Self-adaptive angular deformation flexible lining structure between rotor and bearing of aero-engine

Abstract

The invention discloses a self-adaptive angular deformation flexible lining structure between a rotor and a bearing of an aero-engine, and belongs to the technical field of aero-engine supporting structure design. According to the structure, the flexible lining with the spherical matching characteristic is arranged between the shaft neck of the rotor and the bearing, and through the design of the inner boss, the outer boss and the thin wall, the flexible lining can be deformed in a limited mode under high-speed rotation and impact loads, self-adaption to inclined movement of the rotor is achieved, and the torque effect on the bearing and a base of the bearing is reduced. The flow of lubricating oil can be guided and controlled through the small holes in the flexible lining, damping is generated under the impact load, and axial and radial impact is buffered. The baffle is matched with the flexible lining to form an oil cavity, and oil supply, cooling and lubrication are achieved for the lower portion of the bearing ring in combination with the lubricating oil supply nozzle. Compared with a traditional rigid support, the structure can effectively solve the problem that the bearing is not centered due to bending deformation of the high-speed rotor, improves the reliability of the bearing, prolongs the service life of the bearing, can optimize the damping characteristic by designing the thin wall of the lining and the size of the oil through hole, and has the advantages of simple structure, good adaptability, safety and reliability.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine support structure design, in particular to an aircraft engine rotor-bearing adaptive angular deformation flexible bushing structure. Background Art

[0002] Aircraft gas turbines are the main power source for aircraft and other aircraft. In response to the increasingly urgent high-performance and high-reliability technical requirements of current and future aircraft power systems, the operating speed and working load of aircraft gas turbines are gradually increasing, and at the same time, they are increasingly lightweight. In previous aircraft engine design and analysis, due to the high structural rigidity and low speed, the rotor bending deformation is small, so many design measures are considered based on the assumption of rotor rigid motion. However, for advanced high-speed aircraft engines, the engine rotor system with thin-walled structural characteristics has significant flexibility in structure, and the increase in operating speed requires the rotor to pass through multiple critical speeds, and the rotational inertial excitation load is aggravated. These reasons all cause the rotor system to have non-negligible bending deformation during operation; in addition, affected by the complex and changeable flight state and extreme working conditions, there are also a variety of complex loads acting on the engine rotor system, such as the inertial impact loads generated by maneuvering, overload, hard landing and blade loss, which further makes the rotor bending deformation more complicated.

[0003] When the rotor is bent and deformed, especially when facing large impact loads caused by hard landing and blade loss, the rotor pivot has a significant tilt angle, resulting in misalignment between the inner and outer rings of the bearing, squeezing the bearing rollers and cages and causing damage and destruction to them; the tilt of the pivot will also cause the oil film damper at the engine rotor pivot to tilt, resulting in the failure of its damping function. Therefore, for the design of advanced high-speed aircraft engine rotors, it is necessary to adopt structural design measures that can adapt to angular deformation at the pivot to reduce the damage to the structure caused by the tilting movement of the pivot. Summary of the invention

[0004] The purpose of the present invention is to provide an adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing, which solves the problem of fulcrum tilting movement caused by the bending deformation of the high-speed rotor of the aircraft engine and the bearing misalignment caused by it.

[0005] To achieve the above-mentioned purpose, the present invention provides an adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing, comprising a rotor journal, a bearing, a bearing seat, a flexible bushing, a baffle, and a lubricating oil supply nozzle; The bearing outer ring is assembled on the bearing seat and axially fixed by an axial tightening nut; The lubricating oil supply nozzle is a part of the lubricating oil supply system of the engine, and is used to supply lubricating oil to the bearing and the flexible bushing; The flexible bushing is mounted on the rotor journal and has the characteristics of staggered arrangement of inner bosses and spherical outer bosses; A small hole is processed at the thin wall position of the flexible bushing to allow the lubricating oil to pass through; The baffle is installed on one axial side of the flexible bushing, and the baffle is positioned with the flexible bushing by tightening the round nut against the baffle; The baffle has an inwardly turned convex edge, which cooperates with the lubricating oil supply nozzle to throw the lubricating oil into the flexible bushing during rotation; The inner surface of the bearing inner ring is matched with the flexible bushing through a spherical pair, and the inner ring is processed with a second lower oil supply hole to throw the lubricating oil onto the bearing roller through centrifugal force.

