KR20220145699A - Apparatus for controlling tip clearance of turbine blade and gas turbine compring the same - Google Patents

Abstract

An apparatus for controlling a tip clearance of a turbine blade of the present invention, which is an apparatus for controlling a tip clearance formed between a turbine casing and a turbine blade, comprises: a casing surrounding the turbine blade; a dummy flange mounted in a concave groove formed on the outer circumferential surface of the casing and including a plurality of cooling fins on the outer circumferential surface; mounting ribs formed on the inner circumferential surface of the dummy flange; a carrier segment mounted on the casing to be movable in the radial direction and having an inner space in which cooling air flows; and a ring segment mounted on mounting ribs formed on the inner circumferential surface of the carrier segment, wherein the carrier segment is moved in the radial direction as the mounting ribs formed on the inner circumferential surface of the dummy flange are deformed by the cooling air passing through the dummy flange. According to the apparatus for controlling the tip clearance of the turbine blade and a gas turbine including the same, a cold air supply space for gap adjustment and a cold air supply space for cooling the ring segment can be divided and formed independently within the one carrier segment.

Description

Apparatus for controlling tip clearance of turbine blade and gas turbine compring the same

The present invention relates to a turbine blade tip clearance control device and a gas turbine including the same.

A turbine is a mechanical device that uses the flow of a compressive fluid such as steam or gas to obtain rotational force by impulse or reaction force, 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 to generate high-temperature and high-pressure combustion gas.

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

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

Since these gas turbines do not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction part such as a piston-cylinder, so lubricating oil consumption is extremely low. There are advantages.

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

At this time, a gap defined as a tip clearance is formed between the turbine casing and the blade. If the tip clearance becomes larger than an appropriate level, the amount of flue gas that escapes between the turbine casing and the blades without work increases, reducing the overall efficiency of the gas turbine. Conversely, if the tip clearance becomes smaller than an appropriate level, the blades scratch the inner wall of the turbine casing. Therefore, adjusting the tip clearance of the turbine at an appropriate level is closely related to improving the performance of the gas turbine.

US Patent Publication No. 9115595

The present invention divides a cold air supply space for gap control and a cold air supply space for ring segment cooling inside one carrier segment and forms them independently, and a pair of mounting ribs is formed by collision cooling through a dummy flange and a carrier segment. Tip clearance of the turbine blade that can be cooled by controlling the amount of deformation and moving the carrier segment and the ring segment in the radial direction to adjust the tip clearance, and supplying the cooling air flowing into the first space of the carrier segment to the next stage of the vane carrier An object of the present invention is to provide a control device and a gas turbine including the same.

In order to achieve the above object, there is provided an apparatus for controlling a tip clearance of a turbine blade of a turbine blade of the present invention, comprising: a casing surrounding the turbine blade; a dummy flange mounted on the concave groove formed on the outer circumferential surface of the casing and including a plurality of cooling fins on the outer circumferential surface; a mounting rib formed on the inner circumferential surface of the dummy flange; a carrier segment movably mounted to the casing and having a space in which cooling air flows; and a ring segment mounted on the mounting rib formed on the inner circumferential surface of the carrier segment, wherein the carrier segment is moved in the radial direction by deforming the mounting rib formed on the inner circumferential surface of the dummy flange by cooling air passing through the dummy flange.

The space inside the carrier segment includes a first space in which cooling air supplied from the outside of the casing is introduced through the dummy flange, and the cooling air supplied to the vane carrier is supplied to the vane carrier, and cooling air supplied through the inside of the casing is introduced and the cooling air is introduced It may include a second space for supplying the ring segment.

The dummy flange includes a curved plate part having a pair of support rib parts mounted in the concave grooves of the casing on both sides in the width direction, a plurality of cooling fins formed on the outer peripheral surface of the curved plate part, a plurality of cooling holes formed through the curved plate part, and a curved surface It may include a pair of mounting ribs formed on the inner peripheral surface of the plate and thermally deformed by cooling air supplied from the outside of the casing.

The dummy flange is deformed such that the widthwise central portion of the curved plate portion is deformed radially inwardly and the pair of mounting ribs are widened by the cooling air supplied from the outside of the casing, so that the carrier segment can be moved radially inwardly.

It may further include an impingement plate mounted to be spaced apart a predetermined distance from the outer circumferential surface of the dummy flange.

