KR102329414B1 - gland box for turbin - Google Patents

Abstract

To improve sealing performance, the present invention provides a gland box for a turbine with improved sealing performance. The gland box for a turbine comprises: a main body part arranged roundly in the shape of a ring so that an inner circumference can envelop the outer circumference of a rotor arranged inside a boundary region between a high pressure terminal and a middle pressure terminal of a turbine, arranged with preset thickness in the axial direction of the rotor, divided into a plurality of regions in a circumferential direction, and having a plurality of fixing holes formed on the facing divided surfaces respectively to penetrate therethrough; a pressure adjustment pipe part connected to the outer side of the main body part, having a discharge flow path formed therein, having the inner side end of the discharge flow path, wherein the inner side end communicates with one side of the outer circumference of the main body part, and having an outer side end communicating with the outside; and a plurality of reinforcement rib parts arranged in plurality on the inner circumference of the main body part in the axial direction of the rotor, extending and protruding inside in a radial direction toward the outer circumference of the rotor in a circumferential direction, and having a thread combination groove recessed and formed outside in a radial direction on each inner side end in a circumferential direction so that a sealing device can be inserted into the inner circumference of the rotor to face and align with the same.

Description

Grand box for turbine

The present invention relates to a grand box for a turbine, and more particularly, to a grand box for a turbine having improved sealing performance.

In general, in a turbine for power generation, high-temperature and high-pressure steam or gas generated from a boiler or the like is introduced into a casing through a stop valve and a control valve.

Here, the fluid introduced into the casing rotates the blades assembled to the rotor through a diaphragm device for a turbine, whereby power is obtained while the generator rotates by the rotor.

At this time, by inducing the flow of the fluid so that the introduced fluid moves to the optimal flow path to increase the power generation efficiency, the fluid, which has a role to rotate the blades assembled in the rotor, leaks, so that the high-pressure stage, the medium-pressure stage and the low-pressure stage Efforts to increase overall efficiency are needed to minimize escape from

Here, a ring-type grand box sealing device (hereinafter, 'grand box') may be provided to surround the outer periphery of the rotor disposed inside the boundary region between the high-pressure end and the medium-pressure end of the turbine. Here, as a sealing device such as a labyrinth protrusion and a brush is mounted on the inner periphery of the grand box and disposed to face the outer periphery of the rotor, the pressure difference between the high-pressure end and the medium-pressure end of the turbine can be alleviated.

However, the conventional grand box has a serious problem in that the inner periphery on which the sealing device is mounted is damaged or cracked due to the high pressure acting inside the turbine, thereby reducing durability.

Korean Patent Registration No. 10-0047002

In order to solve the above problems, an object of the present invention is to provide a grand box for a turbine having improved sealing performance.

In order to solve the above problems, the present invention is provided to be round in a ring shape so as to surround the inner periphery of the rotor disposed inside the boundary region between the high-pressure end and the medium-pressure end of the turbine, and has a predetermined thickness along the axial direction of the rotor. a body portion provided with a plurality of divisions along the circumferential direction, and having a plurality of fixing holes formed therethrough on each divided opposing surface; a pressure regulating pipe part connected to the outside of the main body and having a discharge passage formed therein, an inner end of the discharge passage communicating with one of the outer circumferences of the main body, and an outer end communicating with the outside; And a plurality of doedoe provided along the axial direction of the rotor on the inner periphery of the main body, each protruding radially inwardly toward the outer periphery of the rotor along the circumferential direction, each sealing device aligned opposite to the inner periphery of the rotor is inserted A plurality of reinforcing ribs having thread coupling grooves recessed radially outwardly along the circumferential direction at the inner end thereof, wherein the rim of the reinforcing rib portion on the central side of the reinforcing ribs increases radially inward along the circumferential direction of the rotor. The first extension protrudes inclined at a predetermined angle along the axial direction, the second extension protrudes in a direction perpendicular to the outer periphery of the rotor, and the first extension protrudes the edge of each of the reinforcing ribs spaced apart along the axial direction of the rotor A recessed groove is formed between the recessed grooves to be inclinedly expanded along the axial direction of the rotor as they go outward in the radial direction along the circumferential direction, and are respectively recessed. Provided is a grand box for a turbine that is formed to be recessed and extend bent along the radial direction, wherein each inner end of the pressure discharge slit groove communicates with each of the depressed grooves and the outer end communicates with the outside.