[0006] Preferably, the bearing seat is installed on the bearing system of the aviation gas turbine; Preferably, the flexible bushing is mounted on the rotor journal, with one end of the flexible bushing resting on the shoulder of the rotor journal and the other end being the baffle. The flexible bushing and the baffle are axially positioned by tightening a round nut.

[0007] Preferably, the lubricating oil supply nozzle is installed on the stator system of the aircraft gas turbine to provide lubricating oil to the bearing cavity to play a role in lubrication and cooling; Preferably, the baffle has an inwardly turned flange and is processed with an oil hole 1. When the lubricating oil supply nozzle sprays lubricating oil, the lubricating oil flows outward under the action of centrifugation. Restricted by the flange, the lubricating oil accumulates at the flange and flows into the gap of the inner boss of the flexible bushing through the oil hole; a small hole 1 is processed on the thin wall of the flexible bushing, which enables the lubricating oil to flow into the gap of the outer boss under the action of centrifugation. The inner ring of the bearing is also processed with an oil hole 2. The lubricating oil further flows into the bearing roller under the action of centrifugal force, thereby realizing the lubricating oil supply to the bearing under the ring; Preferably, the flexible bushing and the bearing are matched through a spherical pair, so that the angular constraint between the two is relatively low. When the rotor is relatively tilted relative to the bearing seat, the flexible bushing and the bearing can be easily angularly deformed relative to each other through the spherical pair, thereby realizing self-adaptation to the angular tilt deformation of the rotor; Preferably, the outer boss of the flexible bushing isolates the circumferential flow of the lubricating oil, and the structure of the flexible bushing makes it flexible when subjected to radial load. The small hole 1 on the flexible bushing can not only throw the lubricating oil into the bearing, but also squeeze or suck the lubricating oil into the small hole 1 when the rotor is subjected to impact or other types of radial loads and the flexible bushing is deformed, thereby generating a damping effect and reducing the impact of the impact on the bearing and the bearing seat; As an optimization, a circumferential small hole No. 2 can be processed on the inner boss of the flexible bushing. When the lubricating oil is subjected to centrifugal action, it does not flow through the circumferential small hole No. 2. However, when subjected to other types of radial loads such as impact, the lubricating oil is deformed and squeezed by the flexible bushing and can flow in the circumferential small hole No. 2 to enhance the anti-impact damping effect. The size of the small hole No. 2 can be reasonably designed to achieve optimal adjustment of the flow damping.

[0008] Therefore, the present invention adopts an aero-engine rotor-bearing adaptive angular deformation flexible bushing structure of the above structure, which has the following beneficial effects: (1) Since it can adapt to the tilting motion deformation characteristics of the high-speed rotor at the fulcrum position, the torque acting on the bearing and the bearing seat is greatly reduced, reducing bearing damage and the impact on the bearing seat damper.

[0009] (2) The present invention can utilize the small holes on the thin wall of the flexible bushing to control the flow rate of the bearing lubricating oil.

[0010] (3) The flexible bushing in the present invention cooperates with the lubricating oil to have an impact resistance effect, further reducing the damage to the bearing and the bearing seat when subjected to impact loads, thereby improving the safety of the structural system.

[0011] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of an adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing according to the present invention; Figure 2 is a schematic diagram of the flexible bushing structure used in the first embodiment; Figure 3 is a schematic diagram of the flexible bushing structure used in the second embodiment; Reference numerals 1. Rotor journal, 2. Bearing, 3. Axial tightening nut, 4. Bearing seat, 5. Flange flanging, 6. Bearing outer ring, 7. Bolts, 8. Bearing inner ring, 9. Oil hole 2, 10. Spherical pair, 11. Baffle, 12. Oil hole, 13. Lubricating oil supply nozzle, 14. Flange, 15. Flexible bushing, 16. Oil sealing O-ring, 17. Inner boss, 18. Flexible bushing thin-walled section, 19. Small hole 1, 20. Outer boss, 21 Small hole 2. DETAILED DESCRIPTION

[0013] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0014] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0015] Example 1 like Figure 1 As shown, an adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing of the present invention comprises a rotor journal 1, a bearing 2, an axial tightening nut 3, a bearing seat 4, a baffle 11, a lubricating oil supply nozzle 13, a flexible bushing 15, and an oil sealing O-ring 16.

[0016] The rotor journal 1 is a part of the rotor structure of the aircraft gas turbine and is used to assemble and fix the rotor structure.

[0017] The bearing outer ring 6 is mounted on the bearing seat 4 via a flange 5 and bolts 7 .