The impingement plate may include a plurality of cooling holes formed so that cooling air supplied from the outside of the casing is cooled by collision on the outer circumferential surface of the dummy flange.

The plurality of cooling holes of the impingement plate may include a plurality of first cooling holes penetrating toward the curved plate portion of the dummy flange and a plurality of second cooling holes penetrating toward each cooling fin portion of the dummy flange.

The carrier segment includes a body portion having a rectangular cross-section, a pair of side rib portions protruding from the lower portion of the outer surface of the body portion and inserted into the mounting groove of the casing to be mounted, and a concave portion formed on the outer surface of the body portion to form a dummy flange. It may include a pair of mounting grooves mounted on the pair of mounting ribs, and a pair of mounting ribs formed on the inner circumferential surface of the main body to which the ring segment is mounted.

The carrier segment includes a plurality of upper inlet holes that are formed through the upper surface of the main body to introduce cooling air that has passed through the dummy flange into the first space, and a plurality of upper inlet holes that are formed through one side of the main body and direct the cooling air introduced into the first space toward the vane carrier. A plurality of side outlet holes for outflow, a plurality of side inlet holes formed through the other side of the main body to introduce cooling air supplied through the inside of the casing into the second space, It may further include a plurality of lower surface outlet holes for discharging the cooling air toward the ring segment.

The carrier segment may further include an upper rib portion extending outwardly from the upper surface edge portion of the main body portion to form an upper surface groove on the outer peripheral surface of the main body portion.

A gas turbine according to the present invention includes: a compressor for sucking in and compressing external air; a combustor for mixing fuel with compressed air in the compressor and combusting it; The turbine blade is mounted inside the turbine casing, the turbine blade is rotated by the combustion gas discharged from the combustor; and a device for controlling a tip clearance formed between the turbine casing and the turbine blade, the device for controlling the tip clearance comprising: a casing surrounding the turbine blade; a dummy flange mounted on the concave groove formed on the outer circumferential surface of the casing and including a plurality of cooling fins on the outer circumferential surface; a mounting rib formed on the inner circumferential surface of the dummy flange; a carrier segment movably mounted to the casing and having a space in which cooling air flows; and a ring segment mounted on the mounting rib formed on the inner circumferential surface of the carrier segment, wherein the carrier segment is moved in the radial direction by deforming the mounting rib formed on the inner circumferential surface of the dummy flange by cooling air passing through the dummy flange.

The space inside the carrier segment includes a first space in which cooling air supplied from the outside of the casing is introduced through the dummy flange, and the cooling air supplied to the vane carrier is supplied to the vane carrier, and cooling air supplied through the inside of the casing is introduced and the cooling air is introduced It may include a second space for supplying the ring segment.

The dummy flange includes a curved plate part having a pair of support rib parts mounted in the concave grooves of the casing on both sides in the width direction, a plurality of cooling fins formed on the outer peripheral surface of the curved plate part, a plurality of cooling holes formed through the curved plate part, and a curved surface It may include a pair of mounting ribs formed on the inner peripheral surface of the plate and thermally deformed by cooling air supplied from the outside of the casing.

The dummy flange is deformed such that the widthwise central portion of the curved plate portion is deformed radially inwardly and the pair of mounting ribs are widened by the cooling air supplied from the outside of the casing, so that the carrier segment can be moved radially inwardly.

It may further include an impingement plate mounted to be spaced apart a predetermined distance from the outer circumferential surface of the dummy flange.

The impingement plate may include a plurality of cooling holes formed so that cooling air supplied from the outside of the casing is cooled by collision on the outer circumferential surface of the dummy flange.

The plurality of cooling holes of the impingement plate may include a plurality of first cooling holes penetrating toward the curved plate portion of the dummy flange and a plurality of second cooling holes penetrating toward each cooling fin portion of the dummy flange.

The carrier segment includes a body portion having a rectangular cross-section, a pair of side rib portions protruding from the lower portion of the outer surface of the body portion and inserted into the mounting groove of the casing to be mounted, and a concave portion formed on the outer surface of the body portion to form a dummy flange. It may include a pair of mounting grooves mounted on the pair of mounting ribs, and a pair of mounting ribs formed on the inner circumferential surface of the main body to which the ring segment is mounted.

