High-overload-resistant squeeze film damper and aero-engine

Abstract

The invention discloses a high overload resistant squeeze film damper and an aero-engine. An oil film gap in the squeeze film damper structure provides a vibration reduction function for the rotor in conventional flight. In the low overload state, the anti-maneuvering overload damper structure does not work, when the aero-engine conducts high maneuvering overload, the radial change of the elastic support is too large, the anti-maneuvering overload damper structure provides elastic support for the elastic support, and the vibration reduction effect of a rotor system of the extrusion oil film damper structure under the high maneuvering overload condition is further improved. Under the condition that the working state of a squeeze film damper in conventional flight is not changed, the high maneuvering overload resisting capacity of an aero-engine rotor system can be improved only by adding the maneuvering overload resisting damper structure.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, and more particularly, to an anti-high-overload squeeze film damper and an aero-engine. BACKGROUND

[0002] The maneuverability is an important tactical performance index of an aircraft, and good maneuverability can bring excellent air combat and penetration capability to the aircraft. Compared with manned aircraft, unmanned aerial vehicles do not need to consider the human tolerance limit for limiting the maneuvering overload, so the unmanned aerial vehicles have great potential in improving the maneuverability. At present, the maximum overload of the domestic and world mainstream fighter aircrafts (such as J-10, F22, etc.) is -3g / +9g, and by greatly improving the maneuverability of the unmanned aerial vehicle, the maneuvering overload of the future unmanned aerial vehicle will be far more than +9g, which puts higher requirements on the rotor power characteristics and stability of the unmanned aerial vehicle. As the power system of the unmanned aerial vehicle, the aero-engine needs to adapt to the high overload generated by the high maneuvering flight of the unmanned aerial vehicle, especially the higher requirements on the stability of the rotor system of the aero-engine.

[0003] The squeeze film damper is widely used in the rotor system of the aero-engine due to its simple structure and good damping effect. However, for the aircrafts such as unmanned aerial vehicles which need to fly at high maneuvering, the squeeze film damper may have the problems of insufficient stiffness leading to rotor eccentric instability, insufficient oil supply, and finally causing the oil film to break and the squeeze film damper to fail under the condition of large maneuvering overload. The elasticity of the existing squeeze film damper cannot be adjusted, so it cannot meet the high overload use requirement of the aero-engine. SUMMARY

[0004] The present application overcomes the deficiencies of the prior art in terms of anti-high-overload, and provides an anti-high-overload squeeze film damper and an aero-engine, so as to solve the problems existing in the prior art.

[0005] To solve the above technical problems, one aspect of the present application provides an anti-high-overload squeeze film damper:

[0006] An anti-high-overload squeeze film damper, comprising a squeeze film damper and an anti-overload damper.

[0007] The squeeze film damper comprises a damper mounting structure and a damper, and the damper is mounted on the damper mounting structure.

[0008] An oil supply pipeline is arranged on the damper mounting structure, and the oil supply pipeline is connected with an oil film gap.

[0009] The oil film gap is connected with an anti-overload damper mounting position, and the anti-overload damper is mounted in the anti-overload damper mounting position.

[0010] The squeeze oil film damper of the present application can adopt any existing squeeze oil film damper structure, in which the oil film gap provides the damping function of the rotor in normal flight, and the anti-maneuver overload damper structure does not work and does not affect the normal operation of the squeeze oil film damper in the case of high overload.

[0011] When the aero-engine is subjected to high maneuvering overload, the anti-overload damper mounting position changes too much in the radial direction, and the anti-maneuver overload damper structure provides elastic support for the elastic support, further improving the damping effect of the squeeze oil film damper structure on the rotor system under high maneuvering overload.

[0012] The present application can improve the ability of the aero-engine rotor system to resist high maneuvering overload by only adding an anti-maneuver overload damper structure without changing the working state of the squeeze oil film damper in normal flight.

[0013] Further technical solutions are that the anti-overload damper is an elastic structure.

[0014] The anti-overload damper includes a support positioning structure and an overload damper, the support positioning structure is used to limit the circumferential rotation of the anti-overload damper, and the overload damper is a damper under high maneuvering overload.