[0018] The flexible bushing 15 is installed on the rotor journal 1, and an oil-sealing O-ring 16 is provided at one end thereof, and rests on the shoulder of the rotor journal 1; at the other end of the flexible bushing 15 is a baffle 11, and the tightening action of the round nut 3 makes the baffle 11 press against the circumferential end face of the flexible bushing 15 and transmits axial force to the flexible bushing 15, thereby realizing the axial positioning of the flexible bushing 15 and the baffle 11.

[0019] The inner ring of the bearing 2 is mounted on the flexible bushing, and the outer ring is mounted on the bearing seat 4. The load on the rotor can be transmitted from the journal 1 through the flexible bushing 15 to the bearing 2, then to the bearing seat 4, and further to the load-bearing system to realize the external transmission of the load.

[0020] like Figure 1 and Figure 2The main body of the flexible bushing 15 is a thin-walled annular structure, and a plurality of inner bosses 17 and outer bosses 20 are alternately processed on the inner and outer cylindrical surfaces. Among them, the surface of the inner boss 17 is a cylindrical surface, which cooperates with the rotor shaft neck 1 to transmit radial force and achieve positioning; the surface of the outer boss 20 is a spherical surface, which cooperates with the inner surface of the inner ring of the bearing 2 which is also a spherical surface to form a spherical pair 10, and the spherical pair 10 is used to transmit radial loads and axial loads, and to achieve axial and radial positioning of the bearing.

[0021] In the mating state, several inner bosses of the flexible bushing 15, the cylindrical surface and shoulder end surface of the rotor shaft neck 1, and the baffle 11 together constitute several inner oil chambers that are not directly connected; several outer bosses of the flexible bushing 15 and the inner surface of the inner ring of the bearing 2 together constitute several outer oil chambers that are not directly connected.

[0022] The lubricating oil supply nozzle 13 is a part of the lubrication system and is installed on the stator system of the aircraft gas turbine to provide lubricating oil to the bearing cavity to play a role in lubrication and cooling.

[0023] The baffle 11 has an inward-turned flange 14 and is machined with an oil hole 12. When the lubricating oil supply nozzle 13 sprays lubricating oil, the lubricating oil flows outward under the action of centrifugation. Restricted by the flange 14, the lubricating oil accumulates at the flange 14 and flows into the gap of the inner boss of the flexible bushing 15 through the oil hole 12. A small hole 19 is machined on the thin wall of the flexible bushing 15, which enables the lubricating oil to flow into the gap of the outer boss under the action of centrifugation. An oil hole 9 is also machined on the inner ring of the bearing 2. The lubricating oil further flows into the roller of the bearing 2 under the action of centrifugal force, thereby realizing the lubricating oil supply to the under-ring of the bearing 2.

[0024] Since the flexible bushing 15 and the bearing 2 are matched through the spherical pair 10, the angular constraint between the two is relatively low. When the rotor shaft neck 1 is relatively tilted relative to the bearing seat 4, the flexible bushing 15 and the bearing 2 can easily produce relative angular deformation through the spherical pair 10, thereby realizing self-adaptation to the angular tilt deformation of the rotor.

[0025] The structure of the flexible bushing 15 has a number of bosses that are staggered inside and outside, so that it has flexible characteristics when subjected to radial loads. The small hole 19 thereon not only throws the lubricating oil into the bearing through the bearing inner ring 8 with the oil supply hole, but also can squeeze or suck the lubricating oil into the small hole when the thin-walled section 18 of the flexible bushing is squeezed and deformed by the inner boss 17 and the outer boss 20 when the rotor is subjected to impact or other types of radial loads, thereby producing a damping effect and reducing the impact of the impact on the bearing and the bearing seat.

[0026] The flexible bushing 15 is matched with the bearing 2 via a spherical pair 10 , so that when the rotor tilts relative to the bearing seat 4 , the flexible bushing 15 is allowed to produce angular deformation relative to the bearing 2 and adapt to the tilting movement of the high-speed rotor.

[0027] When the spherical outer boss 20 of the flexible bushing 15 cooperates with the inner spherical ring pair 10 of the bearing 2, the axial and radial clearances can be reasonably configured according to the design to allow larger angular deformation while ensuring the load-bearing capacity, thereby achieving self-adaptation to the misaligned motion of the high-speed rotor.

[0028] The shape of the flexible bushing 15 and the number and size of the small holes 19 and the small holes 21 can be adjusted according to the structure and working conditions of the aircraft engine, so as to optimize the load-bearing capacity, lubrication performance and impact damping characteristics.

