A bearing spring support for an aeroengine

Abstract

The utility model discloses a bearing elastic support of aero -engine belongs to aero -engine technical field, including the outer support box, the one end of outer support box is provided with monitoring mechanism, and the inner wall of outer support box is provided with a plurality of internal thread seat, and the inner chamber sleeve of outer support box is provided with elastic ring seat, and the middle part of elastic ring seat is provided with the inner sleeve hole, in the utility model, through the elastic ring seat of the inner chamber sleeve of outer support box, utilize the inner sleeve hole in the inside of elastic ring seat to support the support bearing, and set up the cross stop mechanism of elastic plate and steel plate on the both sides of inner sleeve hole cavity, and the both sides of support bearing are limited, and the extrusion force of rotating body pivot to support bearing is directly conducted to elastic ring seat, plays the role of elastic support, and the elastic ring seat of annular structure can realize the support of support bearing in different radial direction, and reduces the abrasion.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, and more specifically, to an elastic bearing support for an aero-engine. Background Technology

[0002] An aircraft engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers the aircraft's flight but also serves as a crucial driving force for the development of the aviation industry. Every major transformation in the history of human aviation has been inseparable from the technological advancements in aircraft engines. The rotating parts in an engine require the support of bearings, which are typically mounted on bearing supports.

[0003] A search revealed a utility model patent with publication number CN217029683U, which discloses an elastic bearing support for an aero-engine, comprising an outer ring, a support ring, an inner ring, and a drive device. The outer ring is fixedly connected to an external engine. A support ring is fixedly mounted on the inner wall of the outer ring, and an inner ring is fixedly mounted on the inner side of the support ring. The inner ring is sleeved on the engine's drive shaft. A drive device is located on one side of the support ring, outside the inner ring, and fixed to the inner wall of the outer ring. This patent uses a drive device to move a drive rod, causing the force-bearing ring to be supported on the inner ring, thereby sharing the force borne by the support ring and adjusting the rigidity of the support component. Through two opposing hydraulic mechanisms, the force-bearing rings in the horizontal or vertical directions can be selectively driven, thereby elastically adjusting the rigidity of the support component.

[0004] However, the above patent still has the following shortcomings: using multiple hydraulic mechanisms to support the inner ring, when the inner ring is subjected to radial pressure, the inner ring will squeeze one of the hydraulic mechanisms; wear will occur between the force-bearing rings on the two hydraulic mechanisms and the inner ring wall, reducing the service life of the elastic support; secondly, when the elastic support fails, it is not convenient to notify the crew to replace it in a timely manner. Therefore, we propose an elastic support for the bearing of an aero-engine. Utility Model Content

[0005] In view of the problems existing in the prior art, the purpose of this utility model is to provide an elastic bearing support for aero-engines.

[0006] To solve the above problems, the present invention adopts the following technical solution: an elastic bearing support for an aero-engine, comprising an outer support box, a monitoring mechanism at one end of the outer support box, multiple internal thread seats on the inner wall of the outer support box, an elastic annular seat fitted inside the inner cavity of the outer support box, an inner sleeve hole in the middle of the elastic annular seat, a crossbar mechanism fitted at both ends of the inner cavity of the inner sleeve hole, a support bearing fitted inside the inner cavity of the inner sleeve hole and inside the two crossbar mechanisms, a second external through hole at one end of the inner cavity of the outer support box, a box cover fitted at the other end of the inner cavity of the outer support box, multiple countersunk holes on the side of the box cover, internal hexagon screws fitted inside the cavities of the multiple countersunk holes, the ends of the multiple internal hexagon screws being threaded to the inner side of the internal thread seat, a first external through hole in the middle of the box cover, and multiple internal slots on the inner wall of the inner sleeve hole.

[0007] As a preferred embodiment of this utility model, the monitoring mechanism includes multiple mounting seats fixedly connected to one end of the outer support box. Pressure sensors are fixedly mounted on the multiple mounting seats respectively. Telescopic cylinders are fixedly connected to the detection ends of the multiple pressure sensors. Air rods are fixedly installed in the inner cavities of the multiple telescopic cylinders. Telescopic columns are fixedly connected to the ends of the multiple air rods. Rolling balls are sleeved on the ends of the telescopic columns.

[0008] As a preferred embodiment of this utility model, the crossbar mechanism includes two elastic plates and a steel plate sleeved in the inner cavity of the inner sleeve hole. The steel plate is fixedly sleeved on the inner side of the two elastic plates. A first inner through hole is provided in the middle of the elastic plate, and a second inner through hole is provided in the middle of the steel plate. The inner diameter of the second inner through hole is larger than the inner diameter of the first inner through hole. Multiple locking blocks are provided on the sides of both the steel plate and the elastic plates. The ends of the locking blocks are movably sleeved into the inner cavity of the inner locking groove.

