KR102238435B1 - Sealing module of turbine and power generating turbine apparatus having the same - Google Patents

Abstract

The sealing module of the turbine of the present invention is disposed on the inner circumferential surface of the fixture and includes a sealing portion, a shroud, and a labyrinth seal. The sealing portion is disposed on the inner circumferential surface of the fixture. The sealing portion includes a plurality of hollows. The sealing portion extends in the circumferential direction. The shroud surrounds the tip of the turbine blade whose one surface is coupled to the outer peripheral surface of the rotating body. The shroud includes a labyrinth seal protruding toward the sealing portion. The labyrinth seal is a hollow whose width (L) in the axial direction of the rotating body of the opposite surface is the longest distance in the axial direction of the rotating body among the distances formed by any two surfaces facing each other among the plurality of surfaces forming the hollow of the sealing part. It is made longer than or equal to the length of the width (W).
According to the sealing module of the turbine of the present invention, it is possible to reduce the leakage flow of air generated in the turbine, secure an appropriate gap between the sealing portion and the shroud, and at the same time improve the overall efficiency of the turbine device for power generation.

Description

Turbine sealing module and turbine device for power generation including the same {SEALING MODULE OF TURBINE AND POWER GENERATING TURBINE APPARATUS HAVING THE SAME}

The present invention relates to a sealing module of a turbine and a turbine device for power generation including the same.

The turbine device for power generation is a mechanical device that obtains rotational force by impulsive force or reaction force by using a flow of a compressible fluid such as steam or gas, and includes a steam turbine using steam and a gas turbine using high temperature combustion gas.

Among them, the gas turbine is largely composed of a compressor, a combustor and a turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged in the compressor housing.

The combustor supplies fuel to the compressed air compressed by the compressor and ignites it with a burner, thereby generating high-temperature and high-pressure combustion gas.

In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a turbine housing. In addition, the rotor is disposed so as to pass through the center of the compressor, combustor, turbine and exhaust chamber.

Both ends of the rotor are rotatably supported by bearings. Then, a plurality of disks are fixed to the rotor, each blade is connected, and a drive shaft such as a generator is connected to an end of the exhaust chamber side.

This gas turbine does not have a reciprocating mechanism such as a piston of a four-stroke engine, so there is no mutual friction part such as a piston-cylinder, so the consumption of lubricating oil is extremely low. There is an advantage.

Briefly describing the operation of the gas turbine, the compressed air in the compressor is mixed with fuel and combusted to produce a high-temperature combustion gas, and the thus produced combustion gas is injected to the turbine side. The injected combustion gas passes through the turbine vanes and the turbine blades to generate rotational force, thereby rotating the rotor.

Various attempts have been made to improve the efficiency of gas turbines, and one of them is to reduce the amount of leakage of combustion gas. That is, a gap is formed between the end of the turbine and the housing, which is one of the main paths through which combustion gas leaks. Therefore, a sealing module is required to block the leakage as described above.

The present invention provides a sealing module for a turbine capable of reducing a leakage flow of air introduced from a combustor to a turbine, and a turbine device for power generation including the same.

The sealing module of the turbine according to an embodiment of the present invention includes a sealing part, a shroud, and a labyrinth seal. The sealing portion is disposed on the inner circumferential surface of the fixture. The sealing portion includes a plurality of hollows. The sealing portion extends in the circumferential direction. The shroud surrounds the tip of the turbine blade whose one surface is coupled to the outer peripheral surface of the rotating body. The shroud includes a labyrinth seal including a facing surface protruding toward the sealing portion and facing the sealing portion. The labyrinth seal is a hollow whose width (L) in the axial direction of the rotating body of the opposite surface is the longest distance in the axial direction of the rotating body among the distances formed by any two surfaces facing each other among the plurality of surfaces forming the hollow of the sealing part. It is made longer than or equal to the length of the width (W).

In the sealing module of the turbine according to an embodiment of the present invention, the labyrinth seal may be made such that L/W, which is a ratio of the width L and the hollow width W, of the opposite surface of the labyrinth seal is 1 to 3.

In the sealing module of the turbine according to an embodiment of the present invention, the shroud may include two or more labyrinth seals spaced apart from each other along the axial direction.

In the sealing module of the turbine according to an embodiment of the present invention, the shroud includes a first labyrinth seal, and a first labyrinth seal and a second labyrinth seal spaced apart from each other along the axial direction, and the first labyrinth seal and P/W, which is a ratio of the pitch P, which is the distance between the centers of the second labyrinth seal in the axial direction, and the hollow width W, may be 2.5 to 7.

In the sealing module of the turbine according to an embodiment of the present invention, a groove having a thickness thinner than that of the first labyrinth seal and the second labyrinth seal is formed between the first labyrinth seal and the second labyrinth seal, D/W, which is a ratio of the width D and the hollow width W, may be 0.5 to 5.6.

In the sealing module of the turbine according to an embodiment of the present invention, the height difference Tb between the opposite surface of the labyrinth seal and the bottom surface of the groove may be 2L/5 or more and 4L/5 or less.

In the sealing module of the turbine according to an embodiment of the present invention, the sealing unit may be formed such that a plurality of hollow cross-sections are at least one of a triangle, a square, a circle, and a hexagon.

In the sealing module of the turbine according to an embodiment of the present invention, the sealing portion may be a honeycomb seal.

In the sealing module of the turbine according to an embodiment of the present invention, a hollow cross section of the honeycomb seal may be a regular hexagon.

In the sealing module of the turbine according to an embodiment of the present invention, the other surface of the shroud is the bottom surface having the thinnest thickness of the shroud, the thickness of the shroud is the thickest, It includes a protruding surface connecting the opposite surface, and a bottom surface and a lower portion of the protruding surface may be connected to a curved surface.

In the sealing module of the turbine according to an embodiment of the present invention, the opposing surface and the upper portion of the protruding surface may meet at a predetermined angle.

The sealing module of the turbine according to an embodiment of the present invention includes a sealing part, a shroud, and a labyrinth seal. The sealing portion is disposed on the inner circumferential surface of the fixture. The sealing portion includes a plurality of hollows. The sealing portion extends in the circumferential direction. The shroud surrounds the tip of the turbine blade whose one surface is coupled to the outer peripheral surface of the rotating body. The shroud includes a labyrinth seal including a facing surface protruding toward the sealing portion and facing the sealing portion. The labyrinth seal is made to cover at least one surface of the sealing portion included in the virtual surface in which the width of the opposite surface crosses the axial direction of the rotating body along the circumferential direction.

