Graphite sealing structure for aero-engine bearing cavity

Abstract

The utility model relates to a graphite sealing structure for an aero-engine bearing cavity, which comprises a bearing shell and a graphite inner sleeve, and is characterized in that the graphite inner sleeve consists of an upper sleeve section, a lower sleeve section and a middle lantern ring section; an upper annular positioning seat is arranged at the upper end of the bearing shell, an upper sealing ring is arranged in the upper annular positioning seat, an upper annular gland is arranged above the upper annular positioning seat, an upper annular groove is formed in the upper surface of the upper sealing ring, an upper pressing ring is embedded in the upper annular groove, and an upper spring compensation assembly is arranged between the upper pressing ring and the upper annular gland; a lower annular supporting seat is arranged at the lower end of the bearing shell, a lower sealing ring is arranged in the lower annular supporting seat, a lower annular gland is arranged below the lower annular supporting seat, a lower annular groove is formed in the lower surface of the lower sealing ring, a lower pressing ring is embedded in the lower annular groove, and a lower spring compensation assembly is arranged between the lower pressing ring and the lower annular gland. Under the condition that the supporting effect is guaranteed, the damaged graphite supporting structure is convenient to disassemble and replace, cost is saved, the sealing effect is good, and the service life is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of graphite bearings, in particular to a graphite sealing structure for an aero-engine bearing cavity. Background Art

[0002] Aerospace engine bearings, located between the high- and low-pressure rotors in an aeroengine's sealed structure, are typically made of graphite. To balance strength and lubrication, inlaid graphite bearings are often used. However, when the internal graphite of inlaid graphite bearings becomes severely worn, the entire bearing structure must be replaced, wasting resources.

[0003] Based on this, CN 221257439 U discloses a graphite sealing structure for an aeroengine bearing cavity. The structure comprises a top plate and a bottom plate, with a bearing mechanism disposed between the top and bottom plates. The bearing mechanism is used to reduce the frictional resistance of the shaft. The bearing mechanism comprises a bearing housing and a bearing inner ring. The inner side of the bearing housing is provided with a slide groove and a spring receiving groove, a second spring is installed in the spring receiving groove, and a sliding tooth is fixedly connected to the outer side of the bearing inner ring. This graphite sealing structure uses a spring-driven method to replenish graphite loss. Compared with traditional inlaid graphite bearings, it can more fully utilize graphite for self-lubrication. At the same time, a detachable design is adopted to achieve the effect of replaceable graphite columns. However, the following problems still exist: 1. If a large number of graphite columns are used, the support strength of the bearing inner ring is affected due to the large number of openings. If a small number of graphite columns are used, the use effect of the graphite bearing cannot be achieved. 2. After the inner circumference of the sealing ring is worn, the contact with the shaft is not tight, which shortens the service life. Utility Model Content

[0004] The purpose of the utility model is to provide a graphite sealing structure for an aircraft engine bearing cavity that is structurally reasonable and reliable in use to solve the above-mentioned problems. While ensuring the supporting effect, the damaged graphite supporting structure can be easily disassembled and replaced, thereby achieving the purpose of saving costs, while ensuring the sealing effect of the sealing ring and extending its service life.

[0005] The technical solution of the utility model is:

[0006] A graphite sealing structure for an aircraft engine bearing cavity comprises a bearing housing and a graphite inner sleeve arranged on the inner periphery of the bearing housing. The technical key points are as follows: the graphite inner sleeve is composed of an upper sleeve section fixed to the upper part of the bearing housing, a lower sleeve section fixed to the lower part of the bearing housing, and a multi-section intermediate sleeve section clamped between the upper sleeve section and the lower sleeve section; an upper annular positioning seat is supported on the outer edge of the upper end of the bearing housing, an upper sealing ring is provided inside the upper annular positioning seat and is concentric with the upper annular positioning seat, an upper annular pressure cover is buckled above the upper annular positioning seat, an upper surface of the upper sealing ring is provided with an upper annular groove concentric with the upper annular positioning seat, and a cross-section of the upper annular groove is substantially the same as that of the upper annular positioning seat. The surface is a trapezoid that is wide at the top and narrow at the bottom, and an upper pressure ring that matches its shape is embedded in the upper ring groove, and a plurality of upper spring compensation components are provided between the upper surface of the upper pressure ring and the upper annular pressure cover; a lower annular support seat is provided on the outer edge of the lower end of the bearing housing, and a lower sealing ring concentric with it is provided inside the lower annular support seat, and a lower annular pressure cover is buckled under the lower annular support seat, and the lower surface of the lower sealing ring is provided with a lower annular groove concentric with it, and the cross-section of the lower annular groove is a trapezoid that is narrow at the top and wide at the bottom, and a lower pressure ring that matches its shape is embedded in the lower ring groove, and a plurality of lower spring compensation components are provided between the lower surface of the lower pressure ring and the lower annular pressure cover.