[0015] Further technical solutions are that the cross section of the support positioning structure is wave-shaped, and the overload damper is a damper ring with a wave-shaped cross section.

[0016] The peak position of the wave shape of the support positioning structure is higher than the peak position of the wave shape of the overload damper.

[0017] The anti-overload damper mounting position is a convex shape, and the support positioning structure is clamped at the high point position of the convex shape.

[0018] Further technical solutions are that the squeeze oil film damper includes an elastic support and an oil film outer ring.

[0019] The elastic support and the oil film outer ring form an oil film gap therebetween.

[0020] The elastic support and the oil film outer ring are provided with a through oil film hole.

[0021] Further technical solutions are that the squeeze oil film damper further includes a spiral and a bearing.

[0022] The spiral is used to fix the damper mounting structure and the damper.

[0023] The bearing is installed inside the damper.

[0024] A further technical solution is that the elastic support is cylindrical, and the screw ring is fitted inside the elastic support;

[0025] The bearing is installed inside the elastic support and abuts against the screw ring. The bearing and the elastic support are installed with a small gap.

[0026] A further technical solution is that one end of the elastic support is a flange edge, and the other end is a bearing seat;

[0027] The bearing housing is provided with a limit structure, and the flange edge is fixed to the damper mounting structure.

[0028] A further technical solution is that the elastic support is divided into an upper part and a lower part;

[0029] The upper part of the elastic support is installed in contact with the screw ring and the bearing, and the lower part is the remaining part;

[0030] The upper part is provided with a number of windows, and the multiple windows are distributed at intervals along the circumference of the elastic support to form an elastic support area;

[0031] The lower part is provided with a through oil film hole.

[0032] In another aspect, the present invention also provides an aircraft engine.

[0033] An aircraft engine including a high-overload resistant squeeze film damper as described above.

[0034] Compared with the prior art, the present invention has at least the following beneficial effects: the oil film gap in the extrusion oil film damper structure provides vibration reduction for the rotor during normal flight. Under low overload conditions, the anti-maneuvering overload damper structure does not operate. When the aero-engine undergoes high maneuvering overload, the radial change of the elastic support is excessive. The anti-maneuvering overload damper structure provides elastic support for the elastic support, further improving the vibration reduction effect of the extrusion oil film damper structure on the rotor system under high maneuvering overload conditions. The present invention improves the aero-engine rotor system's resistance to high maneuvering overload simply by adding an anti-maneuvering overload damper structure, without changing the operating state of the extrusion oil film damper during normal flight. Attached Figure Description

[0035] Figure 1 A side-view cross-section of an extrusion-resistant oil film damper designed to withstand high overload.

[0036] Figure 2 Side view cross-section of a squeeze film damper designed to withstand high overload.

[0037] In the diagram, 1-squeeze oil film damping structure, 11-damper installation structure, 111-oil supply pipeline, 12-squeeze oil film damper, 121-elastic support, 1211-flange edge, 1212-bearing housing, 122-oil film outer ring, 123-thread ring, 124-bearing, 2-overload damper, 21-support and positioning structure, 22-overload damper. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0039] Example 1

[0040] A high overload resistant extrusion oil film damper 12 includes an extrusion oil film damping structure 1 and an overload resistant damper 2.

[0041] The extrusion oil film damping structure 1 includes a damper mounting structure 11 and an extrusion oil film damper 12, wherein the extrusion oil film damper 12 is mounted on the damper mounting structure 11.

[0042] The damper mounting structure 11 is provided with an oil supply pipe 111, which is connected to the oil film gap.

[0043] The oil film gap is connected to the overload damper 2 mounting position, and the overload damper 2 is installed in the overload damper 2 mounting position.

[0044] In this embodiment, the overload damper 2 is an elastic structure.

[0045] The overload damper 2 includes a support and positioning structure 21 and an overload damper 22. The support and positioning structure 21 is used to limit the circumferential rotation of the overload damper 2, and the overload damper 22 is a damper for high-mobility overload conditions.

[0046] The cross-section of the support and positioning structure 21 is waveform, and the overload damper 22 is a damping ring with a waveform cross-section;

[0047] The peak position of the waveform of the support positioning structure 21 is higher than the peak position of the overload damper 22.