Here, the opposite parts of the divided body parts are integrally extended and protruded outward in the radial direction, and an extended fastening part having the opposing surface is formed on one surface, and the protrusion is integrally extended outward in the radial direction on the outside of the extended fastening part. , It is preferable that the opposite surface is continuously formed on the protrusion, an outer end of the pressure discharge slit groove is disposed, and an inner end of the discharge passage communicates with the recessed groove.

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At this time, each of the fixing holes are spaced apart from each other along the axial direction of the rotor in the extended fastening part and are formed through, and at the same time, it is preferable that the fixing holes are spaced apart from each other along the radial direction of the body part on one side of the protrusion and are formed through each.

Through the above solution means, the present invention provides the following effects.

First, the reinforcing ribs expand along the axial direction of the rotor as they go radially outward along the circumferential direction between each reinforcing rib part protruded from the first to extend obliquely, and the pressure and vortex flow of the fluid flowing into the inclined recessed recess are relieved, so the reinforcing rib Etching and cracking due to the fluid acting on the part are minimized, and durability can be significantly improved.

Second, the pressure discharge slit groove is formed to be bent so that the pressure discharge slit groove is bent on the opposite surface of each body part coupled as a divided body. As it is discharged to the discharge slit groove, cracks in the reinforcing rib are prevented in advance, so durability can be significantly improved.

Third, each fixing hole formed for fastening between the divided body parts is spaced apart from each other in the axial direction of the rotor and penetrates the extended fastening part formed in the opposite part of the main body part, and at the same time, a radius is formed on one side of the protrusion formed on the outside of the extended fastening part. They are spaced apart from each other along the direction and formed through them to provide stable coupling force even when turbine vibration occurs.

1 is an exemplary view showing a state of use of a grand box for a turbine according to an embodiment of the present invention.
Figure 2 is a top view showing a grand box for a turbine according to an embodiment of the present invention.
Figure 3 is an exemplary view showing the opposite surface of the main body divided in the grand box for a turbine according to an embodiment of the present invention.
Figure 4 is an exemplary view showing the use state of the pressure discharge slit groove formed on the opposite surface of the main body divided in the grand box for a turbine according to an embodiment of the present invention.

Hereinafter, a grand box for a turbine according to a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is an exemplary view showing the use state of the grand box for a turbine according to an embodiment of the present invention, Figure 2 is a top view showing the grand box for a turbine according to an embodiment of the present invention, Figure 3 is the present invention An exemplary view showing the opposite surface of the main body divided in the grand box for a turbine according to an embodiment of the present invention, Figure 4 is a pressure discharge slit formed on the opposite surface of the divided main body in the grand box for a turbine according to an embodiment of the present invention It is an example diagram showing the use state of the home.

1 to 4 , the grand box 100 for a turbine according to an embodiment of the present invention includes a body portion 10 , a pressure control tube portion 20 , and a reinforcing rib portion 30 .

Here, the main body 10 is provided to be rounded in a ring shape so as to be spaced apart in a form that the inner periphery surrounds the outer periphery of the rotor r penetratingly disposed inside the boundary region between the high-pressure end and the medium-pressure end of the turbine t, and the rotor ( It is preferably provided with a predetermined thickness (k) along the axial direction of r) and divided into a plurality of places along the circumferential direction.