[0007] The above-mentioned graphite sealing structure for the bearing cavity of an aircraft engine has a flange plate at the upper end of the upper sleeve section, a flange plate at the lower end of the lower sleeve section, and an annular groove corresponding to the flange plate is provided on the upper and lower end surfaces of the bearing housing respectively. The lower surface of the upper sealing ring is in close contact with the upper end surface of the bearing housing and the flange plate, and the upper surface of the lower sealing ring is in close contact with the lower end surface of the bearing housing and the flange plate.

[0008] The above-mentioned graphite sealing structure for the bearing cavity of an aircraft engine is characterized in that the upper sleeve section and the outer peripheries of the opposite ends of the adjacent intermediate ring section are plugged in and fitted with each other using a convex-concave structure, the outer peripheries of the opposite ends of two adjacent intermediate ring sections are plugged in and fitted with each other using a convex-concave structure, and the lower sleeve section and the outer peripheries of the opposite ends of the adjacent intermediate ring section are plugged in and fitted with each other using a convex-concave structure.

[0009] The above-mentioned graphite sealing structure for the aircraft engine bearing cavity has radial positioning screws corresponding to the upper sleeve section, the lower sleeve section and the middle collar section on the outer peripheral wall of the bearing housing, and two adjacent radial positioning screws in the vertical direction are staggered.

[0010] The above-mentioned graphite sealing structure for the aircraft engine bearing cavity, the outer periphery of the upper annular positioning seat and the upper annular pressure cover is provided with an upper annular plate that fits together, the outer periphery of the lower annular support seat and the lower annular pressure cover is provided with a lower annular plate that fits together, and a fixing component is provided between the upper annular plate and the lower annular plate, and the number of the fixing components is multiple and evenly distributed around the center line of the bearing housing.

[0011] The above-mentioned graphite sealing structure for the bearing cavity of an aircraft engine, the fixing assembly includes a fixing column, an upper screw and a lower screw arranged at the upper and lower ends of the fixing column, an upper gasket arranged at the root of the upper screw, a lower gasket arranged at the root of the lower screw, an upper locking nut and an upper fixing nut arranged on the upper screw, a lower locking nut and a lower fixing nut arranged on the lower screw, the upper annular plate is provided with a through hole corresponding to the upper screw, the upper annular plate is clamped between the upper gasket and the upper locking nut, the lower annular plate is provided with a through hole corresponding to the lower screw, and the lower annular plate is clamped between the lower gasket and the lower locking nut.

[0012] The beneficial effects of the utility model are:

[0013] 1. The upper sleeve section, the lower sleeve section and the multi-section intermediate ring section are used to form the graphite inner sleeve. The assembly direction will not affect the supporting strength of the bearing housing. At the same time, the contact area with the shaft is increased, which enhances the use effect. If there is a worn position, the corresponding upper sleeve section, lower sleeve section or intermediate ring section can be replaced to save the use cost.

[0014] 2. Easy to assemble, disassemble and repair.

[0015] 3. During operation, the upper and lower sealing rings are pressed by the upper and lower spring compensation components, and the upper and lower pressure rings extend into the upper and lower ring grooves, causing the inner circumferences of the upper and lower sealing rings to shrink and come into close contact with the shaft, avoiding loose sealing due to wear, ensuring sealing effect, and extending service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is an axial cross-sectional view of the utility model;

[0017] Figure 2 It is a schematic diagram of the external structure of the utility model.

[0018] In the figure: 1. upper screw, 2. upper fixing nut, 3. upper locking nut, 4. upper annular plate, 5. upper gasket, 6. upper annular locating seat, 7. fixing column, 8. radial positioning screw, 9. bearing housing, 10. intermediate collar section, 11. lower sleeve section, 12. lower gasket, 13. lower annular plate, 14. lower locking nut, 15. lower fixing nut, 16. lower screw, 17. lower annular support seat, 18. lower annular pressure cover, 19. lower spring compensation assembly, 20. lower pressure ring, 21. lower sealing ring, 22. upper sleeve section, 23. upper sealing ring, 24. upper annular pressure cover, 25. upper spring compensation assembly, 26. upper pressure ring. DETAILED DESCRIPTION

[0019] The utility model is described in detail according to the accompanying drawings.

