KR102655156B1 - Stator for turbo-machine - Google Patents

Abstract

The present invention includes a casing into which fluid flows; A plurality of vanes coupled to the inner peripheral surface of the casing and disposed along the circumferential direction of the casing; It includes a sealing assembly installed between adjacent vanes and sealing the space between them, wherein the sealing assembly is inserted into one of the adjacent vanes, a main seal member inserted into each vane, and an adjacent vane, It includes a cover seal member surrounding one end of the main seal member, wherein the cover seal member has a cover body portion, protrudes from the cover body portion to the main seal member, and is spaced apart from each other along the radial direction of the casing. A stator for a turbo machine is provided, including a pair of first cover protrusions that surround one end of the main seal member from the radial inner and outer sides, and a second cover protrusion that protrudes radially outward from the cover body portion.

Description

Stator for turbo machine {Stator for turbo-machine}

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

A turbomachine refers to a device that generates power for power generation through fluid (particularly gas) passing through the turbomachine. Therefore, turbo machines are usually installed and used together with generators. These turbo machines may include gas turbines, steam turbines, wind power turbines, etc. A gas turbine is a device that generates combustion gas by mixing compressed air and natural gas and combustion, and uses the generated combustion gas to generate power for power generation. 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 power generation.

Looking at the gas turbine among turbo machines, the gas turbine includes a compressor, combustor, and turbine. The compressor has a plurality of compressor vanes and compressor blades arranged alternately within the compressor casing. And the compressor sucks in external air through the compressor inlet scroll strut. The air sucked in this way passes through the inside of the compressor and is compressed by the compressor vanes and compressor blades. The combustor receives compressed air from the compressor and mixes it with fuel. Additionally, the combustor ignites fuel mixed with compressed air with an igniter to generate high-temperature, high-pressure combustion gas. The combustion gas generated in this way is supplied to the turbine. The turbine has a plurality of turbine vanes and turbine blades arranged alternately within the turbine casing. And the turbine receives the combustion gas generated from the combustor and passes it inside. The combustion gas passing through the inside of the turbine rotates the turbine blades, and the combustion gas that has completely passed through the inside of the turbine is discharged to the outside through the turbine diffuser.

Looking at the steam turbine among turbomachines, the steam turbine includes an evaporator and a turbine. The evaporator generates steam by heating water supplied from the outside. The turbine, like the turbine in a gas turbine, has a plurality of turbine vanes and turbine blades arranged alternately within the turbine casing. However, the turbine in a steam turbine rotates the turbine blades by passing steam generated in the evaporator, not combustion gas, inside.

Meanwhile, the turbine of a turbo machine includes a turbine stator that guides the high-temperature fluid (steam or combustion gas) flowing inside, and a turbine rotor that is placed inside the turbine stator and rotates by the flowing high-temperature fluid to generate power. Includes. And the turbine stator includes a turbine casing and a plurality of turbine vanes coupled to the inner peripheral surface of the turbine casing.

A seal member is installed between turbine vanes adjacent to each other in the circumferential direction of the turbine casing to prevent high-temperature fluid from passing through. These seal members are usually formed in a typical plate shape, but the conventional seal member has a tight assembly tolerance, making it difficult to assemble it to the turbine vane. In addition, according to the conventional turbo machine, the gap between the seal member and the slot of the turbine vane must be designed to be relatively large in consideration of the assemblage of parts and the relative displacement between parts during operation of the turbo machine, so that high-temperature fluid flows through the gap. There is a problem that the amount of leakage is excessive.

U.S. Patent No. 5975944 (Title of invention: Sealing element for sealing a gap and gas turbine plant)

The present invention was developed to solve the above problems, and its purpose is to provide a stator for a turbo machine that is easy to assemble and can effectively seal between adjacent turbine vanes.

The present invention includes a casing into which fluid flows; A plurality of vanes coupled to the inner peripheral surface of the casing and disposed along the circumferential direction of the casing; It includes a sealing assembly installed between adjacent vanes and sealing the space between them, wherein the sealing assembly is inserted into one of the adjacent vanes, a main seal member inserted into each vane, and an adjacent vane, It includes a cover seal member surrounding one end of the main seal member, wherein the cover seal member has a cover body portion, protrudes from the cover body portion to the main seal member, and is spaced apart from each other along the radial direction of the casing. A stator for a turbo machine is provided, including a pair of first cover protrusions that surround one end of the main seal member from the radial inner and outer sides, and a second cover protrusion that protrudes radially outward from the cover body portion.

