Aero hydraulic pump shaft tail heat dissipation structure

Abstract

The utility model discloses an aviation hydraulic pump shaft tail heat radiation structure, including mounting seat, back cover and main shaft, mounting seat axiality is equipped with step hole, and the big hole of step hole is towards the inner chamber of pump, and the big hole in step hole is equipped with bearing, and back cover is fixed in the outside end of mounting seat, and main shaft passes through bearing and back cover, the small hole in step hole is equipped with mechanical seal and two O type sealing rings, and mechanical seal includes the tooth profile ring of connecting main shaft and the sealing ring of connecting back cover, and the outside of sealing ring is equipped with wave elastic pad, and one of O type sealing rings is located between sealing ring and back cover, and the other O type sealing ring is located between tooth profile ring and main shaft, and the inner wall on big hole is equipped with oil guide groove, and the both ends of oil guide groove are located bearing's thick direction both sides respectively. The utility model has can improve the advantage of pump shaft tail heat radiation capacity.

Description

Technical Field

[0001] This utility model belongs to the field of aviation hydraulic pumps, and in particular relates to a heat dissipation structure for the tail of an aviation hydraulic pump shaft. Background Technology

[0002] Currently, the tail structure of a high-power aviation hydraulic pump includes a mounting base and a main shaft passing through the mounting base. To ensure smooth rotation of the main shaft, a stepped hole is provided on the mounting base, with the larger hole of the stepped hole facing the inside of the hydraulic pump. A bearing is installed in the larger hole of the stepped hole, and the main shaft is connected to the mounting base through the bearing. To prevent hydraulic oil from leaking through the gap between the main shaft and the mounting base, a tail sealing mechanism is provided at the smaller end of the stepped hole.

[0003] Most existing shaft tail seal structures adopt a "mechanical seal + O-ring" structure. For example... Figure 1 As shown, the structure of the aviation hydraulic pump shaft tail includes a mounting base, a rear cover, and a main shaft. The mounting base has a stepped hole axially upward, with the larger hole facing the pump's inner cavity. A bearing is installed inside the larger hole of the stepped hole. The rear cover is fixed to the outer end of the mounting base, and the main shaft passes through the bearing and the rear cover. The sealing structure is located in the smaller hole of the stepped hole and includes a mechanical seal and two O-rings. The mechanical seal includes a toothed ring and a sealing ring. The toothed ring is mounted on the main shaft and rotates with it. The sealing ring is slidably connected to the rear cover. A corrugated spring washer is provided at the outer end of the sealing ring, which presses the sealing ring against the toothed ring. The toothed ring fits against the inner ring of the bearing, and a mechanical sealing surface is formed between the toothed ring and the sealing ring. One O-ring is located between the sealing ring and the rear cover, and the other O-ring is located between the toothed ring and the main shaft.

[0004] When a hydraulic pump is operating, the heat generated by mechanical friction is distributed within the pump chamber, causing the chamber temperature to rise. The confined space where the mechanical seal is installed hinders hydraulic oil circulation and is further obstructed by bearings, creating dead zones that impede heat dissipation from the pump shaft tail. Consequently, the temperature of the shaft tail seal structure is higher than other parts of the pump's interior. With increasing operating time, the O-ring seal ages more rapidly under localized high temperatures, leading to decreased sealing performance. The mechanical seal friction pair experiences accelerated wear, and the surface roughness and flatness of the working surface gradually exceed usage requirements, making it difficult to establish a stable lubricating oil film. All these factors combined result in excessive oil leakage from the hydraulic pump shaft tail seal. Utility Model Content

[0005] The purpose of this invention is to provide a heat dissipation structure for the tail of an aviation hydraulic pump shaft. This invention has the advantage of improving the heat dissipation capacity of the pump shaft tail.

[0006] The technical solution of this utility model is as follows: A heat dissipation structure for the tail of an aviation hydraulic pump includes a mounting base, a rear cover, and a main shaft. The mounting base has a stepped hole axially upward, with the larger hole of the stepped hole facing the inner cavity of the pump. A bearing is installed in the larger hole of the stepped hole. The rear cover is fixed to the outer end of the mounting base, and the main shaft passes through the bearing and the rear cover. A mechanical seal and two O-rings are installed in the smaller hole of the stepped hole. The mechanical seal includes a toothed ring connecting the main shaft and a sealing ring connecting the rear cover. A corrugated spring washer is provided on the outer side of the sealing ring. One O-ring is located between the sealing ring and the rear cover, and the other O-ring is located between the toothed ring and the main shaft. An oil guide groove is provided on the inner wall of the larger hole, with the two ends of the oil guide groove located on the thicker sides of the bearing.

[0007] In the aforementioned aviation hydraulic pump tail cooling structure, one end of the oil guide groove extends to the bottom surface of the stepped hole, and the other end of the oil guide groove extends to the outer end face of the large hole.

[0008] In the aforementioned cooling structure for the tail of the aviation hydraulic pump shaft, there are three oil guide grooves.

[0009] In the aforementioned aviation hydraulic pump tail cooling structure, the three oil guide grooves are evenly distributed circumferentially.

[0010] In the aforementioned aviation hydraulic pump shaft tail heat dissipation structure, the root of the oil guide groove is provided with an arc-shaped groove.