[0020] like Figure 1 、 Figure 2 As shown, the graphite sealing structure for the bearing cavity of an aircraft engine includes a bearing housing 9 and a graphite inner sleeve arranged on the inner periphery of the bearing housing 9.

[0021] The graphite inner sleeve is composed of an upper sleeve section 22 fixed to the upper portion of the bearing housing 9, a lower sleeve section 11 fixed to the lower portion of the bearing housing 9, and a multi-section intermediate collar section 10 clamped between the upper sleeve section 22 and the lower sleeve section 11. In this embodiment, radial positioning screws 8 corresponding to the upper sleeve section 22, the lower sleeve section 11, and the intermediate collar section 10 are provided on the outer peripheral wall of the bearing housing 9, with adjacent radial positioning screws 8 arranged alternately in the vertical direction.

[0022] The outer edge of the upper end of the bearing housing 9 supports an upper annular positioning seat 6, and an upper sealing ring 23 concentric with the upper annular positioning seat 6 is provided inside the upper annular positioning seat 6. An upper annular pressure cover 24 is buckled on the upper annular positioning seat 6, and the upper surface of the upper sealing ring 23 is provided with an upper annular groove concentric with the upper annular groove. The cross-section of the upper annular groove is a trapezoid that is wide at the top and narrow at the bottom. An upper pressure ring 26 matching its shape is embedded in the upper annular groove, and a plurality of upper spring compensation components 25 are provided between the upper surface of the upper pressure ring 26 and the upper annular pressure cover 24. A lower annular support seat 17 is provided on the outer edge of the lower end of the bearing housing 9, and a lower sealing ring 21 concentric with the lower annular support seat 17 is provided inside the lower annular support seat 17. A lower annular pressure cover 18 is fastened below the lower annular support seat 17, and the lower surface of the lower sealing ring 21 is provided with a lower annular groove concentric with the lower annular groove. The cross-section of the lower annular groove is a trapezoid that is narrow at the top and wide at the bottom. A lower pressure ring 20 matching its shape is embedded in the lower annular groove, and a plurality of lower spring compensation components 19 are provided between the lower surface of the lower pressure ring 20 and the lower annular pressure cover 18.

[0023] In this embodiment, a flange is provided at the upper end of the upper sleeve section 22, and a flange is provided at the lower end of the lower sleeve section 11. Annular grooves corresponding to the flanges are respectively provided on the upper and lower end surfaces of the bearing housing 9. The lower surface of the upper sealing ring 23 is in close contact with the upper end surface and flange of the bearing housing 9, while the upper surface of the lower sealing ring 21 is in close contact with the lower end surface and flange of the bearing housing 9. The upper sleeve section 22 and the outer periphery of the opposite ends of the adjacent intermediate collar section 10 are plugged together using a convex-concave structure. The outer peripheries of the opposite ends of two adjacent intermediate collar sections 10 are plugged together using a convex-concave structure. The lower sleeve section 11 and the outer periphery of the opposite ends of the adjacent intermediate collar section 10 are plugged together using a convex-concave structure.

[0024] The outer periphery of the upper annular positioning seat 6 and the upper annular pressure cover 24 is provided with an upper annular plate 4 that fits together, and the outer periphery of the lower annular support seat 17 and the lower annular pressure cover 18 is provided with a lower annular plate 13 that fits together. A fixing component is provided between the upper annular plate 4 and the lower annular plate 13, and the number of the fixing components is 4, which are evenly distributed around the center line of the bearing housing 9. In this embodiment, the fixing assembly includes a fixing column 7, an upper screw 1 and a lower screw 16 provided at the upper and lower ends of the fixing column 7, an upper gasket 5 provided at the root of the upper screw 1, a lower gasket 12 provided at the root of the lower screw 1, an upper locking nut 3 and an upper fixing nut 2 provided on the upper screw 1, a lower locking nut 14 and a lower fixing nut 15 provided on the lower screw 16, the upper annular plate 4 is provided with a through hole corresponding to the upper screw 1, the upper annular plate 4 is clamped between the upper gasket 5 and the upper locking nut 3, the lower annular plate 13 is provided with a through hole corresponding to the lower screw 16, and the lower annular plate 13 is clamped between the lower gasket 12 and the lower locking nut 14.

[0025] Working principle:

[0026] During assembly, first secure the lower sleeve section 11 to the lower portion of the bearing housing 9, then stack the intermediate collar sections 10 and upper sleeve section 22 on top of them, and finally secure them using the radial positioning screws 8. The upper and lower sealing rings 23 and 21, the upper and lower pressure rings 26 and 20, and the upper and lower annular glands 21 and 18 with the upper and lower spring compensation assemblies 25 and 19 are then assembled and secured using the four securing assemblies.