The main seal 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 seal member, and a second connection portion connected to the other end of the sealing plate portion. You 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 includes a first vane formed with a first slot into which one end of the cover seal member and the main seal member is inserted, and a second slot adjacent to the first vane and into which the other end of the main seal member is inserted. It may include a second vane formed.

The first slot may have a radial reference width of the casing that is larger than that of the second slot.

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

The main seal member includes 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 seal member, and the cover seal member includes the pair of first connection portions. Each of the cover protrusions protrudes from the other end toward the sealing plate portion, and may further include a pair of auxiliary protrusions supporting the first connection portion on the other side of the first connection portion.

In addition, the present invention includes a casing into which fluid flows; A plurality of vanes coupled to the inner peripheral surface of the casing and disposed along the circumferential direction of the casing; It includes a sealing assembly installed between adjacent vanes and sealing the space between them, wherein the sealing assembly is inserted into one of the adjacent vanes, a main seal member inserted into each vane, and an adjacent vane, It includes a cover seal member surrounding one end of the main seal member, and the plurality of vanes include a first vane having a first slot into which the cover seal member and one end of the main seal member are inserted, and adjacent to the first vane. It includes a second vane in which a second slot is formed into which the other end of the main seal member is inserted, and the cover seal member includes a cover body portion surrounding one end of the main seal member and protruding from the cover body portion to the other side. , It includes a pair of cover protrusions respectively disposed on the radial inner and outer sides of the main seal member, wherein the first slot is a first main slot into which the cover body part is inserted, and the pair of cover protrusions are inserted into it. A stator for a turbo machine including a first auxiliary slot to be inserted is provided.

In the stator for a turbo machine according to the present invention, the main seal member includes 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 seal member, The cover body portion is formed in a circular shape to surround the first connection portion, and the pair of cover protrusions supports the other side of the first connection portion and bends in a direction away from the sealing plate portion as it moves from the cover body portion to the other side. can be formed.

According to the turbomachine assembly according to the present invention, a sealing assembly installed between adjacent turbine vanes and sealing the gap between them is inserted into the main seal member and one of the adjacent vanes and the main seal. By designing the structure to include 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 attempting to assemble the sealing assembly between the turbine vanes, 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 slot of the second vane. By assembling it by inserting it into a slot, easier assembly is possible, the sealing assembly and the first and second slots absorb the deviations that occur during assembly and manufacturing, and assembly stability is ensured. The sealing assembly absorbs the relative displacement of internal components during machine operation, minimizing leakage of high-temperature fluid between turbine vanes and improving structural life and stability.

Figure 1 is a cross-sectional view of a gas turbine among turbo machines.
Figure 2 is a perspective view of the turbine vane disclosed in Figure 1.
Figure 3 is a perspective view of a sealing assembly according to a first embodiment of the present invention.
Figure 4 is a cross-sectional view showing the sealing assembly of Figure 3 installed between the turbine vane (first vane) and the turbine vane (second vane).
Figure 5 is a perspective view showing the sealing assembly according to the second embodiment of the present invention installed between the turbine vane (first vane) and the turbine vane (second vane).

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

Hereinafter, the 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 it goes without saying that the turbo machine according to the present invention may correspond to a steam turbine rather than a gas turbine (1). will be.

Referring to Figure 1, the 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 placed on the upstream side of the gas turbine 1 and the turbine 4 is placed on the downstream side. And a combustor (3) is disposed between the compressor (2) and the turbine (4).

The compressor 2 accommodates the compressor vanes and the compressor rotor inside the compressor casing, and the turbine 4 accommodates the turbine vanes 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 sucked air can be compressed, and on the contrary, the turbine (4) allows the combustion gas supplied from the combustor to expand. It is designed with a structure in which the internal space increases from the front to the rear.

Meanwhile, between the compressor rotor located at the extreme end of the compressor 2 and the turbine rotor 20 located at the extreme end of the turbine 4, the rotational torque generated by the turbine 4 is transferred to the compressor 2. A torque tube as a torque transmitting member is disposed. The torque tube may be composed of a plurality of torque tube disks consisting of a total of three stages as shown in Figure 1, 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 be composed of a plurality of torque tube disks consisting of two or less stages.

The compressor rotor includes a compressor disk and compressor blades. A plurality of compressor disks (for example, 14 disks) are provided inside the compressor casing, and each compressor disk is fastened by a tie rod so as not to be spaced apart in the axial direction. More specifically, each of the compressor disks is aligned with each other along the axial direction with its central portion penetrated by the tie rod. In addition, the opposing surfaces of each adjacent compressor disk are compressed by the tie rod and are arranged so that they cannot rotate relative to each other.