[0011] Compared with existing technologies, this invention adds an oil guide groove to the mounting base of the existing aviation hydraulic pump shaft tail. The two ends of the oil guide groove are located on both sides of the bearing's thickness, allowing for better communication and exchange between the oil in the dead zone of the shaft tail and the oil in the pump chamber. This removes heat from the shaft tail, improving heat dissipation, reducing wear on the mechanical seal, preventing rapid aging of the O-ring seal, and ensuring good sealing performance, thus avoiding excessive oil leakage at the shaft tail. Therefore, this invention has the advantage of improving the heat dissipation capacity of the pump shaft tail. Attached Figure Description

[0012] Figure 1 This is a front view structural diagram of this utility model.

[0013] Figure 2 This is the left view of the toothed ring.

[0014] Figure 3 This is a front view of the toothed ring.

[0015] Figure 4 This is a structural diagram of the mounting base.

[0016] The markings in the attached diagram are: 1-mounting base, 2-rear cover, 3-spindle, 4-stepped hole, 5-bearing, 6-O-ring seal, 7-toothed ring, 8-sealing ring, 9-wave spring washer, 10-large hole, 11-small hole, 12-oil guide groove, 13-arc groove. Detailed Implementation

[0017] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.

[0018] Example: A heat dissipation structure for the tail of an aviation hydraulic pump shaft, such as... Figure 1 As shown, the system includes a mounting base 1, a rear cover 2, and a main shaft 3. The mounting base 1 has a stepped hole 4 extending axially upwards. The larger hole 10 of the stepped hole 4 faces the inner cavity of the pump. A bearing 5 is installed inside the larger hole 10 of the stepped hole 4. The rear cover 2 is fixed to the outer end of the mounting base 1, and the main shaft 3 passes through the bearing 5 and the rear cover 2. A mechanical seal and two O-rings 6 are installed inside the smaller hole 11 of the stepped hole 4. The mechanical seal includes a toothed ring 7 connecting the main shaft 3 and a sealing ring 8 connecting the rear cover 2. A corrugated spring washer 9 is provided on the outer side of the sealing ring 8. One O-ring 6 is located between the sealing ring 8 and the rear cover 2, and the other O-ring 6 is located between the toothed ring 7 and the main shaft 3. Its features are as follows: The inner wall of the large hole 10 is provided with three circumferentially evenly distributed oil guide grooves 12. The two ends of the oil guide grooves 12 are located on the thick side of the bearing 5 respectively. One end of the oil guide groove 12 extends to the bottom surface of the stepped hole 4, and the other end of the oil guide groove 12 extends to the outer end face of the large hole 10.

[0019] Preferably, the root of the oil guide groove 12 is provided with an arc-shaped groove 13, one end of which is connected to the root of the oil guide groove 12, and the other end of which extends in the opposite direction of the rotation of the main shaft 3. The arc-shaped groove 13 can promote the communication of oil inside and outside the dead zone.

[0020] Working principle: In this embodiment, three oil guide grooves 12 are added to the mounting base 1 of the existing aviation hydraulic pump shaft tail. When the hydraulic pump is working, the main shaft drives the toothed ring 7 to rotate. The toothed ring 7 agitates the flow of oil at the shaft tail. The oil flows out of the "dead zone" of the shaft tail through the oil guide grooves 12, exchanges with the oil in the pump chamber, carries away heat, reduces the shaft tail temperature, improves the service life of the mechanical seal and O-ring seal, and avoids oil leakage at the shaft tail.

[0021] In the description of this utility model, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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. Therefore, they should not be construed as limitations on this utility model.

Claims

1. A cooling structure for the tail of an aviation hydraulic pump shaft, comprising a mounting base (1), a rear cover (2), and a main shaft (3), wherein the mounting base (1) is provided with a stepped hole (4) axially upward, the large hole (10) of the stepped hole (4) facing the inner cavity of the pump, a bearing (5) is provided in the large hole (10) of the stepped hole (4), the rear cover (2) is fixed to the outer end of the mounting base (1), and the main shaft (3) passes through the bearing (5) and the rear cover (2); a mechanical seal and two O-rings (6) are provided in the small hole (11) of the stepped hole (4), the mechanical seal comprising a toothed ring (7) connecting the main shaft (3) and a sealing ring (8) connecting the rear cover (2), a wave spring pad (9) is provided on the outer side of the sealing ring (8), one of the O-rings (6) is located between the sealing ring (8) and the rear cover (2), and the other O-ring (6) is located between the toothed ring (7) and the main shaft (3), characterized in that: An oil guide groove (12) is provided on the inner wall of the large hole (10), and the two ends of the oil guide groove (12) are located on the thick side of the bearing (5).

2. The heat dissipation structure for the tail of an aviation hydraulic pump shaft according to claim 1, characterized in that: One end of the oil guide groove (12) extends to the bottom surface of the stepped hole (4), and the other end of the oil guide groove (12) extends to the outer end face of the large hole (10).

3. The heat dissipation structure for the tail of an aviation hydraulic pump shaft according to claim 1, characterized in that: There are three oil guide grooves (12).

4. The heat dissipation structure for the tail of the aviation hydraulic pump shaft according to claim 3, characterized in that: The three oil guide grooves (12) are evenly distributed circumferentially.

5. The heat dissipation structure for the tail of an aviation hydraulic pump shaft according to claim 3, characterized in that: The root of the oil guide groove (12) is provided with an arc-shaped groove (13).

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