivery to the lubricating oil cavity 12 to improve the sealing effect and efficiency; Figure 2 As shown, specifically, the gap size between the sealing ring 4 and the tooth tips of the first comb tooth portion 32 is greater than the gap size between the sealing ring 4 and the tooth tips of the second comb tooth portion 33 .

[0050] like Figure 1 and Figure 2 As shown, optionally, the inner wall of the sealing ring 4 is provided with a guide arc groove 43 corresponding to the position of the air-through hole 31, and the guide arc groove 43 is circumferentially arranged around a circle. Through the guiding effect of the guide arc groove 43, and the two edge ends of the guide arc groove 43 are respectively connected to the gap space between the sealing ring 4 and the first comb tooth part 32 and the gap space between the sealing ring 4 and the second comb tooth part 33, so that the high-pressure gas flowing out through the air-through hole 31 is smoothly divided into two air flows flowing axially to the left and axially to the right, and flows into the gap space between the sealing ring 4 and the first comb tooth part 32 and the gap space between the sealing ring 4 and the second comb tooth part 33 respectively. At the same time, the cavity surrounded by the guide arc groove 43 and the comb tooth ring 3 can mix the high-pressure gas introduced through the rotating shaft 2, thereby improving the comb tooth sealing effect.

[0051] Specifically, the vent holes 22 and the air holes 31 are uniformly distributed along the circumferential direction to ensure that the high-pressure gas introduced through the channel 21 of the rotating shaft 2 enters the guide arc groove 43 and the cavity surrounded by the comb ring 3 uniformly and mixes circumferentially, further improving the sealing effect of the comb teeth.

[0052] like Figure 1 As shown, optionally, the inner diameter of the vent hole 22 is larger than the inner diameter of the through hole 31, and the size of the vent hole 22 is smaller than the size of the guide arc groove 43. Because the through hole 31 is the minimum aperture of the flow path of the high-pressure gas flowing from the channel 21 to the gap space between the sealing ring 4 and the comb ring 3, the high-pressure gas flows faster at the connection between the vent hole 22 and the through hole 31, and then changes the flow direction from radial to axial in the large-sized guide arc groove 43, thereby accelerating the gas transmission efficiency.

[0053] like Figure 1 and Figure 3 As shown, optionally, the oil-slinging plate 6 is provided with a horizontal ring 62 protruding from one side axially facing the sealing ring 4, the horizontal ring 62 covers the end of the sealing ring 4 facing the oil-slinging plate 6, and the inner wall surface of the horizontal ring 62 and the outer peripheral surface of the sealing ring 4 form the outlet of the air cavity 61. The space enclosed between the inner wall surface of the horizontal ring 62 and the outer peripheral surface of the sealing ring 4 is a flow channel for high-pressure gas to be transported from the air cavity 61 to the lubricating oil cavity 12, so that the air flow is converted from radial to axial to be discharged in the opposite direction away from the bearing 5, ensuring that the high-pressure gas flowing into the lubricating oil cavity 12 will not directly flow to the ball and inner ring of the bearing 5, which can effectively avoid the impact on the bearing 5, thereby ensuring that the lubricating oil thrown out by the oil-slinging plate 6 fully lubricates the bearing 5, improves the working environment of the bearing 5, and prolongs the service life of the bearing 5.

[0054] like Figure 1 and Figure 3As shown, optionally, a boss 41 is provided on the outer peripheral surface of the portion of the sealing ring 4 located inside the horizontal ring 62, and the outer wall of the boss 41 and the inner wall of the horizontal ring 62 form an outlet of the air cavity 61; the boss 41 is inclined along an end face axially away from the oil-slinging plate 6, and is gradually approached to the oil-slinging plate 6 in a radial direction away from the center of the sealing ring 4. The space enclosed by the inner wall surface of the horizontal ring 62 and the outer peripheral surface of the boss 41 is the flow channel for high-pressure gas to be transported from the air cavity 61 to the lubricating oil cavity 12, so that the air flow is converted from radial to axial and discharged in the reverse direction away from the bearing 5, ensuring that the high-pressure gas flowing into the lubricating oil cavity 12 will not directly flow to the ball and inner ring of the bearing 5; and the boss 41 is inclined along the end surface axially away from the oil-slinging plate 6, so that an anti-backflow line is added in the effective space, effectively blocking the lubricating oil (oil mist) from entering the air cavity 61, thereby effectively preventing the lubricating oil (oil mist) from entering the flow channel through the gap space between the sealing ring 4 and the comb ring 3 to cause leakage, thereby improving the sealing efficiency and sealing effect of the bearing cavity sealing structure.

