Sealing structure for input shaft of steering oar

Abstract

The utility model relates to the technical field of input shafts of steering oars, and discloses a sealing structure for an input shaft of a steering oar, which comprises an upper gearbox shell, an input shaft bushing is arranged outside one end of the input shaft, and an input shaft sealing seat is arranged outside the input shaft bushing. A first input shaft sealing ring and a second input shaft sealing ring are arranged in the input shaft sealing seat, a distance ring is arranged between the first input shaft sealing ring and the second input shaft sealing ring, one end of the distance ring is connected with an input shaft sealing pipe connector through an oil groove, and the input shaft sealing pipe connector is connected with a gravity oil tank through an oil pipe. By arranging the gravity oil tank, original oil injection lubrication is changed into oil immersion lubrication, the working condition of the sealing ring is improved, the service life of the sealing ring is prolonged, meanwhile, a single-channel sealing ring is changed into a double-channel sealing ring, the risk of sealing failure is reduced, pollution to the environment is reduced, maintenance is convenient, the maintenance period is shortened, and the service life of the sealing ring is prolonged. And the economic loss caused by maintenance is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of azimuth propeller input shafts, in particular to a sealing structure for azimuth propeller input shafts. Background Art

[0002] The azimuth rudder propeller device has excellent maneuverability and dynamic positioning functions, and can adapt to the actual needs of offshore auxiliary production operations. Therefore, the azimuth rudder propeller device is widely used on offshore platform engineering vessels.

[0003] The sealing structure of an azimuth propeller system is a core system. This seal not only affects the proper operation of the azimuth propeller system, but also the safety and environmental impact of the entire vessel. Failure of the seal renders the entire azimuth propeller system inoperable, hindering navigation, but also polluting the environment with leaked lubricating oil, resulting in financial losses for the shipowner.

[0004] The sealing structure of an azimuth propeller system is mainly divided into two parts: dynamic seals and static seals. Generally, lubricating oil leakage mainly occurs in the dynamic seal. The dynamic seal of an azimuth propeller system is mainly divided into three parts: the input shaft dynamic seal, the steering shaft dynamic seal, and the propeller shaft dynamic seal.

[0005] Feedback from a large number of actual ship operations indicates that the risk of leakage at the input shaft dynamic seal is higher than at the rudder dynamic seal and propeller shaft seal. Although leakage at the input shaft dynamic seal is generally small, the lubricating oil will not directly contaminate the seawater and no docking maintenance is required, but maintenance still requires shutdown before operation, which will also cause certain economic losses.

[0006] In view of the existing related technologies, the inventors believe that the following defects exist: the sealing ability of the input shaft sealing ring depends on the thickness of the oil film on the sealing surface. If the thickness is too large, the sealing ring will leak; if the thickness is too small, dry friction may occur, causing wear of the sealing ring and the bushing; if there is no oil film between the sealing ring lip and the bushing, it is easy to cause heat and wear; at the same time, the full-rotation propeller input shaft sealing ring adopts oil spray lubrication, and the oil film thickness is difficult to control, which is prone to heat and wear, resulting in a small amount of oil leakage; and the existing input shaft seals generally use single-channel sealing rings. Once damaged during installation and use, the risk of lubricating oil leakage will be greatly increased. Utility Model Content

[0007] In order to solve the technical problem that the sealing ability of the existing input shaft sealing ring depends on the thickness of the oil film on the sealing surface, if the thickness is too large, the sealing ring will leak; if the thickness is too small, dry friction may occur, causing wear of the sealing ring and the bushing, the utility model provides a sealing structure for the input shaft of the full-rotation propeller.

[0008] The utility model is implemented by the following technical solutions: a sealing structure for an omni-rotating propeller input shaft, comprising an upper gearbox housing, a spherical roller bearing is arranged inside the upper gearbox housing, the spherical roller bearing fixes the input shaft, an input shaft bushing is arranged on the outside of one end of the input shaft, an input shaft sealing seat is arranged on the outside of the input shaft bushing, the input shaft sealing seat is fixedly connected to the upper gearbox housing by bolts, a first input shaft sealing ring and a second input shaft sealing ring are arranged inside the input shaft sealing seat, a spacer ring is arranged between the first input shaft sealing ring and the second input shaft sealing ring, one end of the spacer ring is connected to the input shaft sealing pipe joint through an oil groove, the input shaft sealing pipe joint is connected to the gravity oil tank through an oil pipe, and a locking nut is provided at one end of the input shaft bushing.

[0009] Preferably, a first O-ring is provided on the outside of the upper gearbox housing, and one side of the first O-ring is in contact with one side of the input shaft sealing seat.

[0010] Preferably, a second O-ring is provided inside the input shaft bushing, and one side of the second O-ring is in contact with the outside of the input shaft.

[0011] Preferably, the inner side of the first input shaft sealing ring fits with the outer side of the input shaft bushing, and the outer side of the first input shaft sealing ring fits with the inner side of the input shaft sealing seat.