The carrier segment includes a plurality of upper inlet holes that are formed through the upper surface of the main body to introduce cooling air that has passed through the dummy flange into the first space, and a plurality of upper inlet holes that are formed through one side of the main body and direct the cooling air introduced into the first space toward the vane carrier. A plurality of side outlet holes for outflow, a plurality of side inlet holes formed through the other side of the main body to introduce cooling air supplied through the inside of the casing into the second space, It may further include a plurality of lower surface outlet holes for discharging the cooling air toward the ring segment.

The carrier segment may further include an upper rib portion extending outwardly from the upper surface edge portion of the main body portion to form an upper surface groove on the outer peripheral surface of the main body portion.

According to the device for controlling the tip clearance of the turbine blade of the present invention and the gas turbine including the same, the cold air supply space for regulating the gap and the cold air supply space for ring segment cooling are partitioned and formed independently in one carrier segment. can

In addition, the tip clearance can be adjusted by adjusting the deformation amount of the pair of mounting ribs by impingement cooling through the dummy flange and the carrier segment and moving the carrier segment and the ring segment in the radial direction.

In addition, the cooling air flowing into the first space of the carrier segment to adjust the tip clearance may be supplied to the vane carrier of the next stage, and the cooling air flowing into the second space of the carrier segment may be supplied into the ring segment.

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 a partial cross-sectional view illustrating an internal structure of a gas turbine according to an embodiment of the present invention.
4 is a partial cross-sectional view showing a tip clearance control device according to an embodiment of the present invention.
5 is a cross-sectional view showing a dummy flange (a) and a carrier segment (b) according to an embodiment of the present invention.
6 is a partially cut-away perspective view illustrating a tip clearance control device according to an embodiment of the present invention.
7 is a top perspective view showing a dummy flange according to an embodiment of the present invention.
8 is a front perspective view illustrating a dummy flange according to an embodiment of the present invention.
9 is a bottom perspective view showing a dummy flange according to an embodiment of the present invention.
10 is an upper left perspective view illustrating a carrier segment according to an embodiment of the present invention;
11 is a lower right perspective view illustrating a carrier segment according to an embodiment of the present invention;
12 is a partial cross-sectional view showing the flow of cooling air in the tip clearance control device of the present invention.

Since the present invention can apply various transformations and can have various embodiments, specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and should be understood to include all modifications, equivalents, and substitutes included in the spirit and scope of the present invention.

The terms used in the present invention are only used to describe specific embodiments, and are not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly dictates otherwise. In the present invention, terms such as 'comprise' or 'have' are intended to designate that the features, numbers, steps, operations, components, parts, or combinations thereof described in the specification exist, and one or more other features It is to be understood that this does not preclude the possibility of the presence or addition of numbers, steps, operations, components, parts, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. At this time, it should be noted that in the accompanying drawings, the same components are denoted by the same reference numerals as much as possible. In addition, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components are exaggerated, omitted, or schematically illustrated in the accompanying drawings.

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 an embodiment of the present invention It is a partial cross-sectional view showing the internal structure of the gas turbine according to

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 blades 1110 installed radially. The compressor 1100 rotates the blade 1110 and moves while the air is compressed by the rotation of the blade 1110 . The size and installation angle of the blade 1110 may vary depending on the installation location. In one embodiment, the compressor 1100 may be directly or indirectly connected to the turbine 1300 , and may receive a portion of the power generated from the turbine 1300 and use it to rotate the blade 1110 .

Air compressed in 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 the rear side of the housing 1010 . ) is provided. In addition, a combustor 1200 for receiving and burning compressed air in front of the diffuser 1400 is disposed.

Referring to the flow direction of the air, the compressor section 1100 is positioned on the upstream side of the housing 1010 , and the turbine section 1300 is disposed on the downstream side. And, between the compressor section 1100 and the turbine section 1300, the torque tube unit 1500 as a torque transmitting member for transmitting the rotational torque generated in the turbine section 1300 to the compressor section 1100 is disposed.

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 the axial direction with the tie rods 1600 constituting the rotation shaft passing through the center. Here, each of the adjacent compressor rotor disks 1120 is arranged such that the opposite surfaces are compressed by the tie rods 1600 so that relative rotation is impossible.

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

A vane (not shown) fixed to the housing is positioned between each rotor disk 1120 . Unlike the rotor disk, the vane is fixed not to rotate, and serves to align the flow of compressed air passing through the blades of the rotor disk of the compressor and guide the air to the blades of the rotor disk located on the downstream side.