[0055] Optionally, the outer diameter of the horizontal ring 62 is equal to or greater than the outer diameter of the raceway in the bearing 5 for placing the balls; this can effectively prevent the high-pressure gas flowing into the lubricating oil cavity 12 from the outlet of the air cavity 61 from turning and axially impacting the balls of the bearing 5 along the outer peripheral surface of the horizontal ring 62, so that the lubricating oil thrown out by the oil-slinging plate can lubricate the bearing 5 more fully, more effectively improve the working environment of the bearing 5, and extend the service life of the bearing 5. It can be understood that the outer diameter of the raceway in the text refers to the inner diameter of the outer ring of the bearing 5; the raceway is the space surrounded by the inner and outer rings of the bearing 5 for placing the balls.

[0056] like Figure 1 and Figure 5 As shown, optionally, one end of the oil-slinging plate 6 axially facing the bearing 5 is provided with an inclined surface 63, and the inclined surface 63 is gradually arranged away from the bearing 5 in a direction radially away from the center of the oil-slinging plate 6. In this way, the oil return path of the lubricating oil for lubricating the bearing 5 can be optimized to prevent the lubricating oil from gathering; and the lubricating oil for lubricating the bearing 5 will be thrown out along the inclined surface 63 of the oil-slinging plate 6 by the action of centrifugal force, accelerating the atomization of the lubricating oil.

[0057] like Figure 1 and Figure 3 As shown, optionally, the outer peripheral surface of the sealing ring 4 is fixedly connected to the casing 1 through a connecting portion 42; the connecting portion 42 is arranged obliquely and is arranged gradually close to the bearing 5 in the radial direction away from the center of the sealing ring 4. This arrangement can further optimize the oil return path of the lubricating oil for lubricating the bearing 5, especially when the lubricating oil gathers at the right end of the sealing ring 4 in the axial direction, the lubricating oil will be accelerated to flow into the oil return port of the casing 1 along the inclined connecting portion 42 under the action of the high-pressure gas output from the air cavity 61.

[0058] Optionally, the sealing ring 4 and the connecting portion 42 are integrally formed to form an overall structure; the intermediate assembly steps are reduced, thereby reducing the assembly error between the sealing ring 4 and the connecting portion 42, and improving the structural accuracy of the bearing cavity sealing structure of this embodiment.

[0059] Embodiment 2

[0060] like Figures 1 to 5 The figure shows an aircraft engine provided in this embodiment, including the bearing cavity sealing structure described in the first embodiment. The bearing cavity sealing structure of the aircraft engine in this embodiment is formed by sleeve-fitting the sealing ring 4 in the grate ring 3 with a clearance, so that a space for high-pressure gas to flow through is formed between the sealing ring 4 and the grate ring 3, and an air cavity 61 is formed between the oil-slinging plate 6 and the sealing ring 4, and the outlet of the air cavity 61 is arranged axially away from the bearing 5; Figure 4 As shown, when the aircraft engine of this embodiment is in normal use, high-pressure gas enters through the channel 21 of the rotating shaft 2, and after passing through the vent hole 22 and the air hole 31 in turn, it is divided into two air flows flowing axially to the left and axially to the right. The air flow flowing axially to the left passes through the gap space between the sealing ring 4 and the comb ring 3 and flows into the flow channel cavity 11. At the same time, the air flow flowing axially to the right passes through the gap space between the sealing ring 4 and the comb ring 3 and enters the air cavity 61 and then flows into the lubricating oil cavity 12, so that the high-pressure gas is delivered to the flow channel cavity 11 and the lubricating oil cavity 12 at the same time, which improves the sealing effect and efficiency; at the same time, in the process of high-pressure gas flowing from the air cavity 61 into the lubricating oil cavity 12, because the outlet of the air cavity 61 is arranged axially away from the bearing 5, the lubricating oil flowing from the air cavity 61 The high-pressure gas in the cavity 12 will not flow directly to the ball and inner ring of the bearing 5, which can effectively avoid the impact on the bearing 5, resulting in insufficient lubrication of the bearing 5, deteriorating the working environment of the bearing 5 and reducing the service life of the bearing 5; and an oil-slinging plate 6 is provided at one end where the airflow flowing axially to the right flows through the gap space between the sealing ring 4 and the grate ring 3. The oil-slinging plate 6 can effectively block the high-pressure gas flowing axially to the right and flowing through the gap space between the sealing ring 4 and the grate ring 3 from flowing directly to the ball and inner ring of the bearing 5 while realizing the oil-slinging function, so as to more effectively avoid the impact on the bearing 5, ensure that the lubricating oil thrown out by the oil-slinging plate 6 fully lubricates the bearing 5, improve the working environment of the bearing 5, extend the service life of the bearing 5, and thus extend the service life of the aircraft engine of this embodiment.