[0029] Example 2 like Figure 3 A circumferential small hole 21 can be machined on the inner boss of the flexible bushing 15. When the lubricating oil is subjected to centrifugal force, it does not flow through the small hole 21. However, when subjected to other types of radial loads such as impact, the lubricating oil is deformed and squeezed by the flexible bushing and can flow in the circumferential small hole to enhance the anti-impact damping effect. The size of this small hole can be reasonably designed to achieve optimal adjustment of the flow damping.

[0030] Therefore, the present invention adopts the above-mentioned flexible bushing structure with adaptive angular deformation between the rotor and the bearing of an aircraft engine. By arranging a bearing bushing with a spherical mating surface between the rotor and the bearing, the fulcrum structure has the ability to adaptively tilt the angular direction of the rotor bending deformation. Moreover, through the unique flexible design features, the flexible bushing has flexible deformation characteristics when subjected to loads such as rotation and impact, thereby reducing the radial force and torque transmitted to the bearing.

[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. An adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing, characterized in that: include: Rotor journal, used to assemble and fix the rotor structure of the aviation gas turbine; A bearing, the inner ring of which is mounted on a flexible bushing and the outer ring of which is mounted on a bearing seat; The bearing seat is fixedly installed on the bearing system of the aviation gas turbine; A flexible bushing is mounted on the rotor journal, and the flexible bushing has a plurality of inner bosses and a plurality of outer bosses; A baffle is installed on one axial side of the flexible bushing, and is pressed against the baffle by a round nut to transmit axial force to the flexible bushing to achieve axial positioning; The lubricating oil supply nozzle is installed on the stator system of the aircraft gas turbine and is used to supply lubricating oil to the bearings and flexible bushings.

2. The adaptive angular deformation flexible bushing structure between the rotor and the bearing of an aircraft engine according to claim 1, characterized in that: The flexible bushing is a thin-walled annular structure, and the inner bosses and the outer bosses are arranged alternately in the circumferential direction to form a plurality of inner oil chambers and outer oil chambers that are not directly connected.

3. The adaptive angular deformation flexible bushing structure between the rotor and the bearing of an aircraft engine according to claim 1, characterized in that: The inner boss surface is a cylindrical surface, which cooperates with the rotor journal to transmit radial load and achieve positioning; The surface of the outer boss is a spherical surface, which cooperates with the spherical pair in the bearing to transmit radial load and axial load and realize axial and radial positioning of the bearing.

4. The adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing according to claim 1, characterized in that: A plurality of small holes 1 are processed at the thin-walled position of the flexible bushing, or a plurality of small holes 2 are processed along the circumferential direction on the inner boss of the flexible bushing; Small hole 1 is used to distribute the lubricating oil under the action of centrifugal force and to produce damping effect when subjected to radial impact load; The lubricating oil does not flow through the small hole 2 during normal operation. However, when subjected to impact or other types of radial loads, the lubricating oil flows through the small hole 2 due to the deformation and squeezing of the flexible bushing and further improves the damping effect.

5. The adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing according to claim 1, characterized in that: The baffle is provided with an inwardly turned flange, and the flange is provided with an oil hole. When the lubricating oil supply nozzle sprays lubricating oil, the lubricating oil flows outward under the action of centrifugal force and is blocked by the flange. The lubricating oil then enters the oil cavity in the flexible bushing through the oil hole.

6. The adaptive angular deformation flexible bushing structure between the rotor and the bearing of an aircraft engine according to claim 4, characterized in that: When relative angular deformation occurs between the flexible bushing and the bearing, the flexible bushing generates limited elastic deformation under the impact load and realizes damping through the flow of oil in the first or second small hole, thereby reducing the damage to the bearing and the bearing seat caused by impact or overload.

7. The adaptive angular deformation flexible bushing structure between the rotor and the bearing of an aircraft engine according to claim 4, characterized in that: The shape of the flexible bushing and the number and size of the first or second small holes are adjusted according to the structure and working condition requirements of the aircraft engine.

8. The adaptive angular deformation flexible bushing structure between an aircraft engine rotor and a bearing according to claim 2, characterized in that: The inner ring of the bearing is processed with two oil holes, which are connected with the outer oil cavity formed circumferentially by the outer boss. Lubricating oil can enter the roller of the bearing under the centrifugal force to realize oil supply under the ring.

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