In the sealing module of the turbine according to an embodiment of the present invention, the facing surface crosses the axial direction and may be formed to cover two or more surfaces of the sealing portion included in at least two virtual surfaces spaced apart in the axial direction along the circumferential direction. .

In the sealing module of the turbine according to an embodiment of the present invention, the shroud may include two or more labyrinth seals spaced apart from each other along the axial direction.

In the sealing module of the turbine according to an embodiment of the present invention, in the spaced section in the axial direction between the centers of the first labyrinth seal and the second labyrinth seal axially spaced apart from the first labyrinth seal, crossing the axial direction And 2 to 7 surfaces of the sealing part included in the virtual surfaces spaced apart from each other in the axial direction may be disposed.

A turbine device for power generation according to an embodiment of the present invention includes a compressor, a combustor, and a turbine. The compressor draws in the outside air and compresses it. The combustor combusts by mixing fuel with compressed air in the compressor. The turbine is equipped with turbine blades therein, and the turbine blades rotate by combustion gas discharged from the combustor. The turbine includes a sealing part, a shroud, and a labyrinth seal. The sealing portion is disposed on the inner circumferential surface of the fixture, includes a plurality of hollows, and extends in the circumferential direction. The shroud surrounds the tip of the turbine blade whose one surface is coupled to the outer peripheral surface of the rotating body. The shroud includes a labyrinth seal including a facing surface protruding toward the sealing portion and facing the sealing portion. The labyrinth seal is made to cover at least one surface of the sealing portion included in the virtual surface where the opposite surface intersects the axial direction of the rotating body along the circumferential direction.

In the turbine device for power generation according to an embodiment of the present invention, the labyrinth seal is the axis of the rotating body among the width L of the facing surface and the distance between any two surfaces facing each other among a plurality of surfaces forming the hollow of the sealing unit. L/W, which is the ratio of the hollow width W, which is the longest distance in the direction, may be 1 to 3.

In the turbine device for power generation according to an embodiment of the present invention, the shroud may include two or more labyrinth seals spaced apart from each other along the axial direction.

In the turbine device for power generation according to an embodiment of the present invention, in the axial separation section between the centers of the first labyrinth seal and the second labyrinth seal axially spaced apart from the first labyrinth seal, crossing the axial direction And 2 to 7 surfaces of the sealing part included in the virtual surfaces spaced apart from each other in the axial direction may be disposed.

The present invention can reduce the leakage flow of air generated from the turbine by securing an appropriate gap between the sealing portion and the shroud, and thus, it is possible to improve the overall efficiency of the turbine device for power generation.

1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention.
2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.
3 is an exploded perspective view showing the turbine rotor disk of FIG. 2.
4A is a schematic cross-sectional view of a sealing module of a turbine according to an embodiment of the present invention.
4B is a partially cut-away perspective view schematically showing a part of a turbine according to an embodiment of the present invention.
5 is a view schematically showing various experimental examples of the sealing module of the turbine in order to explain the change of the sealing performance of the sealing module of the turbine.
6 is an enlarged conceptual diagram of the turbine sealing module of FIG. 4A.
7 is a graph for explaining a change in sealing performance according to a ratio of a width of a groove of a labyrinth seal and a width of an opposite surface in a sealing module of a turbine.
8 is a diagram schematically showing a sealing module of a turbine according to another embodiment of the present invention.
9 is a diagram schematically showing a sealing module of a turbine according to another embodiment of the present invention.
10 is a plan view showing a sealing unit according to other embodiments of the present invention.

The present invention is intended to illustrate specific embodiments and to be described in detail in the detailed description, since various transformations may be applied and various embodiments may be provided. However, this is not intended to limit the present invention to a specific embodiment, it should be understood to include all conversions, equivalents, and substitutes included in the spirit and scope of the present invention.

The terms used in the present invention are used only to describe specific embodiments, and are not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In the present invention, terms such as'include' or'have' are intended to designate the presence of features, numbers, steps, actions, components, parts, or a combination thereof described in the specification, but one or more other features. It is to be understood that the presence or addition of elements or numbers, steps, actions, components, parts, or combinations thereof does not preclude in advance.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this case, it should be noted that in the accompanying drawings, the same components are indicated by the same reference numerals as possible. In addition, detailed descriptions of known functions and configurations that may obscure the subject matter of the present invention will be omitted. For the same reason, some elements in the accompanying drawings are exaggerated, omitted, or schematically illustrated.

1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention, FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention, and FIG. 3 is a turbine rotor disk of FIG. It is an exploded perspective view showing.

As shown in FIG. 1, a gas turbine 1000 according to an embodiment of the present invention includes a compressor 1100, a combustor 1200, and a turbine 1300. The compressor 1100 includes a plurality of compressor blades 1110 installed radially. The compressor 1100 rotates the compressor blade 1110 and moves while air is compressed by the rotation of the compressor blade 1110. The size and installation angle of the compressor blade 1110 may vary depending on the installation location. In one embodiment, the compressor 1100 is directly or indirectly connected to the turbine 1300, and receives some of the power generated from the turbine 1300 and may be used to rotate the compressor blade 1110.

Air compressed by the compressor 1100 moves to the combustor 1200. The combustor 1200 includes a plurality of combustion chambers 1210 and a fuel nozzle module 1220 arranged in an annular shape.

As shown in FIG. 2, the gas turbine 1000 according to an embodiment of the present invention includes a housing 1010, and a diffuser 1400 through which combustion gas passing through the turbine is discharged at a rear side of the housing 1010. ) Is provided. In addition, a combustor 1200 that receives compressed air and combusts it is disposed in front of the diffuser 1400.

Hereinafter, directions used in the detailed description of the present invention are defined. Referring to FIG. 2, the axial direction Da is a direction parallel to the tie rod 1600. The radial direction Dr is a direction perpendicular to the axial direction Da. In addition, the circumferential direction Dc is a direction in which the compressor blade 1110 and/or the turbine blade 1340 rotate around the axial direction Da. The circumferential direction Dc can be viewed as a direction along the inner circumferential surface of the housing 1010 along the direction in which the blade rotates.

Referring to the air flow direction, the compressor section 1100 is located on the upstream side of the housing 1010 and the turbine section 1300 is located on the downstream side. In addition, a torque tube unit 1500 is disposed between the compressor section 1100 and the turbine section 1300 as a torque transmission member that transmits the rotational torque generated in the turbine section 1300 to the compressor section 1100.

The compressor section 1100 is provided with a plurality of (for example, 14) compressor rotor disks 1120, and each of the compressor rotor disks 1120 is fastened so as not to be spaced apart in the axial direction by a tie rod 1600. .

