Gas turbine coupling protection cover

Abstract

The gas turbine coupling protection cover comprises an upper shell and a lower shell, the upper shell and the lower shell are buckled to form a containing cavity, and the containing cavity is used for containing a coupling; one end formed after the upper shell and the lower shell are buckled is used for being detachably connected with a speed reducer; the mounting seat is provided with a first connecting part and a second connecting part, the first connecting part is used for being detachably connected with the gas turbine, the second connecting part is connected with the lower shell, a damping block is arranged between the second connecting part and the position where the second connecting part is connected with the lower shell, and the position where the second connecting part is connected with the lower shell has slippage. According to the gas turbine, the damping block is arranged between the mounting base and the lower shell, the damping effect on vibration generated during operation of the gas turbine can be achieved, and the situation that the protection cover is loosened due to vibration of the gas turbine is avoided; and the lower shell and the mounting base are connected according to the reserved slippage amount, the effect of deformation generated when the gas turbine shell is heated can be counteracted, and therefore the protective cover can be further prevented from loosening.

Description

Technical Field

[0001] The present application relates to the field of gas turbines, and in particular to a gas turbine coupling protection cover. Background Art

[0002] In a gas turbine generator set, the gas turbine is connected to the reducer through a coupling, and the reducer is connected to the generator. When the unit is running, the gas turbine transmits torque to the reducer through the coupling, and then to the generator through the reducer, thereby driving the generator to generate electricity. During operation, the coupling will rotate at high speed. If a person or foreign object contacts the coupling during this period, it is very easy to cause a dangerous accident. Therefore, most of the time, a protective cover needs to be installed on the outside of the coupling. However, the current protective cover is easy to loosen when the gas turbine is deformed by heat during operation, and when the gas turbine vibrates during operation. Utility Model Content

[0003] The present application proposes a gas turbine coupling protection cover, which aims to solve the problem mentioned in the background technology that the coupling protection cover is easy to loosen when the gas turbine is deformed by heat or when the gas turbine vibrates.

[0004] In an embodiment of the present application, a gas turbine coupling protection cover is provided, comprising:

[0005] An upper shell and a lower shell, wherein the upper shell and the lower shell are buckled together to form a receiving cavity, and the receiving cavity is used to accommodate the coupling; one end of the upper shell and the lower shell after buckling is used to be detachably connected to the reducer;

[0006] The mounting seat is provided with a first connection part and a second connection part, the first connection part is used for detachable connection with the gas turbine, the second connection part is connected to the lower shell, and a shock-absorbing block is provided between the second connection part and the position where it is connected to the lower shell, and a sliding amount is provided at the position where the second connection part and the lower shell are connected.

[0007] In the embodiment of the present application, the second connection portion and the lower shell are threadedly connected, and a slip amount is provided at the position of the threaded connection.

[0008] In the embodiment of the present application, the second connecting portion has a first mounting plane, the shock absorbing block is laid flat on the first mounting plane, the lower shell is provided with a mounting frame, the mounting frame is provided with a second mounting plane, and the first mounting plane, the shock absorbing block and the second mounting plane are attached to each other;

[0009] The second connection portion, the shock absorbing block and the second mounting plane are all provided with a plurality of coaxial threaded holes, the second connection portion, the shock absorbing block and the second mounting plane are threadedly connected through the coaxial threaded holes, and a slip amount is provided at the position of the threaded connection.

[0010] In the embodiment of the present application, the diameter of the coaxial threaded hole is 5 mm-7 mm larger than the diameter of the bolt arranged therein.

[0011] In the embodiment of the present application, a flange is provided at one end of the upper shell and the lower shell that are connected to the reducer after being buckled together, and the upper shell and the lower shell are connected to the reducer through the flange.

[0012] In an embodiment of the present application, the upper shell and the lower shell are each provided with a wind shield at one end for the gas turbine rotor to pass through, and both wind shields are provided with semicircular holes. After the upper shell and the lower shell are buckled together, the two semicircular holes are combined to form a through hole, and the through hole is used for the gas turbine rotor to pass through the accommodating cavity.