A plurality of compressor blades are radially coupled to the outer peripheral surface of the compressor disk. Additionally, a plurality of compressor vanes are disposed between the compressor blades in an annular shape on the inner peripheral surface of the compressor casing based on 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 located downstream by aligning the flow of compressed air passing through the compressor blade. At this time, the compressor casing and compressor vane may be defined by the comprehensive name of compressor stator to distinguish them from the compressor rotor.

The tie rod is disposed to penetrate the center of the plurality of compressor disks and the turbine disk, which will be described later, and one end is fastened to 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 have 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 that penetrates the central part of the compressor disk and the turbine disk, or a plurality of tie rods may have a shape arranged circumferentially, and a combination of these is also possible.

Although not shown, a deswirler that acts as a guide blade may be installed in the compressor of a gas turbine to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor inlet to the design flow angle.

The combustor (3) mixes and combusts the incoming compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas. Through the isobaric combustion process, the temperature of the combustion gas is raised to the heat resistance limit that the combustor and turbine parts can withstand. It becomes higher.

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

Specifically, the liner provides a combustion space where the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and burned. This liner is formed with a combustion chamber that provides a combustion space in which fuel mixed with air is burned, and a liner annular flow path that surrounds the combustion chamber and forms an annular space. Additionally, a nozzle that injects fuel is coupled to the front end of the liner, and an igniter is coupled to the side wall.

In the liner annular flow path, compressed air flowing in through a plurality of holes provided on the outer wall of the liner flows, and compressed air that cools the transition piece, which will be described later, also flows through it. As 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 combustion gas burned by the spark plug to the turbine side. Like the liner, the transition piece is formed with a transition piece annular passage surrounding the internal space of the transition piece, and the outer wall is formed by compressed air flowing along the transition piece annular passage to prevent damage due to the high temperature of combustion gas. part cools down.

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 as it passes through the interior of the turbine 4, and accordingly applies impulse and reaction forces to the turbine blades 22, which will be described later, to generate rotational torque. The rotational torque obtained in this way is transmitted to the compressor through the torque tube described above, and the portion exceeding the power required to drive the compressor is used to drive a generator, etc.

The turbine 4 is basically similar in structure to 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. Accordingly, the turbine rotor 20 also includes a turbine disk 21 and a plurality of turbine blades 22 disposed radially from the turbine disk 21. Between the turbine blades 22, a plurality of turbine vanes 12 are installed in an annular shape on the turbine casing 11 when based on the same stage, and the turbine vanes 12 are connected to the turbine blades 22. ) guides the direction of flow of the combustion gas that has passed through it. At this time, the turbine casing 11 and the turbine vane 12 may also be defined by the comprehensive name turbine stator 10 to distinguish them from the turbine rotor 20.

For convenience of explanation, from now on, the radial direction is referred to as R, the circumferential direction is referred to as C, and the axial direction is referred to as X, based on 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 peripheral 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 inner side of the inner shroud 15 in the radial direction (R) and is disposed between the turbine disk 21 and the turbine disk 21 adjacent to each other 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 seal the space between them. Specifically, the sealing assemblies 100 and 200 are installed in the portion of the turbine vane 12 excluding the airfoil 14. For example, the sealing assemblies 100 and 200 are located between the outer shrouds 13 and the inner shrouds 13 adjacent to each other in the circumferential direction (C), between the inner shrouds 15 and the inner shrouds 15, and between the U-rings. It can be installed between the and U-ring. 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.

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

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

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

The cover seal 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 portion 112 from the inside and outside in the radial direction (R). The second cover protrusion 122 protrudes outward from the cover body 121 in the radial direction (R). The pair of auxiliary protrusions 124 each protrude from the other end of the pair of first cover protrusions 122 toward the sealing plate part 111, and the second protrusion is formed on the other side of the first connection part 112. 1Supports the connection portion 112.

The first slot 31 includes a first main slot 32 and a first auxiliary slot 33. The cover body portion 121 and the second cover protrusion portion 123 are inserted into the first main slot 32. The first auxiliary slot 33 is into which the pair of first cover protrusions 122 and the first connection part 112 are inserted, and has a radial width (R) 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 their 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. The length from the inner surface to the outer surface in the radial direction (R) of the first main slot 32 is formed to be larger than that of the second main slot 33.

