KR20220151871A - Stator for turbo-machine - Google Patents

Abstract

The present invention provides a stator for a turbo-machine, comprising a casing in which a fluid flows; a plurality of vanes coupled to the inner circumferential surface of the casing and arranged along the circumferential direction of the casing; and a sealing assembly installed between adjacent vanes to seal the gap therebetween, wherein the seal assembly includes a main seal member inserted to each of the adjacent vanes and a cover seal member inserted to one of the adjacent vanes and covering one end of the main seal member. The stator for a turbo-machine according to the present invention is easy to assemble and can effectively seal adjacent turbine vanes.

Description

Stator for turbo-machine {Stator for turbo-machine}

The present invention relates to a stator for a turbo machine, and more particularly, to a stator used in a turbo machine that generates power for power generation by passing a high-temperature fluid (steam or combustion gas) therein.

A turbo machine means a device that generates power for power generation through a fluid (particularly, a gas) passing through the turbo machine. Therefore, turbomachines are usually installed and used together with generators. Such turbomachines may include gas turbines, steam turbines, wind power turbines, and the like. A gas turbine is a device that generates combustion gas by mixing and combusting compressed air and natural gas, and generates power for power generation using the combustion gas generated in this way. A steam turbine is a device that generates power for power generation using steam generated by heating water. A wind turbine is a device that converts wind power into power for electricity generation.

Looking at a gas turbine among turbomachines, a gas turbine includes a compressor, a combustor, and a turbine. In the compressor, a plurality of compressor vanes and compressor blades are alternately arranged in a compressor casing. And the compressor sucks in air from the outside through a compressor inlet scroll strut. Air sucked in as described above is compressed by the compressor vanes and compressor blades while passing through the inside of the compressor. The combustor receives compressed air from the compressor and mixes it with fuel. In addition, the combustor generates high-temperature and high-pressure combustion gas by igniting the fuel mixed with compressed air with an igniter. The combustion gas thus generated is supplied to the turbine. In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a turbine casing. The turbine receives the combustion gas generated from the combustor and passes it through the inside. The combustion gas passing through the inside of the turbine rotates the turbine blades, and the combustion gas passing completely through the inside of the turbine is discharged to the outside through the turbine diffuser.

Looking at a steam turbine among turbomachines, the steam turbine includes an evaporator and a turbine. The evaporator generates steam by heating water supplied from the outside. Like a turbine in a gas turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a turbine casing. However, the turbine in the steam turbine rotates the turbine blades by passing the steam generated in the evaporator instead of the combustion gas to the inside.

On the other hand, the turbine of the turbo machine includes a turbine stator that guides a high-temperature fluid (steam or combustion gas) flowing therein, and a turbine rotor disposed inside the turbine stator and rotating by the flowing high-temperature fluid to generate power. includes The turbine stator includes a turbine casing and a plurality of turbine vanes coupled to an inner circumferential surface of the turbine casing.

A seal member is installed between adjacent turbine vanes in the circumferential direction of the turbine casing to prevent high-temperature fluid from passing therethrough. Such a seal member is usually formed in a typical plate shape, but the conventional seal member has a problem in that it is difficult to assemble to a turbine vane due to tight assembly tolerance. In addition, according to the conventional turbo machine, the gap between the seal member and the slot of the turbine vane should be designed to be relatively large in consideration of the assembly of parts or the relative displacement between parts during operation of the turbo machine. The problem is that the amount of leakage is excessive.

US Patent Registration No. 5975944 (Title of Invention: Sealing element for sealing a gap and gas turbine plant)

The present invention has been developed to solve the above problems, and an object of the present invention is to provide a stator for a turbo machine that can effectively seal between adjacent turbine vanes while being easy to assemble.

The present invention, the casing through which the fluid flows into the interior; a plurality of vanes coupled to an inner circumferential surface of the casing and disposed along a circumferential direction of the casing; A sealing assembly installed between adjacent vanes to seal the gap, wherein the sealing assembly is inserted into either a main seal member inserted into the adjacent vane or the vane, and an adjacent vane or vane, , It provides a stator for a turbo machine including a cover seal member surrounding one end of the main seal member.

The main sealing member may include a sealing plate portion formed in a plate shape, a first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member, and a second connection portion connected to the other end of the sealing plate portion. can

The first connection part and the second connection part may each be formed in a circular shape when viewed along the flow direction of the fluid.

The plurality of vanes include a first vane formed with a first slot into which one end of the cover seal member and the main seal member are inserted, and a second slot adjacent to the first vane and into which the other end of the main seal member is inserted. This may include a formed second vane.