[0013] In the embodiment of the present application, the upper shell and the lower shell are both semi-cylindrical, and the upper shell and the lower shell are snapped together to form a cylindrical shape that imitates the coupling.

[0014] In the embodiment of the present application, an oil outlet communicating with the accommodating cavity is provided at the bottom of the lower shell, and a screw plug is provided at the oil outlet.

[0015] In the embodiment of the present application, at least one handle is provided on the outer side walls of the upper shell and the lower shell.

[0016] In the embodiment of the present application, a copper lining is provided on the inner side walls of the upper shell and the lower shell.

[0017] In the embodiment of the present application, one end of the protective cover is connected to the reducer, and the other end is connected to the gas turbine through a mounting seat. A shock-absorbing block is provided between the mounting seat and the lower shell body. The shock-absorbing block can have a certain shock-absorbing effect on the vibration generated during the operation of the gas turbine, thereby preventing the protective cover from loosening due to the vibration of the gas turbine. In addition, the lower shell body and the mounting seat are connected in a manner of reserving a slip amount. The slip amount reserved between the lower shell body and the mounting seat can offset the deformation of the gas turbine casing when it is heated, thereby further preventing the protective cover from loosening. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0019] Figure 1 It is a schematic diagram of the structure of a gas turbine coupling protection cover in one embodiment of the present application. Description of the drawings:

[0021] 100-upper shell, 110-lower shell, 120-wind shield, 130-perforation, 140-handle, 150-flange, 160-oil outlet, 170-screw plug, 200-mounting seat, 210-first connecting part, 220-second connecting part, 300-mounting frame, 310-first plate, 320-second plate, 330-third plate, 400-shock absorber block.

[0022] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0024] It should be noted that if the embodiments of the present application involve directional indications (such as up, down, left, right, front, back...), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0025] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0026] like Figure 1 As shown, the embodiment of the present application provides a gas turbine coupling protection cover, comprising: an upper shell 100 and a lower shell 110, wherein the upper shell 100 and the lower shell 110 are buckled together to form a receiving cavity, and the receiving cavity is used to accommodate the coupling; one end of the upper shell 100 and the lower shell 110 after buckling is used to be detachably connected to the reducer;

[0027] The mounting seat 200 is provided with a first connecting portion 210 and a second connecting portion 220, wherein the first connecting portion 210 is used for detachable connection with the gas turbine, the second connecting portion 220 is connected to the lower shell 110, and a shock absorbing block 400 is provided between the second connecting portion 220 and the position where it is connected to the lower shell 110, and a sliding amount is provided at the position where the second connecting portion 220 and the lower shell 110 are connected.

[0028] like Figure 1 As shown, in the embodiment of the application, the protective cover includes two parts: an upper shell 100 and a lower shell 110. The upper shell 100 and the lower shell 110 are used to buckle with each other, and the cover is arranged on the outside of the coupling to isolate and protect the coupling. After the upper shell 100 and the lower shell 110 are buckled and the cover is arranged on the coupling, the upper shell 100 is located on the upper side and the lower shell 110 is located on the lower side. Figure 1 As shown, in the embodiment of the present application, the upper shell 100 and the lower shell 110 are both semi-cylindrical, and the upper shell 100 and the lower shell 110 can be buckled together to form a cylindrical shape that imitates the coupling. The position where the upper shell 100 and the lower shell 110 are buckled together can also be fixed by bolts to form a detachable structure, which is easy to disassemble and install.

[0029] In the gas turbine generator set, the coupling is located between the gas turbine and the reducer. After the upper shell 100 and the lower shell 110 are snap-fitted and placed on the coupling, the two can be connected close to one end of the reducer (such as Figure 1 The lower housing 110 is detachably connected to the reducer, for example, fixed to the reducer by threaded connection. The lower housing 110 is snap-fitted to the coupling and is located at the lower side of the coupling. The mounting seat 200 can be mounted at the lower end of the lower housing 110 and mounted at the end away from the reducer, so that one end of the protective cover is mounted on the gas turbine and the other end is mounted on the reducer, and the installation is relatively firm.