Specifically, each of the compressor rotor disks 1120 is aligned along an axial direction with a tie rod 1600 constituting a rotating shaft substantially passing through the center. Here, each of the adjacent compressor rotor disks 1120 is disposed so that the opposite surface is pressed by the tie rod 1600 so that relative rotation is impossible.

A plurality of compressor blades 1110 are radially coupled to the outer circumferential surface of the compressor rotor disk 1120. Each compressor blade 1110 has a dovetail portion 1112 and is fastened to the compressor rotor disk 1120.

A vane (not shown) is positioned between the rotor disks 1120 and fixed to the housing. Unlike the rotor disk, the vane is fixed so as not to rotate, and serves to guide air to the blades of the rotor disk located downstream by aligning the flow of compressed air that has passed through the blades of the compressor rotor disk.

A fastening method of the dovetail portion 1112 includes a tangential type and an axial type. This may be selected according to the required structure of a commercial gas turbine, and may have a commonly known dovetail or fir-tree. In some cases, it is possible to fasten the blade to the rotor disk using a fastener other than the shape, for example, a key or a fastener such as a bolt.

The tie rod 1600 is disposed to pass through the centers of the plurality of compressor rotor disks 1120 and the turbine rotor disks 1320, and the tie rod 1600 may be composed of one or a plurality of tie rods. One end of the tie rod 1600 is fastened in the compressor rotor disk located on the uppermost side, and the other end of the tie rod 1600 is fastened by a fixing nut 1450.

Since the shape of the tie rod 1600 may be formed in various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 2. That is, as shown, one tie rod may have a form penetrating the central portion of the rotor disk, or may have a form in which a plurality of tie rods are arranged in a circumferential shape, or a mixture of these may be used.

Although not shown, in the compressor of the gas turbine, a vane serving as a guide blade may be installed at the next position of the diffuser in order 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. And this is called a deswirler.

In the combustor 1200, the introduced compressed air is mixed with fuel and combusted to produce a high-energy high-temperature and high-pressure combustion gas, and the combustion gas temperature is increased to a heat resistance limit that the combustor and turbine parts can withstand through an isostatic combustion process.

A number of combustors constituting the combustion system of a gas turbine can be arranged in a housing formed in a cell shape, and a burner including a fuel injection nozzle, etc., a combustor liner forming a combustion chamber, and a combustor And a transition piece that becomes a connection part of the turbine and the turbine.

Specifically, the liner provides a combustion space in which fuel injected by a fuel nozzle is mixed with compressed air of a compressor to be burned. The liner may include a flame barrel providing a combustion space in which fuel mixed with air is combusted, and a flow sleeve surrounding the flame barrel and forming an annular space. In addition, the fuel nozzle is coupled to the front end of the liner, and the spark plug is coupled to the side wall.

On the other hand, 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. Such a transition piece is cooled by compressed air supplied from a compressor in an outer wall portion so as to prevent breakage of the combustion gas due to high temperature.

To this end, holes for cooling are provided in the transition piece to inject air into the interior, and compressed air flows toward the liner after cooling the body inside through the holes.

Cooling air cooled by cooling the above-described transition piece flows in the annular space of the liner, and compressed air from the outside of the flow sleeve is provided as cooling air through cooling holes provided in the flow sleeve to collide with the outer wall of the liner.

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor is supplied to the turbine 1300 described above. As the supplied high-temperature and high-pressure combustion gas expands, it collides with the rotor blades of the turbine, giving reaction force to cause rotational torque, and the resulting rotational torque is transmitted to the compressor through the torque tube described above, and exceeds the power required to drive the compressor. The power to be used is used to drive a generator or the like.

The turbine 1300 is basically similar to the structure of a compressor. That is, the turbine 1300 is also provided with a plurality of turbine rotor disks 1320 similar to the compressor rotor disks of the compressor. Accordingly, the turbine rotor disk 1320 also includes a plurality of turbine blades 1340 arranged radially. The turbine blade 1340 may also be coupled to the turbine rotor disk 1320 in a manner such as a dovetail. In addition, a turbine vane (not shown) fixed to the housing is also provided between the turbine blades 1340 of the turbine rotor disk 1320 to guide the flow direction of the combustion gas passing through the blades.

Referring to FIG. 3, the turbine rotor disk 1320 has a substantially disk shape, and a plurality of coupling slots 1322 are formed at the outer circumference thereof. The coupling slot 1322 is formed to have a curved surface in the form of a fir-tree.

The turbine blade 1340 is fastened to the coupling slot 1322. In FIG. 3, the turbine blade 1340 has a flat plate-shaped platform portion 1341 at an approximately central portion. The platform portion 1341 serves to maintain a gap between the blades by contacting the platform portion 1341 of the adjacent turbine blade and its side surfaces.

A root portion 1342 is formed on the bottom of the platform portion 1341. The root portion 1342 has an axial-type shape that is inserted into the coupling slot 1322 of the rotor disk 1320 described above along the axial direction of the rotor disk 1320.

The root portion 1342 has an approximately fir-shaped bent portion, which is formed to correspond to the shape of the bent portion formed in the coupling slot. Here, the coupling structure of the root portion does not necessarily have a fir shape, and may be formed to have a dovetail shape.

A blade portion 1343 is formed on the upper surface of the platform portion 1341. The blade portion 1343 is formed to have an airfoil optimized according to the specifications of the gas turbine, and has a leading edge disposed on the upstream side and a trailing edge disposed on the downstream side based on the flow direction of the combustion gas.

Here, unlike the blades of the compressor, the blades of the turbine are in direct contact with the combustion gas of high temperature and high pressure. Since the temperature of the combustion gas is high enough to reach 1700°C, a cooling means is required. To this end, it has a cooling flow path for extracting compressed air from a part of the compressor and supplying it to the turbine-side blades.

The cooling flow path may extend outside the housing (external flow path) or extend through the inside of the rotor disk (internal flow path), and both external and internal flow paths may be used. In FIG. 3, a plurality of film cooling holes 1344 are formed on the surface of the blade part, and the film cooling holes 1344 communicate with a cooling flow path (not shown) formed inside the blade part 1343 to transfer cooling air to the blade. It serves to supply to the surface of the portion (1343).

Meanwhile, the blade portion 1343 of the turbine is rotated by combustion gas inside the housing, and a gap exists between the end of the blade portion 1343 and the inner surface of the housing so that the blade portion can rotate smoothly. However, as described above, since the combustion gas may leak through the gap, a sealing module is required to block this.