Here, it is preferable to understand that the thickness k of the main body 10 is set to be less than the length of the rotor r, and the inner periphery of the main body 10 and the outer periphery of the rotor r define a radial direction. It is desirable to understand that they are spaced apart from each other.

In addition, the main body portion 10 may be provided in a plurality of divisions along the circumferential direction, and may be formed in the form of a single ring as each divided opposing surfaces 11 are bolted together in a state in which they are aligned with each other. At this time, a case in which the divided body portion 10 is divided into a pair in an arc-shaped divided body in an embodiment of the present invention will be illustrated and described as an example.

Here, it is preferable that a plurality of fixing holes 13 and 13a are formed through each of the divided faces 11 of the main body 10 . In this case, the opposing surface 11 refers to a boundary surface that is in contact with each other for mutual fastening between the divided body parts 10 .

In detail, it is preferable that the opposite part of each divided main body part 10 is provided with an extended fastening part 12 which protrudes integrally outward in the radial direction and has the opposing surface 11 formed on one surface thereof. In this case, the extended fastening portion 12 is set to have a predetermined circumferential thickness, and may extend in a direction corresponding to the axial direction of the rotor r.

In addition, the protrusion 15 is integrally extended outwardly in the radial direction on the outside of the extended fastening part 12 , and it is preferable that the opposite surface 11 is continuously formed on the protrusion 15 . In this case, the cross-sectional shape of the extended fastening part 12 and the protruding part 15 formed integrally with each other may be formed in a 'L' shape. In addition, it is preferable that the opposing surface 11 is continuously formed on one surface of the extended fastening part 12 and the protruding part 15 formed integrally with each other.

In addition, it is preferable that a plurality of fixing holes 13 and 13a are formed on the opposite surface 11 of each of the divided body parts 10 . Here, each of the fixing holes 13 and 13a are spaced apart from each other along the axial direction of the rotor r in the extended fastening part 12 and are formed through, and at the same time, the body part 10 on one side of the protrusion part 15 . ) are spaced apart from each other along the radial direction, and each is preferably formed through.

In detail, in the extended fastening part 12 , a plurality of the fixing holes 13 may be formed through each other in the circumferential direction of the main body 10 at positions spaced apart from each other along the axial direction of the rotor r. . In addition, a plurality of the fixing holes 13a on one side of the protrusion 15 may be spaced apart from each other in a radial direction and formed through the body portion 10 in a circumferential direction. At this time, each of the fixing holes 13 and 13a communicates with the outside in a state in which the fixing holes 13 and 13a formed in the other body portion 10 are aligned to face each other, and the bolts can be fastened to each other. .

Through this, each of the fixing holes 13 and 13a formed for fastening between each of the divided body parts 10 are formed in the extended fastening parts 12 formed in the opposite parts 11 of the body parts 10, respectively. They are spaced apart from each other along the axial direction of the rotor (r) and are formed through, and at the same time, are spaced apart from each other along the radial direction of the body part (10) on one side of the protrusion part (15) formed on the outside of the extended fastening part (12), respectively. It can be formed through. Accordingly, when each of the fixing holes 13 and 13a are aligned with each other and bolted together, it is possible to provide a stable coupling force even when turbine vibration occurs.

And, the opposite surface 11 of each of the divided body parts 10 extends obliquely and bent in the axial direction of the rotor r along the radial direction, and each inner end communicates with a recessed groove 34 to be described later. It is preferable that the pressure discharge slit groove 14 through which the outer end communicates with the outside is recessed along the circumferential direction of the main body 10 . At this time, it is preferable that the outer end of the pressure discharge slit groove 14 is disposed in the protrusion 15 .

Here, it is preferable that at least one pressure discharge slit groove 14 is formed, and the case in which the pressure discharge slit groove 14 is formed in two places is illustrated and described as an example in an embodiment of the present invention.