[0012] Preferably, the inner side of the second input shaft sealing ring fits with the outer side of the input shaft bushing, and the outer side of the second input shaft sealing ring fits with the inner side of the input shaft sealing seat.

[0013] Preferably, a pressure cover is provided on one side of the second input shaft sealing ring, and the pressure cover is fixedly connected to the outside of the input shaft sealing seat by bolts.

[0014] Preferably, an oil drain plug is provided at the other end of the input shaft seal seat, and an oil groove at one end of the oil drain plug is communicated with the interior of the spacer ring.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] When the utility model is in use, the original oil spray lubrication is changed to oil immersion lubrication under the action of the gravity oil tank, thereby improving the working conditions of the sealing ring and extending the service life of the sealing ring. At the same time, the single-channel sealing ring is changed to a double-channel sealing ring, which reduces the risk of sealing failure and reduces pollution to the environment. The optimized structure is easy to maintain, shortens the maintenance cycle, and reduces the economic losses caused by maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1This is a schematic diagram of the input shaft dynamic seal structure of the utility model;

[0018] Figure 2 For the utility model Figure 1 Enlarged schematic diagram of part A in the middle.

[0019] In the figure: 1. Upper gearbox housing; 2. Spherical roller bearing; 3. Input shaft; 4. Input shaft bushing; 5. First O-ring; 6. Input shaft seal seat; 7. First input shaft seal ring; 8. Second O-ring; 9. Lock nut; 10. Oil drain plug; 11. Second input shaft seal ring; 12. Spacer ring; 13. Gland; 14. Input shaft sealing pipe joint; 15. Gravity oil tank. DETAILED DESCRIPTION

[0020] The existing sealing structure is divided into two parts: dynamic seal and static seal. The static seal is mainly composed of two O-rings, and the dynamic seal is mainly composed of the input shaft bushing, the input shaft seal seat, and the input shaft seal ring 1. During operation of the azimuth propeller device, the oil level in the upper gearbox drops, and the input shaft seal ring can only be lubricated and cooled by spraying. However, the input speed of the azimuth propeller input shaft is generally high, and the linear velocity at the contact point between the seal ring and the input shaft bushing is high. Under the action of the seal ring's own spring, the wear between the seal ring lip and the hardened layer of the input shaft bushing will be intensified, resulting in seal failure.

[0021] The present invention is further described in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form new embodiments.

[0022] Example 1: Please refer to Figure 1-Figure 2 The sealing structure for an azimuth propeller input shaft of this embodiment includes an upper gearbox housing 1. A spherical roller bearing 2 is disposed inside the upper gearbox housing 1. The spherical roller bearing 2 fixes an input shaft 3. An input shaft bushing 4 is disposed on the outside of one end of the input shaft 3. An input shaft seal seat 6 is disposed on the outside of the input shaft bushing 4. The input shaft seal seat 6 is fixedly connected to the upper gearbox housing 1 via bolts. A first input shaft seal ring 7 and a second input shaft seal ring 11 are disposed inside the input shaft seal seat 6. A spacer ring 12 is disposed between the first input shaft seal ring 7 and the second input shaft seal ring 11. One end of the spacer ring 12 is connected to an input shaft seal pipe joint 14 via an oil groove. The input shaft seal pipe joint 14 is connected to a gravity oil tank 15 via an oil pipe.

[0023] A locking nut 9 is provided at one end of the input shaft bushing 4. A first O-ring 5 is provided on the outside of the upper gearbox housing 1. One side of the first O-ring 5 fits against one side of the input shaft seal seat 6. A second O-ring 8 is provided inside the input shaft bushing 4. One side of the second O-ring 8 fits against the outside of the input shaft 3. An oil drain plug 10 is provided at the other end of the input shaft seal seat 6. The oil groove at one end of the oil drain plug 10 is connected to the inside of the spacer ring 12.

[0024] The original single input shaft seal ring is replaced with two input shaft seal rings, namely the first input shaft seal ring 7 and the second input shaft seal ring 11. A gravity oil tank 15 is added between the two input shaft seal rings. The original oil spray lubrication is replaced with oil immersion lubrication. This improves the oil film thickness at the input shaft seal ring, avoids the occurrence of dry friction, and reduces the wear between the input shaft seal ring lip and the hardened layer of the input shaft bushing 4. The dual-stage input shaft seal ring structure greatly improves the sealing ability.

[0025] In some examples, the inner side of the first input shaft sealing ring 7 is in contact with the outer side of the input shaft bushing 4, the outer side of the first input shaft sealing ring 7 is in contact with the inner side of the input shaft sealing seat 6, the inner side of the second input shaft sealing ring 11 is in contact with the outer side of the input shaft bushing 4, and the outer side of the second input shaft sealing ring 11 is in contact with the inner side of the input shaft sealing seat 6;

[0026] When the first input shaft seal ring 7 is damaged, the oil in the gravity oil tank 15 will leak into the gearbox of the steering propeller device under the action of gravity. The drop in the liquid level will cause the liquid level sensor installed on the gravity oil tank 15 to alarm, which can detect the fault in time. Moreover, the oil loss in the gravity oil tank 15 is inside the steering propeller, which is an internal leakage and will not cause oil contamination to the cabin.