The turbine vane and the turbine blade are both in the form of airfoils and are composed of a leading edge, a trailing edge, a suction surface, and a pressure surface. The interior of the turbine vanes and turbine blades contains a complex maze structure forming a cooling system. The cooling circuit in the vanes and blades receives cooling fluid, for example air, from the compressor of the turbine engine, and the fluid passes through the ends of the vanes and blades adapted to be coupled to the vanes and blade carriers. The cooling circuit typically includes a number of flow paths designed to keep all sides of the turbine vanes and blades at a relatively uniform temperature, and at least some of the fluid passing through these cooling circuits is the leading edge, trailing edge, and suction of the vane. It is discharged through the openings of the surface and the pressure surface.

A plurality of cooling channels constituting a cooling circuit are provided inside the vanes and blades, and a metering plate is provided at an inlet side of the plurality of cooling channels. One cooling hole corresponding to the inlet of each cooling channel is formed in the metering plate.

On the other hand, the blade part 1343 of the turbine is rotated by the combustion gas inside the housing, and a gap exists between the end of the blade part 1343 and the inner surface of the housing so that the blade part 1343 can rotate smoothly. It is done. However, as described above, since the combustion gas may leak through the gap, a sealing module (means) is required to block this.

4A is a cross-sectional view schematically showing a sealing module of a turbine according to an embodiment of the present invention, and FIG. 4B is a partially cut-away perspective view schematically showing a part of the turbine according to an embodiment of the present invention. 4A and 4B, the sealing module of the turbine of the present invention includes a sealing part 100, a shroud 200, and a labyrinth seal 210 protruding from one side of the shroud 200.

The turbine 1300 shown in FIGS. 4A and 4B includes a turbine blade 1340 that rotates at a high speed with respect to the rotation axis A via a flow due to the combustion gas, and leakage of the flow is caused by the turbine blade 1340. It is made in the gap between the free end and the housing 1010. That is, the flow of the combustion gas discharged after combustion is largely divided into a main flow discharged through the turbine blade 1340 (C) and a leakage flow toward the gap between the turbine blade 1340 and the housing 1010 (D). Can be.

Since the leakage flow (D) of the combustion gas acts as a large factor in determining the efficiency of the engine, the shroud 200 located at the free end of the turbine blade 1340 protrudes from the outer surface toward the inner circumferential surface of the housing 1010. The labyrinth seal 210 is integrally formed. The labyrinth seal 210 protrudes toward the sealing portion 100 and includes a facing surface facing the sealing portion 100.

The shroud 200 includes a labyrinth seal 210 protruding toward the sealing part 100 with one surface surrounding the tip of the turbine blade 1340 coupled to the outer circumferential surface of the rotating body. . Two or more labyrinth seals 210 may be disposed to be spaced apart from each other along the axial direction Da of the shroud 200 and may be provided with two or more. The labyrinth seal 210 maintains an appropriate gap between the sealing part 100.

Meanwhile, a groove having a thickness smaller than the thickness of the labyrinth seal 210 may be formed in the shroud 200 between any one labyrinth seal 210 and the labyrinth seal 210 adjacent thereto. The groove may provide a space in which the leakage flow D that has passed between the labyrinth seal 210 and the sealing unit 100 stays and causes a recirculation flow.

A sealing part 100 for setting an appropriate gap between the labyrinth seal 210 and the labyrinth seal 210 is installed on the inner circumferential surface of the housing 1010. The labyrinth seal 210 protrudes from the outer surface of the shroud 200 in a direction closer to the sealing part 100 to secure an appropriate gap between the sealing part 100 and the sealing part 100.

One side of the shroud 200 wraps the end of the blade to protect the end of the blade, and at the same time, the other side of the shroud 200 is provided with a labyrinth seal 210, thereby narrowing the gap with the sealing part 100 to leak. The flow (D) can be effectively reduced.

By the way, the gap secured as a space between the labyrinth seal 210 and the sealing part 100 in the turbine 1300 is the shroud 200 including the turbine blade 1340 rotating at high speed and the housing corresponding to the fixing member. In addition to the pure function of preventing damage to parts by preventing direct contact between the sealing parts 100 of (1010), when a gap greater than an appropriate level is set, excessive combustion gas leakage is caused, which adversely affects the overall efficiency of the engine. At the same time, ensuring an appropriate level of clearance is a very important factor in the design of a gas turbine.

For example, if the gap is set too narrow, it may contribute to increasing the efficiency of the engine by reducing leakage loss in the initial operation of the gas turbine, but as the operating time of the engine increases, rubbing due to thermal deformation between the rotor and the stator It increases the risk of occurrence and in extreme cases causes problems that result in damage to the parts due to contact.

As an example, in the squealer-type turbine blade 1340 without the labyrinth seal 210, the leakage flow D is accompanied through the gap formed between the housing 1010 to improve the efficiency of the engine. On the other hand, in the case of the turbine blade 1340 equipped with the labyrinth seal 210, the leakage flow D generated in the gap with the housing 1010 can be reduced, but the problem of structural stability and Together, there is a limit in terms of considering the life of the parts.

In addition, a sealing module for blocking leakage between the vane (stator) fixed to the housing and the rotating shaft is required, and a sealing module such as a brush seal in addition to the above-described lever seal may be used.

The relationship between the width of the honeycomb seal and the width of the labyrinth seal 210 as well as the gap between the honeycomb seal and the labyrinth seal 210 acts as an important factor that can effectively reduce the leakage flow (D). .

5 is a view schematically showing various experimental examples of the sealing module of the turbine in order to explain the change of the sealing performance of the sealing module of the turbine.

FIG. 5A is an example of a base of a sealing module of a turbine, which is an object of comparison among various experimental examples. 5B shows an example in which the width L of the labyrinth seal is twice that of the base, and the pitch P, which is the interval between labyrinth seals, is 7 times the hollow width W of the honeycomb seal. FIG. 5C shows an example in which the width L of the labyrinth seal is 4 times that of the base, and the pitch P, which is the gap between labyrinth seals, is 7 times the hollow width W of the honeycomb seal. 5D is an example in which the width L of the labyrinth seal covers the entire honeycomb seal. 5E shows an example in which the diameter (D) of the groove is the same as the hollow width (W), and the pitch (P) is 3.5 times the hollow width (W). FIG. 5(f) shows an example in which the groove has the same diameter D as that of FIG. 5(e), but the depth of the groove is twice and the pitch P is 3.5 times the hollow width W. 5G shows an example in which the diameter D of the groove is half of the hollow width W, and the pitch P is 2.5 times the hollow width W.