[0030] Continue to refer to Figure 1 In the embodiment of the present application, the first connection part 210 can be threadedly connected to the gas turbine for easy disassembly. The shock-absorbing block 400 can be made of rubber material or other materials with shock-absorbing function. The shock-absorbing block 400 is clamped between the second connection part 220 and the lower shell 110, thereby playing a shock-absorbing role. When the second connection part 220 and the lower shell 110 are connected, a slip amount needs to be set, that is, the lower shell 110 is not connected to the second connection part 220 in a completely relatively fixed manner, but the lower shell 110 can produce relative movement with the mounting seat 200 within the set slip amount. For example, the second connection part 220 and the lower shell 110 can be threadedly connected, and the diameter of the threaded hole during the threaded connection is greater than the diameter of the bolt, so that there is a certain amount of slip between the lower shell 110 and the mounting seat 200.

[0031] In the embodiment of the present application, one end of the protective cover is connected to the reducer, and the other end is connected to the gas turbine through the mounting base 200. A shock-absorbing block 400 is provided between the mounting base 200 and the lower shell 110. The shock-absorbing block 400 can have a certain shock-absorbing effect on the vibration generated during the operation of the gas turbine, thereby preventing the protective cover from loosening due to the vibration of the gas turbine; in addition, the lower shell 110 and the mounting base 200 are connected in a manner of reserving a slip amount. The reserved slip amount between the lower shell 110 and the mounting base 200 can offset the deformation of the gas turbine casing when it is heated, thereby further preventing the protective cover from loosening.

[0032] Continue to refer to Figure 1 In the embodiment of the present application, the second connecting portion 220 has a first mounting plane, the shock absorbing block 400 is laid flat on the first mounting plane, the lower shell 110 is provided with a mounting frame 300, the mounting frame 300 is provided with a second mounting plane, and the first mounting plane, the shock absorbing block 400 and the second mounting plane are attached to each other;

[0033] The second connection part 220, the shock absorbing block 400 and the second mounting plane are all provided with a plurality of coaxial threaded holes, the second connection part 220, the shock absorbing block 400 and the second mounting plane are threadedly connected through the coaxial threaded holes, and a slippage amount is provided at the position of the threaded connection.

[0034] like Figure 1 As shown, the mounting seat 200 can be made of angle steel, or its shape can be roughly similar to angle steel. Specifically, the mounting seat 200 includes a first connecting portion 210 and a second connecting portion 220, the first connecting portion 210 and the second connecting portion 220 are perpendicular to each other, the first connecting portion 210 is used to be detachably connected to the gas turbine, such as threaded connection, and the second connecting portion 220 is used to be connected to the lower shell 110. After the first connecting portion 210 is connected to the gas turbine, the second connecting portion 220 is in a horizontal direction, so the upper surface of the second connecting portion 220 forms a first mounting plane.

[0035] like Figure 1As shown, the lower end of the lower shell 110 is also provided with a mounting frame 300, and the mounting frame 300 can be made of channel steel, or its shape can be similar to the shape of the channel steel. Specifically, the mounting frame 300 includes a first plate 310, a second plate 320 and a third plate 330, and the first plate 310 and the third plate 330 are respectively arranged on both sides of the second plate 320 and are perpendicular to the second plate 320, and the first plate 310 and the third plate 330 are fixedly connected to the lower shell 110, such as welding. After the lower shell 110 cover is arranged on the coupling, the second plate 320 is in a horizontal direction, and the lower plate surface of the second plate 320 forms a second mounting plane. When the shock absorbing block 400 is laid flat on the first mounting plane and between the second mounting plane, it not only has a better shock absorbing effect, but also has a better stabilizing effect.