However, this is only an example, and the second cover protrusion 123 may protrude inward in the radial direction (R) of the cover body portion 121. And the first main slot 32 and the second main slot 33 are formed such that their 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 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 seal member 110 and a cover seal member 130. Here, since the main seal member 110 is the same as that in the first embodiment, its description is omitted.

The cover seal member 130 includes a cover main body 131 and a pair of cover protrusions 132. The cover body portion 131 surrounds the first connection portion 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 disposed on the inside and outside of the sealing plate part 111 in the radial direction (R), respectively. At this time, the pair of cover protrusions 132 supports the other side of the first connection portion 112 and is bent in a direction away from the sealing plate portion 111 as it moves from the cover body portion 131 to the other side. It can be.

In the second embodiment of the present invention, like the first embodiment, the first slot 31 includes a first main slot 32 and a first auxiliary slot 33. The cover body portion 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 larger radial width (R) than the first auxiliary slot 33. At this time, unlike the first embodiment, in the second embodiment, the radial (R) inner surface of the first main slot (32) is larger than the radial (R) inner surface of the first auxiliary slot (33). It is disposed further inward, and the radial (R) outer surface of the first main slot (32) may be disposed further outer than the radial (R) outer surface of the first auxiliary slot (33).

100,200: Sealing assembly 110: Main seal member
111: sealing plate part 112: first connection part
113: second connection 120,130: cover seal member
121,131: Cover main body 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 the inner peripheral surface of the casing and disposed along the circumferential direction of the casing;
Includes a sealing assembly installed between adjacent vanes to seal the space between them,
The sealing assembly is,
A main seal member inserted into each adjacent vane and the vane,
It is inserted into one of the adjacent vanes and includes a cover seal member surrounding one end of the main seal member,
The cover seal member is,
Cover body part,
a pair of first cover protrusions that protrude from the cover body portion to the main seal member, are spaced apart from each other along the radial direction of the casing, and surround one end of the main seal member from the inside and outside in the radial direction;
A stator for a turbo machine including a second cover protrusion protruding radially outward from the cover main body. In claim 1,
The main seal member is,
A sealing plate portion formed in a plate shape,
A first connection part connected to one end of the sealing plate part and inserted into the cover seal member,
A stator for a turbo machine including a second connection part connected to the other end of the sealing plate part. In claim 2,
The first connection part and the second connection part are a stator for a turbo machine each formed in a circular shape when viewed along the flow direction of the fluid. In claim 1,
The plurality of vanes are,
A first vane having a first slot into which one end 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. In claim 4,
The first slot is a stator for a turbo machine in which the radial reference width of the casing is larger than that of the second slot. delete In claim 4,
The first slot is,
A first main slot into which the cover body portion and the second cover protrusion are inserted,
A stator for a turbo machine including a first auxiliary slot into which the pair of first cover protrusions and one end of the main seal member are inserted and whose radial width is smaller than the first main slot. In claim 1,
The main seal member is,
A sealing plate portion formed in a plate shape,
It is connected to one end of the sealing plate portion and includes a first connection portion inserted into the cover seal member,
The cover seal member is,
The stator for a turbo machine further includes a pair of auxiliary protrusions that each protrude from other ends of the pair of first cover protrusions toward the sealing plate portion and support the first connection portion on the other side of the first connection portion. A casing through which fluid flows;
A plurality of vanes coupled to the inner peripheral surface of the casing and disposed along the circumferential direction of the casing;
Includes a sealing assembly installed between adjacent vanes to seal the space between them,
The sealing assembly is,
A main seal member inserted into each adjacent vane and the vane,
It is inserted into one of the adjacent vanes and includes a cover seal member surrounding one end of the main seal member,
The plurality of vanes are,
A first vane having a first slot into which one end of the cover seal member and the main seal member are inserted,
It is adjacent to the first vane and includes a second vane formed with a second slot into which the other end of the main seal member is inserted,
The cover seal member is,
A cover body portion surrounding one end of the main seal member,
It protrudes from the cover body portion to the other side and includes a pair of cover protrusions disposed respectively on a radial inner side and an outer side of the main seal member,
The first slot is,
A first main slot into which the cover body part is inserted,
A stator for a turbo machine including a first auxiliary slot into which the pair of cover protrusions are inserted. In claim 9,
The main seal member is,
A sealing plate portion formed in a plate shape,
It is connected to one end of the sealing plate portion and includes a first connection portion inserted into the cover seal 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 as it moves from the cover body portion to the other side.