First, in Figure 5(b), the leakage amount is reduced by 14.5% compared to Figure 5(a) (hereinafter, the base). And, Figure 5(c) shows that the amount of leakage is reduced by 18.4% compared to the base. That is, it can be seen that when the width L of the labyrinth seal is wider, the sealing performance is improved.

However, when the width (L) of the labyrinth seal is excessively wide compared to the hollow width (W) as shown in (d) of FIG. 5, the contact area with the honeycomb seal is excessively widened, and thus the actual operation of the turbine is Problems can arise.

FIG. 5E is an example in which a groove having a diameter D of the same length as the hollow width W is formed between the labyrinth seals. In the example of (e) of FIG. 5, a decrease in leakage of about 30.6% occurs compared to the base. However, in the case of (f) of FIG. 5, where the conditions of FIG. 5(e) and other conditions are the same, but the depth of the groove is twice the diameter (D) of the groove, the leakage amount decreases by about 30% compared to the base. That is, when the depth of the groove becomes deeper than the diameter (D) of the groove, it can be seen that the decrease in leakage flow is insignificant.

5G shows an example in which the diameter D of the groove is half of the hollow width W. This example showed a reduction in leakage of about 28.5% compared to the base. This is a numerical value that decreases the leakage flow lower than that of FIG. 5(e), and it can be seen that the effect of reducing the leakage flow increases when the groove diameter (D) has an appropriate diameter compared to the hollow width (W). have.

We will examine this through more specific examples below.

6 is an enlarged conceptual diagram of the turbine sealing module of FIG. 4A. In this case, part E of FIG. 6 is a planar representation of the sealing part, and is not a part that is actually disposed, but is an additional part shown to aid understanding of the invention. The sealing part 100 shown in the center part of the figure of FIG. 6 is a cross-sectional view showing a state cut from E to B line at the top of the figure.

Referring to FIG. 6, the shroud 200 and the sealing unit 100 are disposed to face each other, and the sealing unit 100 is disposed to face the shroud 200. The sealing part 100 is a honeycomb seal and may be formed in a regular hexagonal cross section. However, the present invention is not limited thereto, and the hollow 112 of the sealing part 100 may have various shapes.

The sealing part 100 includes a plurality of surfaces 110 forming a hollow 112 by forming a certain space. At this time, the longest distance in the axial direction (Da) among the distances formed by any two surfaces facing each other among the plurality of surfaces is referred to as the hollow width (W). The hollow width W may vary according to the shape of the hollow 112 formed by the plurality of surfaces of the sealing part 100. The length of the hollow width W may be approximately 1mm to 2mm, but is not limited thereto and may exist in various lengths.

6, the distance formed by the first surface 1101 of the sealing part 100 and the second surface 1102 facing each other in the axial direction Da is the axial direction Da ) Is the maximum separation distance, and this becomes the hollow width (W). Depending on the relationship between the hollow width W and the width L of the opposite surface 204 of the labyrinth seal 210, the sealing performance of the sealing module of the turbine may increase, which will be described in detail later.

The shroud 200 has one surface 201 surrounding the upper end of the blade, and the other surface facing the sealing part 100. Specifically, the other surface of the shroud 200 has the thinnest bottom surface 205 of the shroud 200, the thickness of the shroud 200 is the thickest, and the labyrinth seal 210 protrudes to close the sealing part 100. It includes an opposing opposing surface 204 and a protruding surface 203 connecting the bottom surface 205 and the opposing surface 204.

The bottom surface 205 of the shroud 200 and the lower portion of the protruding surface 203 may be connected to a curved surface. When the bottom surface 205 and the lower portion of the protruding surface 203 meet at an angle, the combustion gas introduced into the groove 220 rotates inside the groove 220 and may hinder making a recirculation flow. Accordingly, since the bottom surface 205 and the lower portion of the protruding surface 203 are connected to each other in a curved surface, the recirculation flow of the leakage flow can be actively generated in the groove 220.

In addition, when the opposite surface 204 of the shroud 200 and the upper part of the protruding surface 203 are formed of curved surfaces, the opposite surface 204 and the protruding surface 203 can easily pass through the leakage flow along the curved surface. The upper part of the can meet to form a predetermined angle. That is, cross-sections of portions where the facing surface 204 and the protruding surface 203 meet may form vertices with each other. Through this, leakage flow passing between the labyrinth seal 210 and the sealing part 100 may be reduced. However, in order to control the flow of the combustion gas and the leakage flow in consideration of the shape of the sealing part 100 and the arrangement with the labyrinth seal 210, the upper part of the opposing surface 204 and the protruding surface 203 is curved. May lead to.

In the labyrinth seal 210, the width L of the opposite surface 204 in the axial direction Da is equal to or longer than the length of the hollow width W of the sealing part 100. Referring to FIG. 6, the width L of the opposite surface 204 of the labyrinth seal 210 is longer than the hollow width W of the sealing part 100. Since the width L of the opposite surface 204 of the labyrinth seal 210 is equal to or longer than the length of the hollow width W, the sealing part ( The hollow 112 of 100) may exhibit an effect of being sealed, and accordingly, the sealing performance of the sealing module of the turbine against the combustion gas may be improved.

The width L of the opposite surface 204 of the labyrinth seal 210 may be formed such that the ratio of the hollow width W and L/W is 1 to 3. That is, the width (L) of the opposite surface (204) is the same as the hollow width (W), or is preferably formed to be three times the length of the hollow width (W). More preferably, the sealing performance may be the most excellent within the range of L/W of 1.3 to 2.2.

If the width L of the opposite surface 204 is smaller than the length of the hollow width W, the opposite surface 204 of the labyrinth seal 210 does not cover the hollow width W, so that the combustion gas Since it may pass between the rinse seal 210 and the surface 110 of the sealing part 100, leakage flow may increase. In addition, when the width L of the opposing surface 204 is formed to be longer than three times the length of the hollow width W, as the contact area between the opposing surface 204 and the sealing unit 100 increases, the turbine There is a concern that contact may occur during operation, which may adversely affect the life of the parts as well as structural stability problems.

Pitch (P) and hollow width (W), which are the distances between the centers in the axial direction (Da) between any one labyrinth seal 210 spaced apart from each other along the axial direction (Da) and the adjacent labyrinth seal 210 The ratio of and P/W may be 2.5 to 7. That is, it is preferable that the pitch P is 2.5 times or more and 7 times or less of the hollow width W.