[0036] Continue to refer to Figure 1 , the second connection part 220, the shock absorbing block 400 and the second plate 320 are roughly the same in size and shape, for example, they are all rectangular in shape, and threaded holes can be respectively set at the four corners of the second connection part 220, the shock absorbing block 400 and the second plate 320. After the second connection part 220, the shock absorbing block 400 and the second plate 320 are attached to each other, the threaded holes at the four corners are coaxial, and then the second connection part 220, the shock absorbing block 400 and the second plate 320 can be threadedly connected by four bolts and nuts. It should be noted that the slip amount needs to be set when threading, for example, the diameter of the coaxial threaded hole is set to be larger than the bolt diameter inside it.

[0037] Specifically, the diameter of the coaxial threaded hole can be set to be 5mm-7mm larger than the diameter of the selected bolt, so that there is a 2.5mm-3.5mm reserve on one side between the bolt and the coaxial threaded hole, and then there can be a 2.5mm-3.5mm slippage between the lower shell 110 and the mounting seat 200. The slippage under this size structure can not only ensure that the lower shell 110 is fixed on the mounting seat 200, but also offset the deformation of the gas turbine casing when it is heated.

[0038] like Figure 1 As shown, in the embodiment of the present application, the ends of the upper shell 100 and the lower shell 110 connected to the reducer after being buckled are provided with a flange 150, and the upper shell 100 and the lower shell 110 are connected to the reducer through the flange 150. In particular, in the embodiment of the present application, a semicircular flange 150 can be provided at the ends of the upper shell 100 and the lower shell 110 connected to the reducer after being buckled, and after the two are buckled together, the two semicircular flanges 150 form a complete circular flange, which is then connected to the reducer through the circular flange.

[0039] like Figure 1As shown, in the embodiment of the present application, the upper shell 100 and the lower shell 110 are each provided with a wind shield 120 at one end for the gas turbine rotor to pass through, and both wind shields 120 are provided with semicircular holes. After the upper shell 100 and the lower shell 110 are buckled together, the two semicircular holes are combined to form a through hole 130, and the through hole 130 is used for the gas turbine rotor to pass through the accommodating cavity.

[0040] Among them, Figure 1 In the shown orientation, the left ends of the upper shell 100 and the lower shell 110 are used for the gas turbine rotor to penetrate into the accommodating cavity therein, therefore, semicircular wind shields 120 are respectively arranged at the left ends of the upper shell 100 and the lower shell 110, and semicircular holes are respectively arranged at the center positions of the two semicircular wind shields 120. When the upper shell 100 and the lower shell 110 are buckled together, the two semicircular holes form a complete through hole 130, and the two semicircular baffles also form a circular wind shield structure. The through hole 130 allows the gas turbine rotor to penetrate into the interior of the protective cover, and the circular wind shield structure can reduce the flow speed of the air in the protective cover, thereby preventing the input shaft end pressure of the internal coupling gear box from being too low, resulting in seal failure, and further causing oil leakage.

[0041] In the embodiment of the present application, a copper lining is provided on the inner side walls of the upper shell 100 and the lower shell 110. The copper linings in the upper shell 100 and the lower shell 110 are both arranged close to their respective inner side walls, and when the upper shell 100 and the lower shell 110 are buckled together, the two copper liners are combined into a cylindrical lining. The copper lining is arranged inside the protective cover to prevent sparks from accidental friction, so as to meet the use requirements of explosion-proof environment.

[0042] like Figure 1 As shown, in the embodiment of the present application, the bottom of the lower housing 110 is provided with an oil outlet 160 communicating with the accommodating cavity, and the oil outlet 160 is provided with a screw plug 170. When the lower housing 110 is covered on the coupling, the oil outlet 160 is located at the bottom of the lower housing 110, and when the lubricating oil used inside the coupling drips into the lower housing 110, it can be discharged through the oil outlet 160. The screw plug 170 is provided at the oil outlet 160 to facilitate the opening and closing of the oil outlet 160.