[0048] The overload damper 2 is mounted in a convex shape, with the support and positioning structure 21 snapped into the high point of the convex shape.

[0049] For example, the overload damper 22 is composed of damping rings. During installation, the damping rings are sequentially placed into the mounting position of the anti-overload damper 2 to form the complete anti-motor overload damper 22.

[0050] In this embodiment, the overload damper 2 is mounted between the damper mounting structure 11 and the squeeze oil film damper 12.

[0051] It is understandable that the extrusion film damper 12 can be any existing type of extrusion film damper 12, and any existing extrusion film damper 12 can provide better shock absorption under high overload conditions after the addition of the overload damper 2.

[0052] This application uses an oil film gap and an overload damper 2 mounting position connection, which does not require changing the original fuel supply method of the aero engine, nor does it require changing the original oil film gap.

[0053] Applying the overload damper 2 within the originally confined internal space of an aero-engine can improve its damping without altering the external dimensions of the existing compression oil film damping structure 1. Furthermore, by modifying the structure and clearance of the anti-maneuvering overload damper 22, its anti-maneuvering overload capability can be effectively enhanced. Moreover, the anti-maneuvering overload damper 22 has a simple structure, requiring no external structures or devices. Its elastic structure is regular and simple, and the sheet metal processing is not difficult.

[0054] In this embodiment, the squeeze oil film damper 12 includes an elastic support 121, an oil film outer ring 122, a screw ring 123, and a bearing 124.

[0055] An oil film gap is formed between the outer diameter of the elastic support 121 and the outer ring 122 of the oil film.

[0056] The elastic support 121 and the outer ring 122 of the oil film are provided with through oil film holes.

[0057] For example, the elastic support 121 is columnar, and the screw ring 123 is fitted inside the elastic support 121;

[0058] The bearing 124 is installed inside the elastic support 121 and abuts against the screw ring 123. The bearing 124 and the elastic support 121 are installed with a small gap.

[0059] Specifically, one end of the elastic support 121 is a flange edge 1211, and the other end is a bearing seat 1212;

[0060] The bearing 124 seat 1212 is provided with a limiting structure, and the flange edge 1211 is fixed to the damper mounting structure 11.

[0061] For example, the flange edge 1211 is detachably connected to the damper mounting structure 11 by bolts.

[0062] In a preferred embodiment, the oil film gap is 0.1 mm to 0.2 mm, and the gap between the anti-overload damper 2 and the elastic support 121 is slightly larger than the oil film gap. Regarding the setting of the oil film gap, in order to prevent the anti-maneuvering overload damper 22 from affecting normal flight, the gap between the anti-maneuvering overload damper 22 and the elastic support 121 should be larger than the oil film gap;

[0063] Meanwhile, in order to prevent the anti-motor overload damper 22 from failing to work under motor overload conditions, the gap between the anti-motor overload damper 22 and the elastic support 121 cannot be too large. Therefore, the gap between the anti-motor overload damper 22 and the elastic support 121 is required to be 0.22mm to 0.25mm.

[0064] The screw ring 123 is used to fix the damper mounting structure 11 and the damper;

[0065] The bearing 124 is installed inside the damper.

[0066] The elastic support 121 is divided into an upper part and a lower part;

[0067] The upper part of the elastic support 121 is installed in contact with the screw ring 123 and the bearing 124, and the lower part is the remaining part;

[0068] The upper part is provided with a number of windows, and the multiple windows are distributed at intervals along the circumference of the elastic support 121 to form an elastic support area;

[0069] The upper part of the elastic support 121 has several windows spaced apart in the circumferential direction. There are ribs between two adjacent windows. The multiple circumferentially arranged ribs form an elastic support area, which provides elastic support for the axial direction of the elastic support 121, thereby realizing vibration reduction in the axial direction of the elastic support 121.

[0070] The lower part is provided with a through oil film hole.