6, the pitch P, which is the distance between the centers in the axial direction Da between the first labyrinth seal 2101 and the second labyrinth seal 2102, is 6 times and 7 times the hollow width W. It's between the ships. If the length of the pitch P is narrower than 2.5 times the length of the hollow width W, the area where the labyrinth seal 210 and the sealing unit 100 contact becomes wider, and thus a problem in operation may occur. In addition, when the length of the pitch P is longer than 7 times the length of the hollow width W, the length of the groove 220 becomes too long, so that leakage flow due to a decrease in sealing performance may increase.

In addition, D/W, which is the ratio of the width D of the groove 220 and the hollow width W, is preferably 0.5 to 5.6. That is, it is preferable that the width D of the groove 220 is at least half the length of the hollow width W, and less than 5.6 times the length of the hollow width W. When the width D of the groove 220 is less than half of the length of the hollow width W, a contact area between the labyrinth seal 210 and the sealing unit 100 may be widened, resulting in a problem in operation. In addition, when the width D of the groove 220 is greater than 5.6 times the length of the hollow width W, the length of the groove 220 becomes too long, and thus leakage flow is likely to occur.

The height difference Tb between the opposite surface 204 of the labyrinth seal 210 and the bottom surface 205 of the groove 220 is 2/5 or more and 4/5 or less of the width L of the opposite surface 204 desirable. Specifically, the opposite surface 204 constituting the difference between the thickness Tg of the groove 220 of the shroud 200 and the thickness Tt of the labyrinth seal 210 and the bottom surface 205 of the groove 220 The height difference Tb of is 2/5 or more of the width L of the opposite surface 204, and is preferably 4/5 or less. If the height difference (Tb) between the opposite surface 204 and the bottom surface 205 is less than 2L/5, the space of the groove 220 is narrow, so that the combustion gas flowing into the groove 220 causes sufficient recirculation flow. This can be scarce. And, if the height difference (Tb) between the opposite surface 204 and the bottom surface 205 is 4L/5 or more, the combustion gas introduced into the groove 220 tends to stay inside the groove 220 rather than cause a flow. As it becomes relatively large, the recirculation flow rate may drop.

The labyrinth seal 210 may be formed to cover at least one surface of the sealing portion 100 included in a virtual surface in which the opposite surface 204 is perpendicular to the axial direction Da, along the circumferential direction. That is, at least one virtual surface perpendicular to the axial direction Da including the surface of the sealing part 100 passes through the opposite surface 204 of the labyrinth seal 210.

Some of the plurality of surfaces of the sealing unit 100 are included in the virtual surface Pr perpendicular to the axial direction Da. Specifically, referring to FIG. 6, the second surface 1102 of the sealing unit 100 is included in the first virtual surface Pr1 perpendicular to the axial direction Da. In addition, the facing surface 204 of the first labyrinth seal 2101 covers the second surface 1102 of the sealing unit 100 included in the first virtual surface Pr1 perpendicular to the axial direction Da. .

Since the sealing part 100 extends along the circumferential direction Dc, the second surface 1102 may be repeated along the circumferential direction Dc, and the first labyrinth seal 2101 of the sealing part 100 is also circumferential. Since it extends along the direction Dc, the opposite surface 204 of the first labyrinth seal 210 has the second surface 1102 of the sealing part 100 included in the first virtual surface Pr1 in the circumferential direction ( Cover along Dc).

In addition, the opposite surface 204 of the labyrinth seal 210 covers two or more surfaces of the sealing portion 100 included in two or more virtual surfaces spaced apart in the axial direction (Da) along the circumferential direction (Dc). It can be done. 6, of the plurality of surfaces of the sealing unit 100, a first surface 1101 is included in a second virtual surface Pr2, and a second surface 1102 is included in a first virtual surface Pr1. do. In addition, the facing surface 204 of the first labyrinth seal 2101 covers (includes) the first virtual surface Pr1 and the second virtual surface Pr2.

On the other hand, in the axially spaced section between the center of one labyrinth seal 210 and the center of the labyrinth seal 210 adjacent thereto, virtual Two to seven faces of the sealing part 100 included in the face may be disposed. Specifically, referring to FIG. 6, the center of the first labyrinth seal 2101 and the center of the second labyrinth seal 2102 are separated from each other in the axial direction (Da) within the separation distance (P) in the axial direction (Da). Seven surfaces of the sealing unit 100 included in the plurality of spaced apart virtual surfaces Pr2 to Pr8 are included.

As described above, the opposite surface 204 of the labyrinth seal 210 covers at least one surface of the sealing part 100 included in a virtual surface perpendicular to the axial direction, or the center of the adjacent labyrinth seal 210 By arranging 2 to 7 surfaces of the sealing unit 100 included in the virtual surfaces that are intersected with the axial direction (Da) and spaced apart from each other in the axial direction (Da), the sealing module of the turbine is It can exhibit an appropriate sealing effect between the (100) and the shroud (200). In addition, since the above-described sealing module of the turbine can prevent excessive contact between the sealing unit 100 and the shroud 200, it is possible to reduce the occurrence of problems in operation.

7 is a graph for explaining a change in sealing performance according to a ratio of a width of a groove of a labyrinth seal and a width of an opposite surface in a sealing module of a turbine. FIG. 7 shows the reduction rate of the leakage amount compared to the base according to the change of D/L when compared to the base shown in FIG. 5A (improving the sealing performance).

Referring to FIG. 7, it is preferable that the D/L value, which is the ratio of the width D of the groove of the labyrinth seal and the width L of the opposite surface, ranges from 1.5 to 3.5.

Specifically, as the width (D) of the groove narrows, the sealing performance decreases, and as the width (D) of the groove increases, the sealing performance increases. However, the optimum sealing performance was shown at D/L of 3.5, and the sealing performance of the sealing module of the turbine decreased again in the section where D/L exceeded 3.5. When referring to these results, it can be seen that the sealing performance is most improved when the D/L is 1.5 to 3.5.

8 is a diagram schematically showing a sealing module of a turbine according to another embodiment of the present invention. In this case, E of FIG. 8 is a planar representation of the sealing part 100 ′, and is not a part that is actually disposed, but is an additional part shown to aid understanding of the invention. The sealing part 100' shown in the center part of the figure of FIG. 8 is a cross-sectional view showing a state cut from E to B line at the top of the figure.

Referring to FIG. 8, in the sealing part 100 ′, the vertices of a regular hexagon forming the hollow 112 ′ are arranged in a line along the B line in the axial direction Da. At this time, the hollow width W of the sealing part 100 ′ is a distance from the first vertex 1141 ′ to the second vertex 1142 ′, and is the maximum separation distance in the axial direction Da of the hollow part.