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

The tie rods 1600 are disposed to penetrate the central portions of the plurality of compressor rotor disks 1120 and the turbine rotor disks 1322 , and the tie rods 1600 may include one or a plurality of tie rods. One end of the tie rod 1600 may be fastened in the compressor rotor disk located at the most upstream side, and the other end of the tie rod 1600 may be fastened by a fixing nut 1450 .

Since the shape of the tie rod 1600 may have 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 shape passing through the central portion of the rotor disk, or a plurality of tie rods may have a shape arranged in a circumferential shape, and a mixture thereof may be used.

Although not shown, in the compressor of the gas turbine, a vane serving as a guide vane may be installed at a position next to the diffuser in order to adjust the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the fluid pressure. and this is called a deswirler.

The combustor 1200 mixes and combusts the introduced compressed air with fuel to produce high-energy high-temperature, high-pressure combustion gas, and the combustion gas temperature is raised to the limit of heat resistance that the combustor and turbine parts can withstand through the isostatic combustion process. .

A plurality of combustors constituting the combustion system of the gas turbine may be arranged in a housing formed in the form of a cell, a burner including a fuel injection nozzle, etc., a combustor liner forming a combustion chamber, and a combustor And it is configured to include a transition piece (Transition Piece) that becomes a connection part of the turbine.

Specifically, the liner provides a combustion space in which the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and combusted. Such a liner may include a flame passage that provides a combustion space in which fuel mixed with air is combusted, and a flow sleeve that surrounds the flame barrel and forms 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, a transition piece is connected to the rear end of the liner so that the combustion gas combusted by the spark plug can be sent to the turbine side. The transition piece is cooled by the compressed air supplied from the compressor so as to prevent damage caused by the high temperature of the combustion gas.

To this end, holes for cooling are provided in the transition piece so that air can be injected into the transition piece, and compressed air flows toward the liner after cooling the body inside through the holes.

Cooling air cooled by 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 the outer wall of the liner to collide.

On the other hand, the high-temperature, high-pressure combustion gas from the combustor is supplied to the turbine 1300 described above. The supplied high-temperature and high-pressure combustion gas expands and collides with the rotor blades of the turbine, giving a reaction force to generate rotational torque. The power is used to drive a generator, etc.

The turbine 1300 is basically similar to the structure of the compressor. That is, the turbine 1300 is also provided with a turbine rotor 1320 similar to the rotor of the compressor 1100 . Thus, the turbine rotor 1320 includes a turbine rotor disk 1322 and a plurality of turbine blades 1324 disposed radially therefrom. The turbine blade 1324 may also be coupled to the turbine rotor disk 1322 in a dovetail or the like manner.

In addition, a plurality of turbine vanes 1314 fixed to the turbine casing 1312 are also provided between the turbine blades 1324 of the turbine rotor disk 1322, and the flow direction of the combustion gas passing through the turbine blades 1324 is provided. will guide In this case, the turbine casing 1312 and the turbine vane 1314 corresponding to the fixed body may also be defined as a generic name of the turbine stator 110 in order to distinguish them from the turbine rotor 120 corresponding to the rotating body.

The turbine vane 1314 is fixedly mounted within the housing by the vane carrier 200 , which is an endwall coupled to the inner and outer ends of the turbine vane 1314 . On the other hand, at a position facing the outer end of the rotating turbine blade 1324 inside the housing, the ring segment 170 is mounted to form a predetermined gap with the outer end of the turbine blade 1324 . That is, the gap between the ring segment 170 and the outer end of the turbine blade 1324 forms a tip clearance.

On the other hand, the turbine blade 1324 is in direct contact with the combustion gas of high temperature and high pressure. The turbine blade 1324 may be deformed by the combustion gas, and the turbine 1300 may be damaged by the deformation of the turbine blade 1324 . In order to prevent deformation due to such high temperature, a branch flow path for supplying a portion of air in the compressor 1100 having a relatively lower temperature than combustion gas to the turbine blade 1324 between the compressor 1100 and the turbine 1300 is branched. 1800 may be formed.

The branch flow path 1800 may be formed outside the compressor casing, or formed inside the turbine casing or through the compressor rotor disk 1120 . The branch flow path 1800 may supply compressed air branched from the compressor 1100 into the turbine rotor disk 1322 . The compressed air supplied to the inside of the turbine rotor disk 1322 flows outward in the radial direction, and may be supplied to the inside of the turbine blade 1324 to cool the turbine blade 1324 . In addition, the compressed air supplied into the turbine casing may be supplied to cool the ring segment 170 as will be described later.