In the first slot, a reference width of the casing in a radial direction may be greater than that of the second slot.

The cover seal member protrudes from the cover body portion and the main seal member from the cover body portion, and is disposed spaced apart from each other along the radial direction of the casing to surround one end of the main seal member from the inside and outside in the radial direction It may include a pair of first cover protrusions and a second cover protrusion protruding outward in a radial direction from the cover body.

The first slot includes a first main slot into which the cover body and the second cover protrusion are inserted, and one end of the pair of first cover protrusions and the main seal member is inserted, and has a radial width equal to the first It may include a first subslot smaller than the main slot.

The main sealing member includes a sealing plate portion formed in a plate shape, and a first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member, wherein the cover sealing member includes the pair of first A pair of auxiliary protrusions protruding from the other end of the cover protrusion toward the sealing plate portion and supporting the first connection portion at the other side of the first connection portion may be further included.

The cover seal member includes a cover body portion surrounding one end of the main seal member and a pair of cover protrusions protruding from the cover body portion to the other side and disposed on the inside and outside of the main seal member in a radial direction, respectively. can do.

The main sealing member includes a sealing plate portion formed in a plate shape, and a first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member, and the cover body portion surrounds the first connection portion It is formed in a circular shape, and the pair of cover protrusions support the other side of the first connection portion, and may be formed to be bent in a direction away from the sealing plate portion toward the other side from the cover body portion.

According to the assembly for a turbo machine according to the present invention, a sealing assembly installed between adjacent turbine vanes and sealing between them is inserted into a main seal member and any one of the adjacent vanes and the main seal By designing a structure including a cover seal member surrounding one end of the member, it is possible to provide a stator for a turbo machine that is easy to assemble and can effectively seal between adjacent turbine vanes.

Specifically, when assembling the sealing assembly between the turbine vane and the turbine vane, first insert the cover seal member into the first slot of the first vane, and then insert the main seal member into the cover seal member and the second vane of the second vane. By assembling by inserting into the slot, it enables easier assembly, allows the sealing assembly and the first slot and the second slot to absorb deviations generated during assembly and manufacturing, and secures assembly stability. The sealing assembly absorbs the relative displacement of internal parts during machine operation, thereby minimizing leakage of high-temperature fluid between turbine vanes and improving structural life and stability.

1 is a cross-sectional view of a gas turbine among turbomachines.
FIG. 2 is a perspective view of the turbine vane shown in FIG. 1 .
3 is a perspective view of a sealing assembly according to a first embodiment of the present invention.
4 is a cross-sectional view showing a state in which the sealing assembly of FIG. 3 is installed between a turbine vane (first vane) and a turbine vane (second vane).
5 is a perspective view showing a state in which a sealing assembly according to a second embodiment of the present invention is installed between a turbine vane (first vane) and a turbine vane (second vane).

Although the present invention has been described with reference to the embodiments shown in the drawings, this is only exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true technical scope of protection of the present invention should be determined by the technical spirit of the appended claims.

Hereinafter, a stator for a turbo machine according to the present invention will be described with reference to the drawings. At this time, the turbo machine will be described assuming that it is a gas turbine (1), but this is only an example, and the turbo machine according to the present invention may correspond to a steam turbine other than the gas turbine (1). will be.

Referring to FIG. 1 , a gas turbine 1 according to the present invention includes a compressor 2, a combustor 3 and a turbine 4. Based on the flow direction of gas (compressed air or combustion gas), the compressor 2 is disposed on the upstream side of the gas turbine 1 and the turbine 4 is disposed on the downstream side. A combustor 3 is disposed between the compressor 2 and the turbine 4.

The compressor 2 accommodates the compressor vane and the compressor rotor inside the compressor casing, and the turbine 4 accommodates the turbine vane 12 and the turbine rotor 20 inside the turbine casing 11. These compressor vanes and compressor rotors are arranged in multi-stages along the flow direction of compressed air, and the turbine vanes 12 and turbine rotors 20 are also arranged in multi-stages along the flow direction of combustion gas. At this time, the internal space of the compressor 2 decreases from the front-stage to the rear-stage so that the intake air can be compressed, and the turbine 4, on the contrary, expands the combustion gas supplied from the combustor. It is designed with a structure in which the internal space increases from the front end to the rear end.