In addition, it is preferable that the pressure discharge slit groove 14 is spaced apart from each other by the fixing holes 13 and 13a. That is, the pressure discharge slit groove 14 may be extended such that an inner end communicates with the recessed groove 34 and an outer end communicates with the outside in a state in which the pressure discharge slit groove 14 is separated from the fixing holes 13 and 13a.

In detail, the pressure discharge slit groove 14 communicates with the inner end of the recessed groove 34 and extends along the radial direction of the body portion 10 in a state in which the inner end communicates with each of the fixing holes 13 and 13a and is spaced apart from each other. It is preferable to include a first pressure discharge slit groove (14a) to be.

In addition, the pressure discharge slit groove 14 has an inner end in communication with the outer end of the first pressure discharge slit groove 14a, and the inner end of the pressure discharge slit groove 14 is in the axial direction of the rotor r toward the radially outer side of the main body 10 . It is preferable to include a second pressure discharge slit groove (14b) inclined to be bent. At this time, the axial direction of the rotor r is preferably understood to have the same meaning as the vertical direction in FIG. 4 .

In addition, the pressure discharge slit groove 14 is a third pressure discharge slit groove ( 14c) is preferred.

In addition, the pressure discharge slit groove 14 includes a fourth pressure discharge slit groove (14d) in which the inner end communicates with the outer end of the third pressure discharge slit groove (14c) and the outer end communicates with the outside. desirable. At this time, the fourth pressure discharge slit groove 14d may extend to be bent from the outer end of the third pressure discharge slit groove 14c.

Through this, the pressure discharge slit groove 14 is formed to be bent along the radial direction in the opposite surface 11 of each of the body parts 10 coupled to each other as a divided body, and each inner end is formed with the reinforcing rib part ( 30) communicates with the recessed groove 34 formed between the edges, and the outer end communicates with the outside. Therefore, when excessive high pressure is generated inside the turbine, as a part of the fluid such as combustion gas is automatically discharged to the pressure discharge slit groove 14, cracks in the reinforcing rib part 30 are prevented in advance, so that the durability is significantly improved. can

At this time, the pressure discharge slit groove 14 is formed on the opposite surface 11 of at least one of the main body portions 10 coupled to each other as a divided body, and the opposite surface 11 of each of the main body portions 10 is formed. As these are disposed opposite to each other, the remaining regions except for the inner end and the outer end may be formed in the form of a closed flow path.

Furthermore, gaskets, valves, and valves are located between the opposite surfaces 11 of each body part 10 so that a part of the fluid such as combustion gas is discharged along the pressure discharge slit groove 14 only when the pressure inside the turbine exceeds the preset pressure. Fluid discharge control means (not shown) such as may be further provided.

In addition, the outer periphery of the main body 10 is extended radially outward along the circumferential direction, a plurality of coupling holes 16a along the circumferential direction on the outer rim may be formed through the coupling outer ring portion 16 is formed. .

On the other hand, the pressure control pipe part 20 is connected to the outside of the main body part 10, the discharge flow path 21 is formed therein, and the discharge flow path 21 so that the pressure difference between the high-pressure end and the medium-pressure end is adjusted. It is preferable that the inner end of the body portion 10 communicates with one side of the outer periphery, and the outer end communicates with the outside.

Here, the pressure control tube 20 may be connected to one side of the outer periphery of the main body 10 at a position spaced apart from the opposite surface 11 in the circumferential direction. In addition, the discharge passage 21 may have an outer end communicating with the outside, and an inner end communicating with the outer periphery side of the main body 10 , preferably with the recessed groove 34 .

Through this, a fluid such as high-pressure combustion gas flowing from the high-pressure stage flows into the inner end of the discharge passage 21 and is discharged into the middle or low-pressure end through the outer end of the discharge passage 21 . can be In this case, the example of using the pressure control tube part 20 is not limited to the above-described example.