In addition, the branch flow path 1800 connected to the outside of the housing 1010 may supply compressed air branched from the compressor 1100 into the turbine casing 1312 to cool the inside of the turbine casing 1312 . The branch flow path 1800 may have a valve 1820 in the middle to selectively supply compressed air. In addition, a heat exchanger (not shown) may be connected to the branch flow path 1800 to selectively further cool the compressed air and then supply it.

4 is a partial cross-sectional view showing a tip clearance control device according to an embodiment of the present invention, FIG. 5 is a cross-sectional view showing a dummy flange (a) and a carrier segment (b) according to an embodiment of the present invention, FIG. 6 is a partially cut-away perspective view showing a tip clearance control device according to an embodiment of the present invention. 7 to 9 are perspective views illustrating a dummy flange according to an embodiment of the present invention, and FIGS. 10 and 11 are perspective views illustrating a carrier segment according to an embodiment of the present invention.

Tip clearance control device according to an embodiment of the present invention is a device for controlling the tip clearance formed between the turbine casing and the turbine blade, the casing 110 surrounding the turbine blade 1324, a concave groove formed on the outer peripheral surface of the casing A dummy flange 120 mounted on an outer circumferential surface and including a plurality of cooling fins 124 on an outer circumferential surface, a mounting rib 123 formed on an inner circumferential surface of the dummy flange, is mounted movably in a radial direction on the casing, and cooling air flows therein. It may include a carrier segment 140 having a space formed therein, and a ring segment 170 mounted on a mounting rib part 151 formed on an inner circumferential surface of the carrier segment.

The tip clearance control device of the present invention does not mechanically move a specific part to adjust the gap between the turbine blade tip and the ring segment, but adjusts the gap by thermal deformation of the part by controlling the supply amount of cooling air.

The casing 110 forms the exterior of the turbine, and various parts of the tip clearance control device may be mounted in the concave groove 111 formed on the outer circumferential surface.

The dummy flange 120 is mounted on the concave groove 111 of the casing 110 and includes a plurality of cooling fins 124 protruding from the outer circumferential surface and a plurality of cooling holes 122 formed through the casing 110 and supplied from the outside. It can be thermally deformed by the cooling air.

A pair of mounting ribs 123 are formed on the inner circumferential surface of the dummy flange 120 , so that the carrier segment 140 may be mounted on the pair of mounting ribs 123 . The pair of mounting ribs 123 are elastically deformed so as to spread apart from each other so that the inner end of each mounting rib 123 is inserted into the pair of mounting grooves 142 formed on both sides of the carrier segment 140 to be mounted. have.

The carrier segment 140 may be movably mounted to the dummy flange 120 and the casing 110 by a predetermined distance in a radial direction. The carrier segment 140 may have a space in which cooling air flows. The inner space of the carrier segment 140 may be divided into a first space 153 and a second space 154 through which different cooling air flows by a partition wall 155 .

The ring segment 170 may be mounted on a pair of mounting ribs 151 protruding from the inner circumferential surface of the carrier segment 140 . The ring segment 170 may be mounted by being inserted into the pair of mounting ribs 151 of the carrier segment 140 in the circumferential direction.

The carrier segment 140 may be moved in the radial direction as the mounting rib 123 formed on the inner circumferential surface of the dummy flange 120 is deformed by the cooling air passing through the dummy flange 120 .

The shape of the dummy flange 120 and the carrier segment 140 shown in FIG. 4 is particularly in the shape of the mounting rib 123 and the mounting groove 142, and the dummy flange 120 and the carrier segment 140 shown in FIG. 140) is different. Although the form shown in FIG. 5 is more specific, the form shown in FIG. 4 may also be included in the present invention.

The space inside the carrier segment 140 includes a first space 153 in which cooling air supplied from the outside of the casing 110 is introduced through the dummy flange 120 and the introduced cooling air is supplied to the vane carrier 200; A second space 154 through which cooling air supplied through the inside of the casing 110 is introduced and the introduced cooling air is supplied to the ring segment 170 may be included. A detailed structure of the carrier segment 140 will be described in detail later.