In order to improve the sealing performance of the turbine through the effect of temporarily sealing the hollow 112 ′ of the sealing part 100 ′ by the opposite surface 204 ′ of the labyrinth seal 210 ′, the shroud 200 ′ The width L of the first labyrinth seal 2101 ′ is formed longer than the hollow width W of the sealing part 100 ′. However, unlike shown in the drawing, the labyrinth seal 210 ′ of the shroud 200 ′ is provided with 3 or more, and may be spaced apart along the axial direction Da.

In addition, unlike shown in the drawing, the sealing portion 100 ′ may be formed to have different hollow widths W in the axial direction Da, and accordingly, the width L of the labyrinth seal 210 ′ ) May also have different widths L corresponding thereto. Specifically, the sealing portion 100 ′ may be formed to have a longer hollow width (W) or a shorter hollow width (W) along the flow direction of the combustion gas, and the labyrinth seal 210 ′ Corresponding to this, it may have a longer width L or a shorter width L.

The sealing module of the turbine according to the embodiment of the present invention is the opposite surface of the labyrinth seal 210 ′ meeting the conditions as described in the above-described embodiment according to the hollow width W of the sealing part 100 ′ ( It may be formed to have a distance between the width L of 204 ′ and the labyrinth seal 210 ′, and accordingly, the sealing performance of the sealing module of the turbine may be improved.

9 is a diagram schematically showing a sealing module of a turbine according to another embodiment of the present invention. In this case, E of FIG. 9 is a planar representation of the sealing portion 100 ″, and is not a part that is actually disposed, but is an additional part shown to aid understanding of the invention. The sealing part 100 ″ shown in the central part of the drawing of FIG. 9 is a cross-sectional view showing a state cut from E to B line at the top of the drawing.

Referring to FIG. 9, the shroud 200 ″ is provided with four labyrinth seals 2101 ″, 2012 ″, 2013 ″, and 2014 ″ spaced apart from each other along the axial direction Da. A groove 220'' having a predetermined diameter D is formed between the first labyrinth seal 2101" and the second labyrinth seal 2102". At this time, the diameter (D) of the groove is preferably 2.5 times or more and 3.5 times or less of the hollow width (W).

In addition, as described in the above-described embodiment, the groove 220 ′ to satisfy the relationship between the pitch and the hollow width (W), which is the distance between the labyrinth seals 210, and the width L of the labyrinth seal 210. The diameter (D) of') may be determined.

The sealing module of the turbine according to an embodiment of the present invention has a groove having a narrower width and a depth between the labyrinth seals 210 than in the above-described embodiments, so that the labyrinth seal 210 and the sealing part 100 It is possible to increase the sealing area therebetween, and accordingly, the sealing performance of the sealing module of the turbine can be improved.

FIG. 10 is a plan view showing a sealing part according to other embodiments of the present invention, and FIGS. 10A to 10E are plan views illustrating a sealing part according to different embodiments having a cross section of a hollow part having different shapes. to be.

The sealing portions 100a, 100b, 100c, 100d, and 100e of the sealing module of the turbine may have a plurality of hollow cross-sections of at least one of a triangle, a square, a circle, and a hexagon.

Referring to Figure 10 (a), the sealing portion (100a) includes a plurality of surfaces formed to form a hollow triangle. Specifically, the plurality of surfaces 115 is made so that the hollow is a triangle, and the triangle may be an equilateral triangle. At this time, the hollow width W of the sealing part 100a may be the widest width formed by a triangle along the axial direction Da. When the hollow forms a regular triangle than a honeycomb seal having a regular hexagonal hollow width (W) having the same length, since the hollow has a relatively narrow hollow width (W), it is possible to effectively reduce the leakage flow.

Meanwhile, the sum of the six hollow equilateral triangles of the sealing portion 100a may form a hexagonal shape. Specifically, the surface 110a formed by the outer shape of the six triangles forms a regular hexagon, and the regular hexagonal surface 110a may be formed to protrude longer toward the labyrinth seal than the surface 115 forming the triangle. In this case, a hollow formed by the triangular surface 115 is additionally formed in the hollow formed by the regular hexagonal surface 110a, and the effect of sealing the hollow interior is increased, so that leakage flow of the sealing module of the turbine can be more effectively reduced. .

Referring to FIG. 10B, a plurality of surfaces of the sealing portion 100b may be formed to form a rectangular hollow. In this example, the hollow width W is a separation distance in the axial direction Da formed by the adjacent two surfaces 1101b and 1102b. In this case, the square may be formed in a rectangular shape, unlike the illustrated one.

Referring to FIG. 10C, a plurality of surfaces of the sealing portion 100c may be formed to form a circular hollow. In this example, the hollow width (W) is the distance in the axial direction (Da) of the circular hollow, that is, the length of the diameter.

Referring to FIG. 10D, a plurality of surfaces of the sealing portion 100d may be formed to form a hexagonal hollow formed elongated in the axial direction Da. In this example, the hollow width W is the maximum separation distance in the axial direction Da formed by the first vertex 1141d and the second vertex 1142d.

Referring to FIG. 10E, a plurality of surfaces of the sealing portion 100e may be formed to form a hexagonal hollow that is elongated along the circumferential direction Dc. In this example, the hollow width W is the maximum separation distance in the axial direction Da formed by the first surface 1101e and the second surface 1102e of the hexagonal hollow.

Comparing FIG. 10(d) and FIG. 10(e), even though they have the same size of the hollow, the hollow width W may be different according to the arrangement of the hollows, and accordingly, the opposite of the labyrinth seal The width of the surface may also vary according to the hollow width (W).

On the other hand, as shown in the above-described embodiment, the hollow of the sealing portion 100 is not composed of the sealing portion 100 having one shape according to the above-described different embodiments, but two of the above-described embodiments. The above shape can be made complex.

In addition, according to the relationship between the length in the axial direction (Da) of the labyrinth seal 210 and the hollow width (W) of the sealing part 100, the sealing ability to reduce the leakage flow (D) will be further improved. I can.

As described above, one embodiment of the present invention has been described, but those of ordinary skill in the relevant technical field add, change, delete or add components within the scope not departing from the spirit of the present invention described in the claims. It will be possible to variously modify and change the present invention by means of the like, and it will be said that this is also included within the scope of the present invention.