On the other hand, the reinforcing rib portion 30 is provided in a plurality along the axial direction of the rotor (r) on the inner periphery of the body portion 10, radially inward toward the outer periphery of the rotor (r) along the circumferential direction. Thread coupling grooves 31 extending radially outward along the circumferential direction at each inner end of the reinforcing rib part 30 so that the sealing devices s respectively protruding and aligned oppositely to the inner periphery of the rotor r are inserted. Each of these is preferably formed by depression. At this time, the coupling portion of the sealing device (s) may be slide-inserted and fixed in the thread coupling groove (31).

And, the rim of the central portion side of the reinforcing rib portion 30 of the reinforcing rib portion 30 protrudes from the radially inner side along the circumferential direction to be inclined at a preset angle along the axial direction of the rotor (r). , It is preferable that the secondary extension protrudes in a direction perpendicular to the outer periphery of the rotor (r).

That is, the edge of at least one of the reinforcing ribs 30 of the reinforcing ribs 30 is first expanded to be inclined at a predetermined angle along the axial direction of the rotor r as it goes radially inward along the circumferential direction. It may protrude and protrude a second time in a direction perpendicular to the outer periphery of the rotor (r), and the rim of the remaining reinforcing ribs 30 among the reinforcing ribs 30 is perpendicular to the outer periphery of the rotor (r). It can extend and protrude in the direction.

In detail, the rim of the central reinforcing rib part 30 of the reinforcing rib part 30 extends inwardly in the radial direction along the circumferential direction to be inclined at a preset angle along the axial direction of the rotor (r). It is preferable to include a protruding inclined border (32).

And, the first expansion protruding between the edges of each of the reinforcing ribs 30 spaced apart along the axial direction of the rotor (r), the recessed groove 34 is radially outward along the circumferential direction of the rotor ( It is preferable that the tube expands obliquely along the axial direction of r) and is recessed, respectively.

Accordingly, the rim of the central reinforcing rib part 30 of the reinforcing rib part 30 is inclined at a predetermined angle along the axial direction of the rotor (r) as it goes radially inward along the circumferential direction. The pressure and vortex flow (vortex) of the fluid flowing into the recessed groove 34 which is formed to expand along the axial direction of the rotor as it goes outward in the radial direction along the circumferential direction between the edges of each of the reinforcing ribs 30. ) is relieved, so etching and cracking caused by the fluid acting on the reinforcing rib part 30 are minimized, and durability can be significantly improved.

Here, the preset angle of the inclined border 32 may be set at an angle of 25 to 35° with respect to the outer periphery of the rotor r. At this time, when the preset angle of the inclined rim 32 is set to less than 25° with respect to the outer periphery of the rotor r, the reinforcement by the vortex of the fluid flowing into the recessed groove 34 There is a fear that the etching acting on the rib portion 30 and the crack generation may not be alleviated. On the other hand, when the preset angle of the inclined rim 32 is set to be greater than 35° with respect to the outer periphery of the rotor r, the radial length of the reinforcing rib part 30 is excessively increased, so that the turbine grand Since the volume of the box 100 is increased, there is a fear that economic efficiency is lowered.

Accordingly, as the preset angle of the inclined edge 32 is set at an angle of 25 to 35° with respect to the outer periphery of the rotor r, the vortex of the fluid flowing into the recessed groove 34 by It is possible to minimize the etching acting on the reinforcing rib portion 30 and the crack generation due to the etching.

In addition, the rim of the reinforcing rib part 30 on the central side of the reinforcing rib part 30 is an extension rim protruding from the inner end of the inclined rim 32 in a direction perpendicular to the outer periphery of the rotor r. (33) is preferably included.

On the other hand, the grand box 100 for a turbine including the body portion 10, the pressure control tube portion 20 and the reinforcing rib portion 30 according to an embodiment of the present invention is made of a metal material such as chrome steel. can be provided.

In addition, on the surface of the grand box 100 for a turbine including the main body 10 , the pressure control pipe 20 and the reinforcing rib 30 , a first surface layer made of inorganic zinc material is It can be laminated to a thickness of 70-80 μm.