The dummy flange 120 includes a curved plate part 121 having a pair of support rib parts 125 mounted in the concave grooves of the casing 110 on both sides in the width direction, and a plurality of cooling fins formed on the outer peripheral surface of the curved plate part ( 124), a plurality of cooling holes 122 penetrating through the curved plate part, and a pair of mounting ribs 123 formed on the inner peripheral surface of the curved plate part and thermally deformed by cooling air supplied from the outside of the casing. .

Eight dummy flanges 120 may be disposed in the circumferential direction of the turbine casing 110 . Thus, each dummy flange 120 may be arranged at about 45 degrees with respect to the central axis of the turbine.

The curved plate part 121 is a curved plate having a predetermined radius of curvature, and both the cooling fin part 124 on the outer peripheral surface and the mounting rib 123 on the internal peripheral surface may be integrally formed. A pair of support ribs 125 extending radially outward from the outer circumferential surface may be formed on both sides of the curved plate part 121 in the width direction, that is, in the axial direction. A protruding rib is formed on the outer surface of each support rib part 125 , and may be inserted and mounted in a circumferential direction into a groove formed on the inner surface of the casing 110 .

Two or more cooling fins 124 may be formed on the outer peripheral surface of the curved plate part 121 to extend radially outwardly. The plurality of cooling fins 124 may increase the heat transfer efficiency of the cooling air supplied from the outside of the casing 110 .

The plurality of cooling holes 122 may be formed in two to four rows in the center of the curved plate part 121 , that is, between the two cooling fin parts 124 .

The pair of mounting ribs 123 may extend radially inward from the outside of the two cooling fins 124 on the inner circumferential surface of the curved plate part 121 . The inner ends of the pair of mounting ribs 123 may be bent in opposite directions, and the bent ends may be formed in a curved shape.

The dummy flange 120 is deformed such that the width direction center of the curved plate part 121 is deformed radially inwardly by the cooling air supplied from the outside of the casing 110 and the pair of mounting ribs 123 are spread apart, so that the carrier segment 140 may be moved radially inward.

And, the outer side of the dummy flange 120 may further include an impingement plate 130 mounted to be spaced apart from the outer peripheral surface by a predetermined distance. The impingement plate 130 may be disposed to be spaced apart a predetermined distance from the outer peripheral surface of the curved plate part 121 , the outer peripheral surface of the cooling fin parts 124 , and the outer peripheral surface of the support rib parts 125 . Thus, the space formed by the gap between the dummy flange 120 and the impingement plate 130 may form a cooling space in which cooling air flows in from the outside.

4, the impingement plate 130 is provided with a plurality of cooling holes formed so that the cooling air supplied from the outside of the casing 110 is impingement cooling on the outer peripheral surface of the dummy flange 120. can

The plurality of cooling holes of the impingement plate 130 includes a plurality of first cooling holes 133 penetrating toward the curved plate portion 121 of the dummy flange 120 , and each cooling fin portion 124 of the dummy flange 120 . ) may include a plurality of second cooling holes 135 through-formed toward.

The plurality of first cooling holes 133 may be formed through a portion parallel to the curved plate portion 121 of the impingement plate 130 in a radial direction. The plurality of first cooling holes 133 may be formed in 3 to 5 rows between the two cooling fin parts 124 of the dummy flange 120 in the impingement plate 130 , and the cooling fin part 124 and the support ribs. It may be formed in one row between the parts 125 .

The plurality of second cooling holes 135 may be formed one by one in the axial direction at the lower portions of the two cooling fins 124 in the impingement plate 130 .

The cooling air supplied from the outside of the casing 110 is introduced into the inner space between the impingement plate 130 and the dummy flange 120 through a plurality of cooling holes to cool the dummy flange 120 by collision, and the dummy flange ( It may flow out toward the carrier segment 140 through the plurality of cooling holes 122 of the 120 .

In addition, the carrier segment 140 includes a body portion 141 having a rectangular cross-section, and a pair of side rib portions protruding from the lower portion of the outer surface of the body portion and inserted into the mounting groove 117 of the casing 110 to be mounted ( 152), a pair of mounting grooves 142 formed concavely on the outer surface of the main body and mounted on a pair of mounting ribs 123 of the dummy flange 120, and a ring segment formed on the inner circumferential surface of the main body ( A pair of mounting ribs 151 to which 170 is mounted may be included.

Eight carrier segments 140 may be mounted in the circumferential direction. Thus, one carrier segment 140 may be formed at an angle of about 45 degrees with respect to the central axis.