On the other hand, between the compressor rotor located at the rear end of the compressor 2 and the turbine rotor 20 located at the front end of the turbine 4, the rotational torque generated in the turbine 4 is transferred to the compressor 2 A torque tube as a torque transmission member for transmitting to is disposed. As shown in FIG. 1, the torque tube may be composed of a plurality of torque tube disks having a total of three stages, but this is only one of several embodiments of the present invention, and the torque tube may have four or more stages or It may also consist of a plurality of torque tube disks with two or less stages.

The compressor rotor includes a compressor disk and a compressor blade. A plurality of (for example, 14) compressor disks are provided inside the compressor casing, and each of the compressor disks is fastened by tie rods so as not to be spaced apart in the axial direction. More specifically, the respective compressor disks are axially aligned with each other with their central portions pierced by the tie rods. And, each of the adjacent compressor disks is arranged such that opposing surfaces are compressed by the tie rods and cannot rotate relative to each other.

A plurality of compressor blades are radially coupled to an outer circumferential surface of the compressor disk. In addition, between the compressor blades, a plurality of compressor vanes which are annularly installed on the inner circumferential surface of the compressor casing are disposed on the basis of the same stage. Unlike the compressor disk, the compressor vane maintains a fixed state so as not to rotate, and serves to guide the compressed air to the compressor blade positioned downstream by aligning the flow of compressed air passing through the compressor blade. In this case, the compressor casing and the compressor vane may be defined as a comprehensive name of a compressor stator in order to be distinguished from the compressor rotor.

The tie rod is disposed to pass through the center of the plurality of compressor disks and a turbine disk to be described later, one end is fastened into the compressor disk located at the front end of the compressor, and the other end is fastened by a fixing nut. do.

Since the shape of the tie rod may be formed in various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 1 . That is, as shown, one tie rod may have a shape penetrating the center of the compressor disk and the turbine disk, or a plurality of tie rods may be arranged in a circumferential shape, and a combination thereof is possible.

Although not shown, a deswirler serving as a guide vane may be installed in the compressor of the gas turbine to adjust the flow angle of the fluid entering the inlet of the combustor to the design flow angle after increasing the pressure of the fluid.

In the combustor 3, the introduced compressed air is mixed with fuel and combusted to produce high-energy, high-temperature, high-pressure combustion gas. will raise

A plurality of combustors constituting the combustion system of the gas turbine 1 may be arranged in a combustor casing formed in a cell shape, and a nozzle for injecting fuel, a liner for forming a combustion chamber, and a combustor It includes a transition piece that becomes a connection part of the turbine.

Specifically, the liner provides a combustion space in which fuel injected through a fuel nozzle is mixed with compressed air of a compressor and burned. Such a liner is formed with a combustion chamber providing a combustion space in which fuel mixed with air is combusted, and an annular liner passage forming an annular space while surrounding the combustion chamber. In addition, a nozzle for injecting fuel is coupled to the front end of the liner, and an igniter is coupled to the side wall.

Compressed air introduced through a plurality of holes provided in the outer wall of the liner flows in the annular liner flow passage, and compressed air cooling a transition piece to be described later also flows therethrough. As the compressed air flows along the outer wall of the liner, it is possible to prevent the liner from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

At the rear end of the liner, a transition piece is connected to send the combustion gas burned by the spark plug to the turbine side. Like the liner, the transition piece has a transition piece annular flow path surrounding the inner space of the transition piece, and the outer wall is compressed by compressed air flowing along the transition piece annular flow path to prevent damage due to high temperature of the combustion gas. part is cooled

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor 3 is supplied to the turbine 4 described above. The high-temperature, high-pressure combustion gas supplied to the turbine 4 expands while passing through the inside of the turbine 4, and thus applies impulse and reaction forces to the turbine blades 22, which will be described later, so that rotational torque is generated. The rotational torque obtained in this way is transmitted to the compressor via the above-described torque tube, and a portion exceeding the power necessary for driving the compressor is used to drive a generator or the like.

The turbine 4 is basically similar to the structure of the compressor 2. That is, the turbine 4 is also provided with a plurality of turbine rotors 20 similar to the compressor rotor of the compressor 2. Therefore, the turbine rotor 20 also includes a turbine disk 21 and a plurality of turbine blades 22 radially disposed therefrom. Also between the turbine blades 22, a plurality of turbine vanes 12 are provided, which are annularly installed in the turbine casing 11 when based on the same stage, and the turbine vanes 12 are turbine blades 22 ) guides the flow direction of the combustion gas passing through. At this time, the turbine casing 11 and the turbine vane 12 may also be defined as a comprehensive name of the turbine stator 10 in order to distinguish them from the turbine rotor 20 .