[0071] In this embodiment, the bearing 124 is mounted on the bearing 124 seat 1212 with a small clearance. The inner ring of the elastic support 121 is threaded, and the threaded ring 123 is screwed into the thread to abut against the bearing 124, fixing the bearing 124. The threaded ring 123 is detachably connected via the thread. With this configuration, the conventional damper mounting structure 11 stably achieves dual axial and radial positioning.

[0072] During installation, lubricating oil is injected into the outer ring 122 of the oil film from the oil supply pipe 111, forming an oil film gap between the outer ring 122 and the elastic support 121. Excess lubricating oil flows out from the oil film hole, and a small amount of lubricating oil flows into the mounting position of the anti-motor overload damper 22.

[0073] Because the space between the anti-motor overload damper 22 support positioning structure 21 and the anti-motor overload damper 22 is large, an oil film gap will not be formed in the anti-motor overload damper 22 to affect the conventional damper.

[0074] Under low overload conditions, the anti-maneuvering overload damper 22 structure does not operate. When the aero-engine undergoes high maneuvering overload, the radial change of the elastic support 121 is too large. The anti-maneuvering overload damper 22 structure provides elastic support for the elastic support 121, further improving the vibration reduction effect of the squeeze oil film damper 12 structure on the rotor system under high maneuvering overload conditions.

[0075] Example 2

[0076] An aircraft engine including a high-overload resistant squeeze film damper as described above.

[0077] Although the invention has been described herein with reference to illustrative embodiments, it should be understood that many other modifications and implementations can be devised by those skilled in the art, which will fall within the scope and spirit of the principles disclosed herein. More specifically, various variations and modifications can be made to the components and / or layout of the subject matter combination within the scope of this disclosure. Besides variations and modifications to the components and / or layout, other uses will be apparent to those skilled in the art.

Claims

1. A squeeze film damper resistant to high g-loads, characterized by, The extrusion oil film damping structure comprises a damper mounting structure and an extrusion oil film damper mounted on the damper mounting structure. An oil supply pipeline is arranged on the damper mounting structure and connected with the oil film gap. The oil film gap is connected with an anti-overload damper mounting position, and the anti-overload damper is mounted in the anti-overload damper mounting position. The anti-overload damper is an elastic structure.

2. A squeeze film damper for resisting high g-loads as in claim 1, wherein, The anti-overload damper comprises a support positioning structure for limiting the circumferential rotation of the anti-overload damper and an overload damper. The support positioning structure has a wave-shaped cross section, and the overload damper is a damping ring with a wave-shaped cross section.

3. A squeeze film damper for resisting high g-loads as defined in claim 2 wherein, The wave peak position of the support positioning structure is higher than the wave peak position of the overload damper. The anti-overload damper mounting position is a convex shape, and the support positioning structure is clamped at the high point position of the convex shape. The extrusion oil film damper comprises an elastic support and an oil film outer ring.

4. A squeeze film damper for resisting high g-loads according to any one of claims 1-3, wherein, An oil film gap is formed between the outer diameter of the elastic support and the oil film outer ring. An oil film hole is arranged on the elastic support and the oil film outer ring. The extrusion oil film damper further comprises a coil and a bearing.

5. A squeeze film damper for resisting high g-loads as defined in claim 4 wherein, The coil is used to fix the damper mounting structure and the damper. The bearing is mounted inside the damper. The elastic support is columnar, and the coil is sleeved inside the elastic support.

6. A squeeze film damper for resisting high g-loads as in claim 5, wherein, The bearing is mounted inside the elastic support and abuts against the coil. The bearing and the elastic support are installed with a small gap.

7. A squeeze film damper for resisting high g-loads as in claim 4, wherein, One end of the elastic support is a flange, and the other end is a bearing seat. The bearing seat is provided with a limiting structure, and the flange is fixed with the damper mounting structure.

8. A squeeze film damper for resisting high g-loads as in claim 4, wherein, The elastic support is divided into an upper part and a lower part. The upper part of the elastic support is in contact with the coil and the bearing, and the lower part is the remaining part. The upper part is provided with a plurality of windows, and the windows are distributed along the circumference of the elastic support to form an elastic support area. The lower part is provided with an oil film hole.

9. An aeroengine characterised in that, The extrusion oil film damper of any one of claims 1-8 is used for resisting high overload.

Images