[0027] When the second input shaft seal ring 11 is damaged, the oil in the gravity oil tank 15 will leak to the outside of the steering propeller device under the action of gravity. The drop in the liquid level will cause the liquid level sensor installed on the gravity oil tank 15 to alarm. However, since the oil volume of the gravity oil tank 15 is only about 20L, which is much smaller than the oil in the gearbox on the steering propeller, it will not cause large-scale oil contamination.

[0028] Secondly, since a gland 13 is provided on one side of the second input shaft sealing ring 11, and the gland 13 is fixedly connected to the outside of the input shaft sealing seat 6 by bolts, when the second input shaft sealing ring 11 needs to be replaced, there is no need to extract the oil in the upper gearbox. Instead, one only needs to unscrew the screws on the gland 13, remove the gland 13 and the damaged input shaft sealing ring, replace them with a new input shaft sealing ring, and then reinstall the gland 13. If the maintenance cycle is tight, a non-full-ring sealing ring can be used, and then the gravity oil tank 15 is filled with oil to the specified liquid level height, and then the oil level is observed to see if there is any change.

[0029] The oil level in the gravity oil tank 15 is approximately 400-500mm above the centerline of the input shaft. The lip of the input shaft seal ring, under the action of its own spring, clings tightly to the hardened layer of the bushing. The pressure from the back side to overcome the spring tension of the input shaft seal ring is generally about 0.01MPa-0.02MPa. The oil pressure at the centerline of the input shaft is only 0.005MPa, and the oil will not flow out of the first input shaft seal ring 7.

[0030] When the entire rudder-propeller device adopts air sealing, the pressure on the left side of the first input shaft sealing ring 7 is about 0.2 MPa, which needs to be determined according to the draft of the ship. At this time, the installation height of the gravity oil tank 15 can be adjusted to balance the pressure on the first input shaft sealing ring 7, so as to avoid the oil film thickness between the input shaft sealing ring lip and the input shaft bushing 4 being reduced under the action of pressure, thereby causing heating and wear.

[0031] Working principle: Under the action of the gravity oil tank, the original oil spray lubrication is changed to oil immersion lubrication, which improves the working conditions of the sealing ring and extends the service life of the sealing ring. At the same time, the single-channel sealing ring is changed to a double-channel sealing ring, which reduces the risk of sealing failure and reduces pollution to the environment. The optimized structure is easy to maintain, shortens the maintenance cycle, and reduces the economic losses caused by maintenance.

[0032] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and replacements made by technicians in this field on the basis of the present invention fall within the scope of protection required by the present invention.

Claims

1. A sealing structure for an input shaft of an azimuth propeller, comprising an upper gearbox housing (1), characterized in that: A spherical roller bearing (2) is provided inside the upper gearbox housing (1), and the spherical roller bearing (2) fixes the input shaft (3). An input shaft bushing (4) is provided outside one end of the input shaft (3), and an input shaft sealing seat (6) is provided outside the input shaft bushing (4). The input shaft sealing seat (6) is fixedly connected to the upper gearbox housing (1) through bolts. A first input shaft sealing ring (7) and a second input shaft sealing ring (11) are provided inside the input shaft sealing seat (6), and a spacer ring (12) is provided between the first input shaft sealing ring (7) and the second input shaft sealing ring (11). One end of the spacer ring (12) is connected to the input shaft sealing pipe joint (14) through an oil groove, and the input shaft sealing pipe joint (14) is connected to the gravity oil tank (15) through an oil pipe. A locking nut (9) is provided at one end of the input shaft bushing (4).

2. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: A first O-ring (5) is provided on the outside of the upper gearbox housing (1), and one side of the first O-ring (5) is in contact with one side of the input shaft seal seat (6).

3. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: A second O-shaped sealing ring (8) is provided inside the input shaft bushing (4), and one side of the second O-shaped sealing ring (8) is in contact with the outside of the input shaft (3).

4. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: The inner side of the first input shaft sealing ring (7) fits in contact with the outer side of the input shaft bushing (4), and the outer side of the first input shaft sealing ring (7) fits in contact with the inner side of the input shaft sealing seat (6).

5. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: The inner side of the second input shaft sealing ring (11) fits in contact with the outer side of the input shaft bushing (4), and the outer side of the second input shaft sealing ring (11) fits in contact with the inner side of the input shaft sealing seat (6).

6. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: A pressure cover (13) is provided on one side of the second input shaft sealing ring (11), and the pressure cover (13) is fixedly connected to the outside of the input shaft sealing seat (6) by bolts.

7. The sealing structure for the azimuth propeller input shaft according to claim 1, characterized in that: An oil drain plug (10) is provided at the other end of the input shaft seal seat (6), and an oil groove at one end of the oil drain plug (10) is connected to the interior of the spacer ring (12).

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