For convenience of explanation, hereinafter, the radial direction is referred to as R, the circumferential direction as C, and the axial direction as X with respect to the turbine casing 11. The flow direction of the high-temperature fluid (combustion gas) flowing inside the turbine casing 11 is included in the axial direction X.

Referring to FIG. 2 , the turbine vane 12 includes an outer shroud 13, an airfoil 14, an inner shroud 15, and a U-ring (not shown). The outer shroud 13 is coupled to the inner circumferential surface of the turbine casing 11 . The airfoil 14 is coupled to the inside of the outer shroud 13 in the radial direction R, and guides the flowing high-temperature fluid to the rear end. The inner shroud 15 is coupled to the inside of the airfoil 14 in the radial direction R. The U-ring is coupled to the inside of the inner shroud 15 in the radial direction R, and is disposed between adjacent turbine disks 21 and 21 along the axial direction X.

The turbine stator 10 further includes sealing assemblies 100 and 200 . The sealing assemblies 100 and 200 are installed between adjacent turbine vanes 12 and turbine vanes 12 and seal between them. Specifically, the sealing assemblies 100 and 200 are installed in a portion of the turbine vane 12 excluding the airfoil 14 . For example, the sealing assemblies 100 and 200 are formed between the outer shroud 13 and the outer shroud 13 adjacent in the circumferential direction C, between the inner shroud 15 and the inner shroud 15, and the U ring It can be installed between the and U-rings. The first slot 31 and the second slot 41, which will be described later, are also formed in the outer shroud 13, the inner shroud 15, and the U ring.

Referring to FIGS. 3 and 4 , the sealing assembly 100 according to the first embodiment of the present invention includes a main sealing member 110 and a cover sealing member 120 . The main seal member 110 is inserted into adjacent turbine vanes 12 and turbine vanes 12 , respectively. The cover seal member 120 is inserted into any one of the adjacent turbine vane 12 and the turbine vane 12 and surrounds one end of the main seal member 110 . Hereinafter, the turbine vane 12 into which the cover seal member 120 is inserted is disposed on one side (left side of FIG. 4) of the main seal member 110, and is referred to as the first vane 30, and the main seal The turbine vane 12 disposed on the other side (right side of FIG. 4) of the member 110 is referred to as a second vane 40.

The main sealing member 110 includes a sealing plate part 111, a first connection part 112, and a second connection part 113. The sealing plate portion 111 is formed in a plate shape. The first connection part 112 is connected to one end of the sealing plate part 111 and is inserted into the cover sealing member 120 . The second connection part 113 is connected to the other end of the sealing plate part 111 . The first connecting portion 112 and the second connecting portion 113 may be formed in a circular shape when viewed from the front, but are not limited thereto.

In the first vane 30, a first slot 31 into which ends of the cover seal member 120 and the main seal member 110 are inserted extends along the axial direction X. In the second vane 40, a second slot 41 into which the other end of the main seal member 110 is inserted extends along the axial direction X. In this case, the first slot 31 may have a larger radial width (R) than the second slot 41 .

The cover sealing member 120 includes a cover main body 121, a pair of first cover protrusions 122, a second cover protrusion 123, and a pair of auxiliary protrusions 124. The cover body portion 121 is formed in a block shape. The pair of first cover protrusions 122 protrude from the cover body 121 to the main seal member 110 and are spaced apart from each other along the radial direction R of the turbine casing 11 It is arranged to surround the first connection part 112 in the radial direction (R) inside and outside. The second cover protrusion 122 protrudes outward from the cover body 121 in the radial direction R. The pair of auxiliary protrusions 124 protrude from the other end of the pair of first cover protrusions 122 toward the sealing plate part 111, respectively, and at the other side of the first connection part 112, the first 1 Supports the connecting portion 112.

The first slot 31 includes a first main slot 32 and a first auxiliary slot 33 . In the first main slot 32, the cover body 121 and the second cover protrusion 123 are inserted. The first auxiliary slot 33 is inserted into the pair of first cover protrusions 122 and the first connection part 112, and has a radial direction (R) width smaller than that of the first main slot 32. is formed Specifically, the first main slot 32 and the second main slot 33 are formed so that the inner surfaces in the radial direction R are connected to each other at the same height (radius) from the center of the turbine casing 11. And, the length from the inner surface to the outer surface in the radial direction (R) of the first main slot 32 is formed larger than that of the second main slot 33.

However, this is only an example, and the second cover protrusion 123 may protrude toward the inner side of the cover body 121 in the radial direction R. In addition, the first main slot 32 and the second main slot 33 are formed so that the outer surfaces in the radial direction (R) are connected to each other at the same height (radius) from the center of the turbine casing 11, The length from the outer surface to the inner surface in the radial direction (R) of the first main slot 32 may be formed larger than that of the second main slot 33 .