[0061] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A bearing cavity sealing structure, characterized in that: include: Receiver (1); A rotating shaft (2) is axially arranged in the casing (1); a channel (21) is provided in the rotating shaft (2), and the channel (21) is used for charging high-pressure gas; a vent hole (22) is formed radially through the rotating shaft (2) and is in communication with the channel (21); A grate ring (3) is arranged on the rotating shaft (2) and rotates together with the rotating shaft (2); a vent hole (31) is formed through the grate ring (3) at a position corresponding to the vent hole (22) in a radial direction; A sealing ring (4) is arranged with a clearance fit outside the outer periphery of the comb ring (3); the sealing ring (4) is fixedly connected to the casing (1) and divides the interior of the casing (1) into a flow channel cavity (11) and a lubricating oil cavity (12) from left to right along the axial direction; A bearing (5) is disposed in the lubricating oil cavity (12), and the rotating shaft (2) is rotatably connected in the bearing (5); an oil-slinging plate (6) disposed between the sealing ring (4) and the bearing (5) and used for throwing lubricating oil into the lubricating oil chamber (12); an air chamber (61) is formed between the oil-slinging plate (6) and the sealing ring (4), an outlet of the air chamber (61) being disposed axially away from the bearing (5) and communicating with the lubricating oil chamber (12); The part of the grate ring (3) located on the relatively left side of the air-through hole (31) along the axial direction is configured as a first grate portion (32); and the part of the grate ring (3) located on the relatively right side of the air-through hole (31) along the axial direction is configured as a second grate portion (33); the gap between the tooth tip of the first grate portion (32) and the sealing ring (4) is communicated with the flow channel cavity (11); the gap between the tooth tip of the second grate portion (33) and the sealing ring (4) is communicated with the air cavity (61); the outer diameter of the first grate portion (32) is greater than the outer diameter of the second grate portion (33) to form a stepped structure.

2. A bearing cavity sealing structure according to claim 1, characterized in that: A horizontal ring (62) is protruded from one side of the oil-slinging plate (6) axially facing the sealing ring (4); the horizontal ring (62) covers the end of the sealing ring (4) facing the oil-slinging plate (6); the inner wall surface of the horizontal ring (62) and the outer peripheral surface of the sealing ring (4) form an outlet of the air cavity (61).

3. A bearing cavity sealing structure according to claim 2, characterized in that: A boss (41) is provided on the outer peripheral surface of the portion of the sealing ring (4) located inside the horizontal ring (62), and the outer wall of the boss (41) and the inner wall of the horizontal ring (62) form an outlet of the air cavity (61); the boss (41) is arranged obliquely along an end surface axially away from the oil-slinging plate (6), and is arranged radially away from the center of the sealing ring (4) and gradually approaches the oil-slinging plate (6); And / or, the outer diameter of the horizontal ring (62) is not less than the outer ring diameter of the raceway in the bearing (5) for placing the balls.

4. A bearing cavity sealing structure according to claim 2, characterized in that: An end of the oil-slinging plate (6) axially facing the bearing (5) is provided with an inclined surface (63), and the inclined surface (63) is arranged gradually away from the bearing (5) in a direction radially away from the center of the oil-slinging plate (6).

5. The bearing cavity sealing structure according to claim 1, characterized in that: The outer peripheral surface of the sealing ring (4) is fixedly connected to the casing (1) via a connecting portion (42); the connecting portion (42) is arranged obliquely and is arranged gradually approaching the bearing (5) in a radial direction away from the center of the sealing ring (4).

6. A bearing cavity sealing structure according to claim 5, characterized in that: The sealing ring (4) and the connecting portion (42) are integrally formed to form an integral structure.

7. A bearing cavity sealing structure according to claim 1, characterized in that: A guide arc groove (43) is recessed on the inner wall of the sealing ring (4) at a position corresponding to the air-through hole (31), and the guide arc groove (43) surrounds the inner wall in the circumferential direction.

8. A bearing cavity sealing structure according to claim 7, characterized in that: The inner diameter of the vent hole (22) is greater than the inner diameter of the air-through hole (31), and the size of the vent hole (22) is smaller than the size of the arc guide groove (43).

9. An aircraft engine, characterized in that: The bearing cavity sealing structure comprises the bearing cavity sealing structure as described in any one of claims 1 to 8 above.

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