[0009] As a preferred embodiment of this utility model, the outer side of the elastic annular seat is provided with a plurality of external slots, the external slots are sleeved on the outer side of the internal thread seat, the side of the internal thread seat is in contact with the inner wall of the external slots, and the outer side of the elastic annular seat is in contact with the inner wall of the outer support box.

[0010] In a preferred embodiment of this utility model, the inner diameter of the inner sleeve hole is equal to the outer diameter of the supporting bearing, the elastic plate, and the steel plate, respectively, and the outer diameter of the box cover is equal to the inner diameter of the outer support box.

[0011] In a preferred embodiment of this utility model, the second outer perforation, the first outer perforation, the first inner perforation, the second inner perforation, and the support bearing are arranged concentrically.

[0012] Compared with the prior art, the advantages of this utility model are: (1) In this utility model, by fitting an elastic ring seat into the inner cavity of the outer support box, the support bearing is supported by the inner sleeve hole on the inner side of the elastic ring seat. At the same time, a cross-stop mechanism composed of an elastic plate and a steel plate is set on both sides of the inner cavity of the inner sleeve hole to limit the two sides of the support bearing. The squeezing force of the rotating shaft on the support bearing is directly transmitted to the elastic ring seat, which plays the role of elastic support. Moreover, the elastic ring seat with the ring structure can support the support bearing in different radial directions and reduce wear.

[0013] (2) In this utility model, when the elastic ring seat and elastic plate are squeezed by the support bearing and the rotating shaft, they will wear out. When the elastic support of the elastic ring seat and elastic plate is about to fail, the rotating shaft will shift and contact a ball. The ball is under pressure, causing the telescopic column to contract into the inner cavity of the telescopic cylinder. At this time, the squeezing force of the telescopic cylinder is detected by the pressure sensor. The pressure detected by the pressure sensor is transmitted to the control room of the aircraft so as to remind the staff to replace the elastic ring seat and the crossbar mechanism in time, thus realizing the function of monitoring the elastic support of the bearing. Attached Figure Description

[0014] Figure 1 is a schematic diagram of the overall structure of the front of this utility model.

[0015] Figure 2 is a schematic diagram of the overall structure of the back of this utility model.

[0016] Figure 3 is an exploded view of the overall structure of this utility model.

[0017] Figure 4 is a schematic diagram of the crossbar mechanism of this utility model.

[0018] Figure 5 is a cross-sectional schematic diagram of the telescopic cylinder of this utility model.

[0019] The following are the labels in the diagram: 1. Outer support box; 2. Internal threaded seat; 3. Elastic ring seat; 4. External groove; 5. Inner sleeve hole; 6. Support bearing; 7. Crossbar mechanism; 8. Monitoring mechanism; 9. Box cover; 10. Countersunk hole; 11. Socket head screw; 12. Second external through hole; 13. First external through hole; 14. Mounting base; 15. Pressure sensor; 16. Telescopic cylinder; 17. Air rod; 18. Telescopic column; 19. Ball bearing; 20. Elastic plate; 21. Steel plate; 22. First internal through hole; 23. Second internal through hole; 24. Locking block; 25. Internal groove. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0021] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" 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 an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. Example 1

[0023] As shown in Figures 1 to 5, a bearing elastic support for an aero-engine includes an outer support box 1, which is fixedly connected to an external engine. A monitoring mechanism 8 is provided at one end of the outer support box 1. Multiple internally threaded seats 2 are provided on the inner wall of the outer support box 1. An elastic annular seat 3 is fitted inside the inner cavity of the outer support box 1. An inner sleeve hole 5 is provided in the middle of the elastic annular seat 3. A crossbar mechanism 7 is fitted at both ends of the inner cavity of the inner sleeve hole 5. A support bearing 6 is fitted inside the inner cavity of the inner sleeve hole 5 and inside the two crossbar mechanisms 7. A second external through hole 12 is provided at one end of the inner cavity of the outer support box 1. A box cover 9 is fitted at the other end of the inner cavity of the outer support box 1. The inner surface of the box cover 9 fits against the end face of the elastic annular seat 3 to ensure the elastic annular seat 3 is fixed. Multiple countersunk holes 10 are provided on the side of the box cover 9. Hexagon socket screws 11 are fitted into the inner cavities of the multiple countersunk holes 10. The ends of all are threaded to the inner side of the internal thread seat 2. Spring washers and flat washers are fitted on the internal hexagonal screws 11. A first external through hole 13 is provided in the center of the cover 9. Multiple internal slots 25 are provided on the inner wall of the inner sleeve hole 5. The crossbar mechanism 7 includes two elastic plates 20 and a steel plate 21 fitted into the inner cavity of the inner sleeve hole 5. Both the elastic ring seat 3 and the elastic plates 20 are supported by natural rubber. The elastic plates 20 and the steel plate 21 are vulcanized and bonded. The steel plate 21 is fixedly fitted onto the inner side of the two elastic plates 20. A first internal through hole 22 is provided in the center of the elastic plate 20. A second internal through hole 23 is provided in the center of the steel plate 21. The inner diameter of the second internal through hole 23 is larger than the inner diameter of the first internal through hole 22. Multiple locking blocks 24 are provided on the sides of both the steel plate 21 and the elastic plates 20. The ends of the locking blocks 24 are movably fitted into the inner cavity of the internal slots 25. The outer side of the crossbar mechanism 7 fits against the inner wall of the inner groove 25 to ensure the stability of the crossbar mechanism 7 when it is fitted into the inner cavity of the inner sleeve hole 5. The inner sides of the other two crossbar mechanisms 7 fit against the two sides of the outer ring of the support bearing 6. Example 2

