Composite brush type sealing device for bearing

Abstract

The utility model provides a bearing composite brush type sealing device which comprises an inner casing baffle, a front clamping plate and a rear clamping plate, and the front clamping plate and the rear clamping plate are connected to the two ends of the inner casing baffle. The brush wires are installed between the front clamping plate and the rear clamping plate, the fixed ends of the brush wires are fixed to an inner casing baffle in the circumferential direction, and the working ends of the brush wires extend from the fixed ends in the radial direction of the front clamping plate and the rear clamping plate and make contact with a rotor runway of the turbomachinery; gaps are formed between the brush wires and the front clamping plate, and zero gaps are formed between the brush wires and the rear clamping plate. According to the brush type sealing device, the axial deflection deformation of the brush wire bundle is reduced, the deterioration effect of the blowing effect on the sealing performance at the high rotating speed is restrained, and the sealing performance of the brush type sealing device at the high rotating speed is improved. And meanwhile, the brush type sealing device is matched with the graphite sealing ring, so that an oil-gas mixture at a bearing part is effectively prevented from leaking, and the effective service life of the brush type sealing device is prolonged.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of turbomachinery seal, especially to a bearing composite brush type sealing device. BACKGROUND

[0002] In the technical field of turbomachinery seal, rotary dynamic seal is a key component in modern turbomachinery, and advanced rotary seal technology can significantly improve the operating efficiency and stability of turbomachinery. For example, in the case of an aero-engine, although the labyrinth seal has a simple structure, its sealing effect is not satisfactory. Especially after the occurrence of collision and abrasion, the gap increases and cannot be repaired in real time, resulting in a significant increase in leakage. In addition, the labyrinth seal technology inevitably has a "hard-hard" collision and abrasion phenomenon, which directly leads to the entry of grinding particles into the interior of the aero-engine, adversely affecting the normal operation of other components.

[0003] Brush seal belongs to contact seal technology, and under the same conditions, the leakage level of brush seal is only 50% or less than that of traditional labyrinth seal. If the sealing structure at the key position is replaced with brush seal, the engine thrust can be increased by 1% to 3%, and the oil consumption can be reduced by 3% to 5%. In order to ensure the excellent sealing performance of brush seal, the brush bundle must be in contact with the rotor during operation, but the brush filaments will be deformed and worn due to the combined action of leakage airflow, rotor, brush filaments, and rear clamping plate during operation, so that the brush bundle cannot always maintain contact with the rotor, resulting in the degradation of the sealing performance of the brush seal device.

[0004] The blowout effect, friction heat effect, steeling effect, hysteresis effect, and blow-up effect of brush seal all have important influences on its sealing performance and service life, and at the same time limit the application range of brush seal. Currently, the brush seal used in turbomachinery usually contacts the rotor surface at a certain angle along the rotation direction of the rotor to effectively reduce the wear of the brush filaments and improve the sealing performance.

[0005] Bearing components are the focus of rotary dynamic seal, and once the oil-gas mixture leaks due to poor sealing, it will directly affect the overall performance of the turbomachinery. Therefore, the rotary seal technology for bearings includes traditional labyrinth seal, fingertip seal, graphite seal, and brush seal. Among them, brush seal is increasingly widely used in dynamic sealing of bearing components due to its excellent sealing performance.

[0006] However, in engineering practice, the brush seal of bearing components faces the following challenges: at high rotation speed, the inclined brush filaments are severely worn, and the blow-up effect causes the brush filaments to separate from the rotor, resulting in reduced sealing performance and leakage of oil-gas mixture.

[0007] That is, the turbo machinery high speed operation, there will be many problems, for example, blowing effect intensified, intensified steel effect, sealing performance is reduced, and bearing parts of the oil and gas mixture leakage and other problems.

[0008] In view of this, the present application inventors designed a bearing composite brush seal device, in order to overcome the above technical problems. Practical new type content

[0009] The technical problem solved by the present application is to overcome the defects of the prior art, such as the serious wear of the inclined brush wire of the bearing part at high speed, and the reduced sealing performance, and to provide a bearing composite brush seal device.

[0010] The utility model discloses a technical scheme to solve the above technical problems:

[0011] A bearing composite brush seal device, characterized in that the bearing composite brush seal device comprises:

[0012] The inner casing baffle, the front clamping plate and the rear clamping plate are connected at both ends of the inner casing baffle;

[0013] The brush wire is installed between the front clamping plate and the rear clamping plate, and the fixed end of the brush wire is fixed on the inner casing baffle in the circumferential direction, and the working end extends radially from the fixed end along the front clamping plate and the rear clamping plate to contact the turbine rotor runway;

[0014] The brush wire has a gap between the front clamping plate, and there is no gap between the brush wire and the rear clamping plate.