Referring to FIG. 5 , the sealing assembly 200 according to the second embodiment of the present invention includes a main sealing member 110 and a cover sealing member 130 . Here, since the main sealing member 110 is the same as that in the first embodiment, a description thereof is omitted.

The cover seal member 130 includes a cover main body 131 and a pair of cover protrusions 132 . The cover body part 131 surrounds the first connection part 112 . At this time, the cover body portion 131 may be formed in a circularly curved shape. The pair of cover protrusions 132 protrude from the cover body 131 to the other side, and are respectively disposed inside and outside the sealing plate 111 in the radial direction R. At this time, the pair of cover protrusions 132 support the other side of the first connection portion 112, and are bent in a direction away from the sealing plate portion 111 toward the other side from the cover body portion 131 It can be.

In the second embodiment of the present invention, the first slot 31 includes a first main slot 32 and a first auxiliary slot 33 as in the first embodiment. The cover main slot 131 is inserted into the first main slot 32 , and the pair of cover protrusions 132 are inserted into the first auxiliary slot 33 . The first main slot 32 has a radial direction (R) width larger than that of the first auxiliary slot 33 . At this time, unlike the first embodiment, in the second embodiment, the inner surface of the first main slot 32 in the radial direction R is larger than the inner surface of the first auxiliary slot 33 in the radial direction R. It is disposed further inside, and the outer surface in the radial direction (R) of the first main slot 32 may be disposed further outside than the outer surface in the radial direction (R) of the first auxiliary slot 33 .

100,200: sealing assembly 110: main sealing member
111: sealing plate part 112: first connection part
113: second connection part 120,130: cover seal member
121,131: cover body portion 122: first cover protrusion
123: second cover protrusion 124: auxiliary protrusion
132: cover protrusion

Claims (10)

a casing through which fluid flows;
a plurality of vanes coupled to an inner circumferential surface of the casing and disposed along a circumferential direction of the casing;
Including a sealing assembly installed between adjacent vanes and sealing therebetween,
The sealing assembly,
A main seal member inserted into the adjacent vane and the vane, respectively;
A stator for a turbo machine including a cover seal member inserted into any one of adjacent vanes and vanes and surrounding one end of the main seal member. The method of claim 1,
The main seal member,
A sealing plate portion formed in a plate shape;
A first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member;
A stator for a turbo machine including a second connection portion connected to the other end of the sealing plate portion. The method of claim 2,
The first connection part and the second connection part are each formed in a circular shape when viewed along the flow direction of the fluid. The method of claim 1,
The plurality of vanes,
A first vane having a first slot into which ends of the cover seal member and the main seal member are inserted;
A stator for a turbo machine including a second vane adjacent to the first vane and having a second slot into which the other end of the main seal member is inserted. The method of claim 4,
The stator for a turbo machine wherein the first slot has a larger reference width in the radial direction of the casing than the second slot. The method of claim 4,
The cover seal member,
a cover body,
A pair of first cover protrusions that protrude from the cover body to the main seal member and are spaced apart from each other along the radial direction of the casing to surround one end of the main seal member from inside and outside in the radial direction;
A stator for a turbo machine including a second cover protrusion protruding outward in a radial direction from the cover body. The method of claim 6,
The first slot,
A first main slot into which the cover body and the second cover protrusion are inserted;
A stator for a turbo machine comprising a first auxiliary slot into which one end of the pair of first cover protrusions and the main seal member is inserted and having a radial width smaller than that of the first main slot. The method of claim 6,
The main seal member,
A sealing plate portion formed in a plate shape;
A first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member,
The cover seal member,
The stator for a turbo machine further comprising a pair of auxiliary protrusions protruding from the other ends of the pair of first cover protrusions toward the sealing plate portion and supporting the first connection portion at the other side of the first connection portion. The method of claim 4,
The cover seal member,
A cover body portion surrounding one end of the main seal member;
A stator for a turbo machine comprising a pair of cover protrusions that protrude from the cover body to the other side and are respectively disposed inside and outside the main seal member in a radial direction. The method of claim 9,
The main seal member,
A sealing plate portion formed in a plate shape;
A first connection portion connected to one end of the sealing plate portion and inserted into the cover sealing member,
The cover body portion is formed in a circular shape to surround the first connection portion,
The pair of cover protrusions support the other side of the first connection portion, and are formed to be bent in a direction away from the sealing plate portion toward the other side from the cover body portion.

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