[0043] In the embodiment of the present application, at least one handle 140 is provided on the outer side wall of the upper shell 100 and the lower shell 110. Providing the handle 140 on the upper shell 100 and the lower shell 110 can facilitate installation and transportation by the operator.

[0044] In the embodiment of the present application, one end of the protective cover is connected to the reducer, and the other end is connected to the gas turbine through the mounting base 200. A shock-absorbing block 400 is provided between the mounting base 200 and the lower shell 110. The shock-absorbing block 400 can have a certain shock-absorbing effect on the vibration generated during the operation of the gas turbine, thereby preventing the protective cover from loosening due to the vibration of the gas turbine; in addition, the lower shell 110 and the mounting base 200 are connected in a manner of reserving a slip amount. The reserved slip amount between the lower shell 110 and the mounting base 200 can offset the deformation of the gas turbine casing when it is heated, thereby further preventing the protective cover from loosening.

[0045] The above description is only an optional embodiment of the present application, and does not limit the patent scope of the present application. All equivalent structural transformations made by using the contents of the present application specification and drawings under the inventive concept of the present application, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A gas turbine coupling protection cover, characterized in that: include: An upper shell and a lower shell, wherein the upper shell and the lower shell are buckled together to form a receiving cavity, and the receiving cavity is used to accommodate the coupling; one end of the upper shell and the lower shell after buckling is used to be detachably connected to the reducer; The mounting seat is provided with a first connection part and a second connection part, the first connection part is used for detachable connection with the gas turbine, the second connection part is connected to the lower shell, and a shock-absorbing block is provided between the second connection part and the position where it is connected to the lower shell, and a sliding amount is provided at the position where the second connection part and the lower shell are connected.

2. The gas turbine coupling protection cover according to claim 1, characterized in that: The second connection portion and the lower shell are threadedly connected, and a slip amount is provided at a position of the threaded connection.

3. The gas turbine coupling protection cover according to claim 2, characterized in that: The second connecting portion has a first mounting plane, the shock absorbing block is laid flat on the first mounting plane, the lower shell is provided with a mounting frame, the mounting frame is provided with a second mounting plane, and the first mounting plane, the shock absorbing block and the second mounting plane are in contact with each other; The second connection portion, the shock absorbing block and the second mounting plane are all provided with a plurality of coaxial threaded holes, the second connection portion, the shock absorbing block and the second mounting plane are threadedly connected through the coaxial threaded holes, and a slip amount is provided at the position of the threaded connection.

4. The gas turbine coupling protection cover according to claim 3, characterized in that: The diameter of the coaxial threaded hole is 5mm-7mm larger than the diameter of the bolt arranged therein.

5. The gas turbine coupling protection cover according to claim 1, characterized in that: The ends of the upper shell and the lower shell connected to the reducer after being buckled are both provided with flanges, and the upper shell and the lower shell are connected to the reducer through the flanges.

6. The gas turbine coupling protection cover according to claim 1, characterized in that: The upper shell and the lower shell are both provided with wind shields at one end for the gas turbine rotor to pass through, and semicircular holes are provided on both wind shields. After the upper shell and the lower shell are buckled together, the two semicircular holes are combined to form a through hole, and the through hole is used for the gas turbine rotor to pass through the accommodating cavity.

7. The gas turbine coupling protection cover according to claim 1, characterized in that: The upper shell and the lower shell are both semi-cylindrical, and after being buckled together, the upper shell and the lower shell form a cylindrical shape that imitates the coupling.

8. The gas turbine coupling protection cover according to claim 7, characterized in that: The bottom of the lower shell is provided with an oil outlet communicating with the accommodating cavity, and the oil outlet is provided with a screw plug.

9. The gas turbine coupling protection cover according to claim 1, characterized in that: At least one handle is provided on the outer side walls of the upper shell and the lower shell.

10. The gas turbine coupling protection cover according to claim 1, characterized in that: The inner side walls of the upper shell and the lower shell are both provided with copper linings.

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