[0015] According to one embodiment of the present application, the front clamping plate is provided with a ventilation groove hole, which is arranged in the circumferential direction and blows the brush wire centripetally towards the direction of the turbine rotor runway.

[0016] According to one embodiment of the present application, the ventilation groove hole gradually expands from the outside to the inside.

[0017] According to one embodiment of the present application, the ventilation groove hole is arranged radially staggered.

[0018] According to one embodiment of the present application, the rear clamping plate is provided with a plurality of support bosses, and an oil guide groove is formed between adjacent two support bosses, and an oil discharge hole is arranged at the lower part of the rear clamping plate.

[0019] According to one embodiment of the present application, the oil discharge hole is arranged at the lowest end of the oil guide groove.

[0020] According to one embodiment of the utility model, the support boss is provided with wear-resistant coating at the contact surface of the brush wire, and the turbine rotor runway is provided with wear-resistant coating at the contact surface of the brush wire.

[0021] According to one embodiment of the utility model, graphite sealing ring is further installed between the lower part of the rear clamping plate and the turbine rotor runway, and gap exists between the end of the graphite sealing ring and the turbine rotor runway.

[0022] According to one embodiment of the utility model, the inner casing baffle has circumferential arc surface towards the rotor, and the fixed end of the brush wire is fixed on the circumferential arc surface.

[0023] According to one embodiment of the utility model, the front clamping plate is fixedly connected with one end of the inner casing baffle, and the rear clamping plate is detachably connected with the other end of the inner casing baffle.

[0024] The utility model discloses a positive progress effect lies in:

[0025] The bearing composite brush type sealing device of the utility model reduces the axial distortion amount of brush wire bundle, suppresses the deterioration effect of blowing effect on sealing performance at high speed, improves the sealing performance of brush type sealing device at high speed.

[0026]

Reference Signs

[0027] Inner casing baffle 10

[0028] Front clamping plate 20

[0029] Rear clamping plate 30

[0030] Brush wire 40

[0031] Fixed end of brush wire 41

[0032] Working end of brush wire 42

[0033] Turbine rotor runway 50

[0034] Ventilation groove hole 21

[0035] Support boss 31

[0036] Oil guide groove 60

[0037] Oil discharge hole 70

[0038] Graphite sealing ring 80

[0039] Wear-resistant coating 100

[0040] lubricating coating 200 BRIEF DESCRIPTION OF DRAWINGS

[0041] The above and other features, properties and advantages of the present application will become more apparent by describing in detail the following embodiments with reference to the attached drawings, in which:

[0042] Fig. 1 It is a structural schematic view of the bearing composite brush type sealing device of the present application.

[0043] Fig. 2 It is a structural schematic view of the front clamping plate in the bearing composite brush type sealing device of the present application.

[0044] Fig. 3 It is a structural schematic view of the rear clamping plate in the bearing composite brush type sealing device of the present application. DETAILED DESCRIPTION

[0045] In order to make the above objectives, features and advantages of the present application more apparent, the following will describe the specific embodiments of the present application in detail with reference to the drawings.

[0046] The embodiments of the present application will now be described in detail with reference to the drawings. The preferred embodiments of the present application will now be described in detail with reference to the drawings. In all the drawings, the same reference numerals will be used to denote the same or similar parts.

[0047] In addition, although the terms used in the present application are selected from the commonly used terms, some of the terms mentioned in the specification of the present application can be selected by the applicant according to his or her judgment, and the detailed meanings thereof are described in the relevant part of the description herein.

[0048] In addition, the present application is required to be understood not only by the actual terms used, but also by the meanings implied by each term.

[0049] As Figs. 1 to 3 As shown in the drawings, the present application discloses a bearing composite brush type sealing device, which comprises an inner machine case baffle 10, a front clamping plate 20, a rear clamping plate 30 and brush filaments 40. Among them, the front clamping plate 20 and the rear clamping plate 30 are connected at both ends of the inner machine case baffle 10. Preferably, the front clamping plate 20 is integrally prepared with the inner machine case baffle 10, the rear clamping plate 30 is detachably connected with the inner machine case baffle 10, and the inner machine case baffle 10 is provided with a brush filament bundle fence.