[0024] Based on Embodiment 1, as shown in Figures 1, 2, and 5, the monitoring mechanism 8 includes multiple mounting seats 14 fixedly connected to one end of the outer support box 1. The mounting seats 14 are evenly arranged circumferentially around the axial direction of the outer support box 1. Pressure sensors 15 are fixedly mounted on each mounting seat 14. Telescopic cylinders 16 are fixedly connected to the detection ends of each pressure sensor 15. Air rods 17 are fixedly mounted inside the inner cavities of each telescopic cylinder 16. Telescopic columns 18 are fixedly connected to the ends of each air rod 17. Ball bearings 19 are fitted onto the ends of each telescopic column 18. The outer diameter of the telescopic column 18 is equal to the inner diameter of the telescopic cylinder 16, ensuring the stability of the telescopic column 18 within the inner cavity of the telescopic cylinder 16. Furthermore, the ball bearings 19 are located on the side of the second outer perforation 12 and do not contact the rotating shaft passing through the inner cavity of the second outer perforation 12. Additionally, the pressure sensors 15... The wiring at the tail end connects to the controller and power supply in the aircraft equipment; this is a standard circuit connection and will not be elaborated further. Example 3

[0025] Based on Embodiments 1 and 2, as shown in Figures 1 to 4, the outer side of the elastic annular seat 3 is provided with multiple outer slots 4. The outer slots 4 are fitted onto the outer side of the internal thread seat 2. The side of the internal thread seat 2 is in contact with the inner wall of the outer slots 4. The cooperation between the internal thread seat 2 and the outer slots 4 ensures the stability of the elastic annular seat 3 fitted into the inner cavity of the outer support box 1. The outer side of the elastic annular seat 3 is in contact with the inner wall of the outer support box 1, ensuring the stability of the elastic annular seat 3 fitted into the inner cavity of the outer support box 1. The inner diameter of the inner sleeve hole 5 is equal to the outer diameter of the support bearing 6, the elastic plate 20, and the steel plate 21, respectively, ensuring the stability of the support bearing 6, the elastic plate 20, and the steel plate 21 fitted into the inner cavity of the inner sleeve hole 5. The outer diameter of the box cover 9 is equal to the inner diameter of the outer support box 1, ensuring the stability of the box cover 9 fitted into the inner cavity of the outer support box 1. The second outer through hole 12, the first outer through hole 13, the first inner through hole 22, and the second inner through hole 23 are also provided. The support bearing 6 is arranged concentrically to ensure that the rotating shaft of the engine can pass through the inner cavity of the second outer through hole 12, the first outer through hole 13, the first inner through hole 22, and the second inner through hole 23. The inner diameter of the inner ring of the support bearing 6 is equal to the inner diameter of the first inner through hole 22, so that the elastic plate 20 can provide auxiliary support for the rotating shaft.