[0027] The above detailed description of the embodiments of the present invention is intended to be a preferred embodiment of the present invention and should not be construed as limiting the scope of implementation of the present invention. Any equivalent changes and improvements made within the scope of the present invention shall still fall within the scope of this patent.

Claims

1. A graphite sealing structure for an aircraft engine bearing cavity, comprising a bearing housing and a graphite inner sleeve arranged on the inner periphery of the bearing housing, characterized in that: The graphite inner sleeve is composed of an upper sleeve section fixed to the upper part of the bearing housing, a lower sleeve section fixed to the lower part of the bearing housing, and a multi-section intermediate sleeve ring section clamped between the upper sleeve section and the lower sleeve section; the outer edge of the upper end of the bearing housing supports an upper annular positioning seat, an upper sealing ring concentric with the upper annular positioning seat is provided inside the upper annular positioning seat, an upper annular pressure cover is buckled on the upper annular positioning seat, an upper ring groove concentric with the upper sealing ring is provided on the upper surface of the upper sealing ring, the cross section of the upper ring groove is a trapezoidal shape with a width at the top and a narrowness at the bottom, and an upper ring matching its shape is embedded in the upper ring groove. A pressure ring, a plurality of upper spring compensation components are provided between the upper surface of the upper pressure ring and the upper annular pressure cover; a lower annular support seat is provided on the outer edge of the lower end of the bearing housing, a lower sealing ring concentric with the lower annular support seat is provided inside the lower annular support seat, a lower annular pressure cover is buckled under the lower annular support seat, and a lower annular groove concentric with the lower surface of the lower sealing ring is provided, and the cross-section of the lower annular groove is a trapezoid that is narrow at the top and wide at the bottom, and a lower pressure ring matching its shape is embedded in the lower annular groove, and a plurality of lower spring compensation components are provided between the lower surface of the lower pressure ring and the lower annular pressure cover.

2. The graphite sealing structure for an aircraft engine bearing cavity according to claim 1, characterized in that: The upper end of the upper sleeve section is provided with a flange, and the lower end of the lower sleeve section is provided with a flange. The upper and lower end surfaces of the bearing housing are respectively provided with annular grooves corresponding to the flanges. The lower surface of the upper sealing ring is in close contact with the upper end surface of the bearing housing and the flange, and the upper surface of the lower sealing ring is in close contact with the lower end surface of the bearing housing and the flange.

3. The graphite sealing structure for an aircraft engine bearing cavity according to claim 1, characterized in that: The upper sleeve section and the outer periphery of the opposite ends of the adjacent intermediate ring section are plugged in and matched with each other using a convex-concave structure, the outer peripheries of the opposite ends of the two adjacent intermediate ring sections are plugged in and matched with each other using a convex-concave structure, and the lower sleeve section and the outer periphery of the opposite ends of the adjacent intermediate ring section are plugged in and matched with each other using a convex-concave structure.

4. The graphite sealing structure for an aircraft engine bearing cavity according to claim 1, characterized in that: The outer peripheral wall of the bearing housing is provided with radial positioning screws corresponding to the upper sleeve section, the lower sleeve section and the middle collar section, and two adjacent radial positioning screws in the vertical direction are arranged alternately.

5. The graphite sealing structure for an aircraft engine bearing cavity according to claim 1, characterized in that: The outer periphery of the upper annular positioning seat and the upper annular pressure cover is provided with an upper annular plate that fits together, the outer periphery of the lower annular support seat and the lower annular pressure cover is provided with a lower annular plate that fits together, and a fixing component is provided between the upper annular plate and the lower annular plate. The number of the fixing components is multiple and evenly distributed around the center line of the bearing housing.

6. The graphite sealing structure for an aircraft engine bearing cavity according to claim 5, characterized in that: The fixing assembly includes a fixing column, an upper screw and a lower screw provided at the upper and lower ends of the fixing column, an upper gasket provided at the root of the upper screw, a lower gasket provided at the root of the lower screw, an upper locking nut and an upper fixing nut provided on the upper screw, a lower locking nut and a lower fixing nut provided on the lower screw, the upper annular plate is provided with a through hole corresponding to the upper screw, the upper annular plate is clamped between the upper gasket and the upper locking nut, the lower annular plate is provided with a through hole corresponding to the lower screw, and the lower annular plate is clamped between the lower gasket and the lower locking nut.

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