[0050] The brush filaments 40 are installed between the front clamping plate 20 and the rear clamping plate 30, and the fixed end 41 of the brush filaments 40 is fixed on the inner casing baffle 10 in the circumferential direction, and the working end 42 of the brush filaments 40 extends from the fixed end 41 in the radial direction of the front clamping plate 20 and the rear clamping plate 30 and is in contact with the turbine rotor raceway 50. There is a gap between the brush filaments 40 and the front clamping plate 20, and there is zero gap between the brush filaments 40 and the rear clamping plate 30.

[0051] Preferably, the inner casing baffle 10 has a circumferential arc surface facing the rotor, the fixed end 41 of the brush filaments 40 is fixed on the circumferential arc surface, the working end 42 of the brush filaments 40 extends in the radial direction of the front clamping plate 20 and the rear clamping plate 30 to be in contact with the turbine rotor raceway 50, and there is a gap between the brush filaments 40 and the front clamping plate 20, and there is zero installation gap between the brush filaments 40 and the rear clamping plate 30. The gap between the front clamping plate 20 and the brush filaments 40 is preferably in the range of 0mm to 2mm.

[0052] The air passage groove 21 is provided on the front clamping plate 20, and the air passage groove 21 is arranged in the circumferential direction and blows the brush filaments 40 in the centripetal direction towards the turbine rotor raceway 50. The air passage groove 21 is preferably gradually expanded from the outside to the inside, and an expanding type structure is adopted to increase the gas pressure at the outlet.

[0053] Further preferably, the air passage groove 21 is arranged in the radial direction. The inlet width of the air passage groove 21 is preferably in the range of 2mm to 3mm, and the outlet width is preferably in the range of 5mm to 6mm.

[0054] The increase in gas pressure on the lower part of the brush filaments 40 reduces the porosity between the brush filaments 40, effectively preventing the leakage of oil-gas mixture at the bearing. Since the brush filaments 40 are blown in the centripetal direction, the deterioration of the sealing performance caused by the blowing effect at high speed is effectively inhibited.

[0055] In addition, the increase in gas pressure at the front of the brush filaments 40 helps the oil droplets adhering to the brush filaments 40 to enter the oil guide groove and finally flow back into the bearing cavity through the oil discharge hole.

[0056] The rear clamping plate 30 is provided with a support boss 31, and the channel formed by the support boss 31 serves as an oil guide groove 60, and an oil discharge hole 70 is provided at the lower part of the rear clamping plate 30, and the oil discharge hole 70 is arranged at the lowest end of the oil guide groove 60. The depth of the oil guide groove 60 is preferably in the range of 1mm to 3mm. The diameter of the oil discharge hole 70 is preferably in the range of 2mm to 3mm. In this way, not only can the brush filaments be effectively supported at multiple points to reduce the amount of axial distortion and deformation of the brush filaments, but also the oil droplets adhering to the brush filaments can be guided into the bearing cavity behind the rear clamping plate through the oil guide groove and the oil discharge hole.

[0057] The support boss 31 is arranged at an angle perpendicular to the angle of the brush wire 40. The support boss 31 forms effective multi-point support for the brush wire 40, reduces the amount of axial distortion of the brush wire 40, maintains the matching relationship between the brush wire 40 and the turbine rotor raceway 50, and improves the sealing performance at high speed.

[0058] The oil guide groove 60 guides the oil droplets adhered to the brush wire 40 into the oil guide groove 60, and then guides the oil droplets to the bearing cavity behind the rear clamping plate 30 through the oil outlet hole 70, thereby reducing the oil concentration in the gap of the brush wire 40 and more effectively preventing the leakage of the oil-gas mixture.

[0059] Preferably, a graphite sealing ring 80 is installed at the lower part of the rear clamping plate 30 and located between the lower part of the rear clamping plate 30 and the turbine rotor raceway 50. The end of the graphite sealing ring 80 is spaced apart from the turbine rotor raceway 50 and does not directly contact the turbine rotor raceway 50.

[0060] In the bearing composite brush seal device, the installation of the graphite sealing ring 80 not only forms effective back support for the bottom of the brush wire 40, but also directly functions as a secondary seal at high speed, thereby enhancing the sealing performance of the composite brush seal device and more effectively preventing the leakage of the oil-gas mixture. Even if the sealing performance of the brush wire 40 is reduced due to the blowout effect, the graphite sealing ring 80 can still function as a seal.