In addition, on the surface of the grand box 100 for the turbine, a second surface layer made of a curable resin including an epoxy resin may be laminated on the outside of the first surface layer to a thickness of 95 to 105 μm.

Accordingly, a first surface layer made of an inorganic zinc material and a second surface layer made of a curable resin including an epoxy resin are double laminated on the surface of the grand box 100 for a turbine, so that durability can be remarkably improved.

In this case, terms such as "include", "comprise" or "comprise" described above mean that the corresponding component may be inherent unless otherwise stated, so other components are excluded. Rather, it should be construed as being able to include other components further. All terms including technical and scientific terms have the same meaning as commonly understood by one of ordinary skill in the art to which the present invention belongs, unless otherwise defined. Commonly used terms such as terms defined in the dictionary should be interpreted as being consistent with the contextual meaning of the related art, and are not interpreted in an ideal or excessively formal meaning unless explicitly defined in the present invention.

As described above, the present invention is not limited to each of the above-described embodiments, and modifications can be implemented by those of ordinary skill in the art to which the present invention pertains without departing from the scope of the claims of the present invention. and such modifications are within the scope of the present invention.

10: body part 11: opposing surface
13: fixing hole 14: pressure discharge slit groove
20: pressure control pipe part 30: reinforcing rib part
31: thread coupling groove 34: recessed groove
100: grand box for turbine

Claims (5)

It is provided to be round in a ring shape so as to surround the inner periphery of the outer periphery of the rotor disposed inside the boundary region between the high-pressure end and the medium-pressure end of the turbine, and is provided with a predetermined thickness along the axial direction of the rotor and divided into a plurality of places along the circumferential direction, , A body portion having a plurality of fixing holes formed through each of the divided opposing surfaces;
a pressure regulating pipe part connected to the outside of the main body and having a discharge passage formed therein, an inner end of the discharge passage communicating with one of the outer circumferences of the main body, and an outer end communicating with the outside; and
A plurality of doedoe provided along the axial direction of the rotor on the inner periphery of the main body, each extending radially inwardly toward the outer periphery of the rotor along the circumferential direction, each inner so that sealing devices aligned opposite to the inner periphery of the rotor are inserted Including a plurality of reinforcing ribs in which the thread coupling grooves are recessed outward in the radial direction along the circumferential direction at the end,
Among the reinforcing ribs, the edges of the reinforcing ribs on the central side are protruded to be inclined at a predetermined angle along the axial direction of the rotor toward the inner side in the radial direction along the circumferential direction, and are secondarily extended in a direction perpendicular to the outer periphery of the rotor. extended and protruding,
Doedoe, the first extension protruding between the edges of each of the reinforcing ribs spaced apart along the axial direction of the rotor, a recessed groove is expanded and expanded in an inclined direction along the axial direction of the rotor as it goes outward in the radial direction along the circumferential direction, and each is recessed.
A pressure discharge slit groove is formed in the opposite surface of each divided body part in a depression along the circumferential direction of the body part and extends to be bent along the radial direction,
Each inner end of the pressure discharge slit groove communicates with each of the recessed grooves, and the outer end communicates with the outside. delete delete The method of claim 1,
An extended fastening portion is formed on one side of the divided body portion opposite to each other to extend integrally outwardly in the radial direction, and the opposite surface is formed on one surface,
On the outer side of the extended fastening part, a protrusion is integrally extended outward in a radial direction, the opposite surface is continuously formed on the protrusion, and an outer end of the pressure discharge slit groove is disposed,
An inner end of the discharge passageway is a grand box for a turbine, characterized in that it communicates with the recessed groove. 5. The method of claim 4,
Each of the fixing holes are spaced apart from each other along the axial direction of the rotor in the extension fastening part and are formed through, and at the same time, are spaced apart from each other along the radial direction of the main body on one side of the protrusion and are formed through each other. .

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