1000: gas turbine 1010: housing
1100: compressor 1110: compressor blade
1112: dovetail part 1120: compressor rotor disk unit
1130: compressor cooling air supply flow path 1200: combustor
1300: turbine 1320: turbine rotor disk
1340: turbine blade 1400: diffuser
1450: fixing nut 1500: torque tube unit
1600: tie rod 100: sealing portion
110: surface of the sealing portion 112: hollow of the sealing portion
200: shroud 201: one side
203: protruding surface 204: facing surface
205: bottom surface 210: labyrinth seal
220: groove Da: axial
Dr: radial direction Dc: circumferential direction
W: Hollow width of the sealing part L: Width of labyrinth seal
Pv1, Pv2: Virtual Surface Tt: Labyrinth Seal Thickness
Tg: groove thickness

Claims (19)

A sealing portion disposed on the inner circumferential surface of the fixture, including a plurality of hollows, and extending in the circumferential direction; And
One side includes; a shroud surrounding the tip of the turbine blade coupled to the outer circumferential surface of the rotating body,
The shroud,
Any two of the plurality of surfaces protruding toward the sealing part and facing each other include a facing surface facing the sealing part, and a width L of the opposite surface in the axial direction of the rotating body forming a hollow of the sealing part It comprises a labyrinth seal that is equal to or longer than the length of the hollow width W, which is the longest distance in the axial direction of the rotating body, and is spaced apart from each other along the axial direction and disposed at least two,
The shroud includes a first labyrinth seal, and a second labyrinth seal spaced apart from each other along the first labyrinth seal and the axial direction,
A groove having a thickness thinner than that of the first labyrinth seal and the second labyrinth seal is formed between the first labyrinth seal and the second labyrinth seal,
D/L, which is a ratio of the width (D) of the groove of the labyrinth seal and the width (L) of the opposite surface, is 1.5 to 3.5,
The sealing module of the turbine, D/W, which is a ratio of the width (D) of the groove and the hollow width (W) is 0.5 to 5.6. The method of claim 1,
The labyrinth seal,
A turbine sealing module configured such that L/W, which is a ratio of the width L of the opposite surface of the labyrinth seal and the hollow width W, is 1 to 3. delete The method of claim 1,
A turbine sealing module in which a P/W that is a ratio of a pitch P, which is a distance between the center of the axial direction of the first labyrinth seal and the second labyrinth seal, and the hollow width W is 2.5 to 7. delete The method of claim 4,
The shroud,
A turbine sealing module in which a height difference (Tb) between the opposite surface of the labyrinth seal and the bottom surface of the groove is 2L/5 or more and 4L/5 or less. The method of claim 1,
The sealing part,
The sealing module of the turbine made so that the cross section of the plurality of hollows is at least one of a triangle, a square, a circle, and a hexagon. The method of claim 1,
The sealing module of the turbine is a honeycomb seal. The method of claim 8,
The sealing module of the turbine in which the hollow cross section of the honeycomb seal is a regular hexagon. The method of claim 1,
The other side of the shroud,
A bottom surface having the thinnest thickness of the shroud;
A facing surface having the largest thickness of the shroud and protruding from the labyrinth seal to face the sealing portion; And
It includes a protruding surface connecting the bottom surface and the opposite surface,
The sealing module of the turbine is connected to the bottom of the bottom surface and the protruding surface in a curved surface. The method of claim 10,
The sealing module of the turbine where the opposite surface and the upper portion of the protruding surface meet at a predetermined angle. A sealing portion disposed on the inner circumferential surface of the fixture, including a plurality of hollows, and extending in the circumferential direction; And
One side includes; a shroud surrounding the tip of the turbine blade coupled to the outer circumferential surface of the rotating body,
The shroud,
At least one surface of the sealing unit including a facing surface protruding toward the sealing unit and facing the sealing unit, and the surface of the sealing unit included in a virtual surface intersecting the axial direction of the rotating body is at least one in the circumferential direction. It is made to cover the abnormality, and comprises a labyrinth seal that is spaced apart from each other along the axial direction and disposed at least two,
The shroud includes a first labyrinth seal, and a second labyrinth seal spaced apart from each other along the first labyrinth seal and the axial direction,
A groove having a thickness thinner than that of the first labyrinth seal and the second labyrinth seal is formed between the first labyrinth seal and the second labyrinth seal,
D/L, which is a ratio of the width (D) of the groove of the labyrinth seal and the width (L) of the opposite surface, is 1.5 to 3.5,
The sealing module of the turbine, D/W, which is a ratio of the width (D) of the groove and the hollow width (W) is 0.5 to 5.6. The method of claim 12,
The facing surface,
A sealing module of a turbine configured to cover two or more surfaces of the sealing portion included in two or more imaginary surfaces intersecting the axial direction and spaced apart in the axial direction along the circumferential direction. delete The method of claim 12,
In a spaced section in the axial direction between the centers of the first labyrinth seal and the second labyrinth seal, two surfaces of the sealing part intersected with the axial direction and included in virtual surfaces spaced apart from each other in the axial direction The sealing module of the turbine is arranged to seven. A compressor that suctions and compresses external air;
A combustor for combusting by mixing fuel with air compressed by the compressor; And
Includes; a turbine blade is mounted therein, the turbine blade rotates by the combustion gas discharged from the combustor,
The turbine,
A sealing portion disposed on the inner circumferential surface of the fixture, including a plurality of hollows, and extending in the circumferential direction; And
One surface includes a shroud surrounding the tip of the turbine blade coupled to the outer peripheral surface of the rotating body; and,
The shroud,
Covers at least one surface of the sealing part that protrudes toward the sealing part and includes a facing surface facing the sealing part, and the surface of the sealing part included in an imaginary surface crossing the axial direction of the rotating body along the circumferential direction. And a labyrinth seal disposed to be spaced apart from each other along the axial direction,
The shroud includes a first labyrinth seal, and a second labyrinth seal spaced apart from each other along the first labyrinth seal and the axial direction,
A groove having a thickness thinner than that of the first labyrinth seal and the second labyrinth seal is formed between the first labyrinth seal and the second labyrinth seal,
D/L, which is a ratio of the width (D) of the groove of the labyrinth seal and the width (L) of the opposite surface, is 1.5 to 3.5,
The ratio of the width (D) and the hollow width (W) of the groove D / W is 0.5 to 5.6 turbine device for power generation. The method of claim 16,
The labyrinth seal,
L, which is the ratio of the width L of the opposing surface and the hollow width W, which is the longest distance in the axial direction of the rotating body among the distances formed by any two surfaces facing each other among a plurality of surfaces forming the hollow of the sealing part Turbine device for power generation made so that /W is 1 to 3. delete The method of claim 17,
In a spaced section in the axial direction between the centers of the first labyrinth seal and the second labyrinth seal, two surfaces of the sealing part intersected with the axial direction and included in virtual surfaces spaced apart from each other in the axial direction Turbine device for power generation is arranged to seven.

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