[0026] It should be noted that this utility model is a bearing elastic support for an aero-engine. In use, firstly, the elastic annular seat 3 is fitted into the inner cavity of the outer support box 1, and the outer slot 4 is fitted into the outer side of the internal thread seat 2. Then, the box cover 9 and a crossbar mechanism 7 composed of an elastic plate 20 and a steel plate 21 are fitted into the outer side of the engine rotating body shaft. Next, another crossbar mechanism 7 composed of an elastic plate 20 and a steel plate 21 is fitted into the inner sleeve hole 5 on the inner side of the elastic annular seat 3, and the locking block 24 is fitted into the inner cavity of the inner slot 25. Additionally, the support bearing 6 is fitted into the outer side of the engine rotating body shaft. Then, the end of the engine rotating body shaft is inserted into the inner cavity of the outer support box 1, and the end of the shaft protrudes from the second outer through hole 12. At this point, the support bearing 6 is fitted into the elastic annular seat 3. The inner sleeve hole 5 on the inner side is used to fit the crossbar mechanism 7 on the outer side of the rotating shaft into the inner sleeve hole 5 of the inner cavity of the elastic ring seat 3. The box cover 9 on the outer side of the rotating shaft is fitted into the inner cavity of the outer support box 1. The box cover 9 is installed in the inner cavity of the outer support box 1 by using the cooperation of the internal hexagon screw 11, the countersunk hole 10 and the internal thread seat 2. At the same time, the elastic ring seat 3, the crossbar mechanism 7 and the support bearing 6 fitted in the inner cavity of the outer support box 1 are fixed. Finally, the elastic ring seat 3 is used to support the radial direction of the support bearing 6, and the two crossbar mechanisms 7 are used to support the axial direction of the support bearing 6. As the elastic ring seat 3 is pressured and wears, the rotating shaft of the engine rotating body moves to the side. The rotating shaft will squeeze a ball 19. The ball 19 squeezes the air rod 17 and compresses it. At the same time, the tail end of the air rod 17 squeezes the telescopic cylinder 16. The pressure detected by the pressure sensor 15 changes so as to transmit the signal to the control room so as to replace the elastic ring seat 3 and the crossbar mechanism 7 in time.

[0027] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model based on the technical solution and its improved concept should be covered within the protection scope of the present utility model.

Claims

1. A bearing elastic support for an aero-engine, comprising an outer support box (1), characterized in that: A monitoring mechanism (8) is provided at one end of the outer support box (1). Multiple internal thread seats (2) are provided on the inner wall of the outer support box (1). An elastic annular seat (3) is fitted inside the inner cavity of the outer support box (1). An inner sleeve hole (5) is provided in the middle of the elastic annular seat (3). A crossbar mechanism (7) is fitted at both ends of the inner cavity of the inner sleeve hole (5). A support bearing (6) is fitted inside the inner cavity of the inner sleeve hole (5) and on the inner side of the two crossbar mechanisms (7). The inner cavity of the outer support box (1)... One end is provided with a second external through hole (12), and the other end of the inner cavity of the outer support box (1) is fitted with a box cover (9). The side of the box cover (9) is provided with multiple countersunk holes (10), and the inner cavity of each of the multiple countersunk holes (10) is fitted with an internal hexagon screw (11). The ends of the multiple internal hexagon screws (11) are threaded to the inner side of the internal thread seat (2). The middle of the box cover (9) is provided with a first external through hole (13), and the inner wall of the inner sleeve hole (5) is provided with multiple internal slots (25).

2. The bearing elastic support for an aero-engine according to claim 1, characterized in that: The monitoring mechanism (8) includes multiple mounting bases (14) fixedly connected to one end of the outer support box (1). Pressure sensors (15) are fixedly installed on the multiple mounting bases (14). Telescopic cylinders (16) are fixedly connected to the detection ends of the multiple pressure sensors (15). Air rods (17) are fixedly installed in the inner cavities of the multiple telescopic cylinders (16). Telescopic columns (18) are fixedly connected to the ends of the multiple air rods (17). Roller balls (19) are sleeved on the ends of the telescopic columns (18).

3. The bearing elastic support for an aero-engine according to claim 1, characterized in that: The crossbar mechanism (7) includes two elastic plates (20) and a steel plate (21) sleeved in the inner cavity of the inner sleeve hole (5). The steel plate (21) is fixedly sleeved on the inner side of the two elastic plates (20). A first inner through hole (22) is provided in the middle of the elastic plate (20), and a second inner through hole (23) is provided in the middle of the steel plate (21). The inner diameter of the second inner through hole (23) is larger than the inner diameter of the first inner through hole (22). Multiple locking blocks (24) are provided on the sides of both the steel plate (21) and the elastic plate (20). The ends of the locking blocks (24) are movably sleeved into the inner cavity of the inner locking groove (25).

4. The bearing elastic support for an aero-engine according to claim 1, characterized in that: The elastic ring seat (3) has multiple outer slots (4) on its outer side. The outer slots (4) are fitted on the outer side of the inner thread seat (2). The side of the inner thread seat (2) is in contact with the inner wall of the outer slots (4). The outer side of the elastic ring seat (3) is in contact with the inner wall of the outer support box (1).

5. The bearing elastic support for an aero-engine according to claim 3, characterized in that: The inner diameter of the inner sleeve hole (5) is equal to the outer diameter of the support bearing (6), the elastic plate (20), and the steel plate (21), respectively, and the outer diameter of the box cover (9) is equal to the inner diameter of the outer support box (1).

6. The bearing elastic support for an aero-engine according to claim 3, characterized in that: The second external perforation (12), the first external perforation (13), the first internal perforation (22), the second internal perforation (23) and the support bearing (6) are arranged concentrically.

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