[0061] In addition, high speed can cause the shaft to expand, and the graphite sealing ring 80 comes into contact with the turbine rotor raceway 50 and shares the load with the brush wire 40, thereby reducing the wear of the brush wire 40 and prolonging the effective service life of the brush wire 40.

[0062] Preferably, a wear-resistant coating 100 is provided at the contact surface between the support boss 31 and the brush wire 40, and a wear-resistant coating 100 is provided at the contact surface between the turbine rotor raceway 50 and the brush wire 40. The turbine rotor raceway 50 is provided with a wear-resistant coating 100 at the position where the turbine rotor raceway 50 contacts the graphite sealing ring 80.

[0063] The contact surface between the support boss 31 and the brush wire 40 is provided with a lubricating coating 200. The installation gap between the end of the graphite sealing ring 80 and the turbine rotor raceway 50 is preferably in the range of 0.05mm to 0.1mm.

[0064] According to the structure description, the bearing composite brush type sealing device can improve the sealing performance of the composite brush type sealing device at high rotating speed, and prolong the effective service life of the bearing composite brush type sealing device.

[0065] The above disclosure is merely exemplary and is not intended to limit the application. Although not explicitly described, those skilled in the art can make various modifications, improvements and corrections to the application. Such modifications, improvements and corrections are suggested in the application, so they still belong to the spirit and scope of the exemplary embodiments of the application.

[0066] At the same time, specific words are used in the application to describe the embodiments of the application. As "one embodiment", "an embodiment" and / or "some embodiments" mean a certain feature, structure or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the application can be properly combined.

[0067] Similarly, it should be noted that, in order to simplify the description of the disclosure and to help understand one or more embodiments of the application, sometimes multiple features are combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the application are more than the features mentioned in the claims. In fact, the features of the embodiment are less than all the features of the disclosed single embodiment. Some embodiments use numbers to describe components, attributes and quantities. It should be understood that such numbers used in the description of the embodiments are modified by the modifier "about", "approximately" or "generally" in some examples.

[0068] Although the specific embodiments of the application are described above, those skilled in the art should understand that these are only illustrative, and the protection scope of the application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the application. Such changes and modifications fall within the protection scope of the application.

Claims

1. A bearing composite brush seal device, characterized in that, The bearing composite brush seal device includes: An inner casing baffle, a front clamping plate, and a rear clamping plate, wherein the front clamping plate and the rear clamping plate are connected to both ends of the inner casing baffle; The brush bristles are installed between the front clamping plate and the rear clamping plate, and the fixed end of the brush bristles is fixed circumferentially to the inner casing baffle, and the working end extends radially from the fixed end along the front clamping plate and the rear clamping plate to contact the turbine rotor track. There is a gap between the brush bristles and the front clamping plate, and there is zero gap between the brush bristles and the rear clamping plate.

2. The bearing composite brush seal device as described in claim 1, characterized in that, The front clamp is provided with ventilation slots, which are arranged circumferentially and blow the brush filaments obliquely towards the direction of the turbine rotor track.

3. The bearing composite brush seal device as described in claim 2, characterized in that, The ventilation slots gradually expand from the outside to the inside.

4. The bearing composite brush seal device as described in claim 2, characterized in that, The ventilation slots are arranged in a staggered pattern along the radial direction.

5. The bearing composite brush seal device as described in claim 1, characterized in that, The rear clamp plate is provided with several support bosses, and an oil guide groove is formed between two adjacent support bosses. An oil drain hole is provided at the lower part of the rear clamp plate.

6. The bearing composite brush seal device as described in claim 5, characterized in that, The oil drain hole is located at the lowest end of the oil guide groove.

7. The bearing composite brush seal device as described in claim 5, characterized in that, The contact surface between the support boss and the brush bristles is provided with a wear-resistant coating, and the contact surface between the turbine rotor track and the brush bristles is provided with a wear-resistant coating.

8. The bearing composite brush seal device as described in claim 1, characterized in that, A graphite sealing ring is also installed between the lower part of the rear clamping plate and the turbine rotor track, and there is a gap between the end of the graphite sealing ring and the turbine rotor track.

9. The bearing composite brush seal device as described in claim 1, characterized in that, The inner casing baffle has a circumferential arc surface facing the rotor, and the fixed end of the brush bristles is fixed to the circumferential arc surface.

10. The bearing composite brush seal device as described in claim 1, characterized in that, The front clamping plate is fixedly connected to one end of the inner casing baffle, and the rear clamping plate is detachably connected to the other end of the inner casing baffle.

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