The body portion 141 may be a tubular body having a rectangular cross-section, a first space 153 and a second space 154 formed therein, and bent along the circumferential direction.

A pair of side rib parts 152 may be formed to protrude under both side surfaces of the body part 141 . As shown in FIG. 6 , a pair of mounting grooves 117 are formed on the inner surface of the concave groove of the casing 110 , so that a pair of side rib parts 152 are attached to the pair of mounting grooves 117 . It can be inserted and mounted in the circumferential direction.

A pair of mounting grooves 142 may be concavely formed on both sides of the main body 141 . Each end of the pair of mounting ribs 123 of the dummy flange 120 may be elastically inserted and mounted in the pair of mounting grooves 142 .

The pair of mounting ribs 151 are formed to protrude inward in the radial direction from the inner circumferential surface of the main body 141 so that the upper portion of the ring segment 170 is inserted and mounted. Three ring segments 170 may be inserted and mounted in one carrier segment 140 in the circumferential direction.

The carrier segment 140 includes a plurality of upper surface inlet holes 147 that are formed through the upper surface of the main body 141 to introduce cooling air that has passed through the dummy flange 120 into the first space 153 , and the main body portion ( A plurality of side outlet holes 148 that are formed through one side of 141 and flow the cooling air introduced into the first space 153 toward the vane carrier 200 are formed through a plurality of side outlet holes 148 and are formed through the other side of the main body 141. A plurality of side inlet holes 149 for introducing cooling air supplied through the inside of the casing 110 into the second space 154, and a plurality of side inlet holes 149 formed through the lower surface of the main body 141 into the second space 154 It may further include a plurality of lower surface outlet holes 150 for discharging the introduced cooling air toward the ring segment 170 .

The plurality of upper inlet holes 147 may be arranged in three to five columns on the upper surface of the body portion 141 . In the embodiment shown in FIG. 10 , the plurality of upper inlet holes 147 are exemplarily shown to be arranged in 4 columns and 6 rows. The cooling air introduced through the plurality of upper inlet holes 147 is introduced into the first space 153 .

The plurality of side outlet holes 148 are formed through the downstream side of the main body 141 to discharge the cooling air introduced into the first space 153 toward the vane carrier 200 . In the embodiment shown in FIG. 11 , three of the plurality of side outlet holes 148 are exemplarily arranged in the circumferential direction under the mounting groove 142 on the right side of the main body 141 . Just as three ring segments 170 are inserted and mounted in one carrier segment 140 in the circumferential direction, one vane carrier 200 may be mounted in three turbine vanes 1314 in the circumferential direction. to be.

The plurality of side inlet holes 149 are formed through the upstream side of the main body 141 to introduce cooling air supplied through the inside of the casing 110 into the second space 154 . In the embodiment shown in FIG. 10 , six of the plurality of side inlet holes 149 are exemplarily arranged on the left side of the main body 141 in the circumferential direction. The plurality of side inlet holes 149 may be disposed more inwardly in a relatively radial direction than the plurality of side outlet holes 148 . Cooling air compressed by the compressor 1100 and supplied through the inside of the casing 110 may be introduced into the second space 154 through the plurality of side inlet holes 149 .

The plurality of lower surface outlet holes 150 may be formed through the lower surface of the main body 141 in a radial direction to allow the cooling air introduced into the second space 154 to flow out toward the ring segment 170 . In the embodiment shown in FIG. 11 , the plurality of bottom outflow holes 150 are exemplarily shown in which three are arranged in the circumferential direction. This is because three ring segments 170 are inserted and mounted in one carrier segment 140 in the circumferential direction.

Meanwhile, the carrier segment 140 may further include an upper rib portion 143 extending outwardly from the upper surface edge portion of the body portion 141 to form an upper surface groove 144 on the outer peripheral surface of the body portion.

The upper rib portion 143 may be formed to extend radially outwardly from all four corners of the upper edge of the carrier segment 140 in the form of a bent rectangular plate. Thus, the upper surface groove 144 surrounded by the upper rib portion 143 in four directions may be formed on the outer circumferential surface of the carrier segment 140 . In addition, the upper rib portion 143 may be formed so that the width of the portion extending from both edges in the width direction is greater than the width of the inner body portion 141 in the radial direction. Thus, the mounting grooves 142 formed on both sides of the carrier segment 140 may have an upper (radial outward) curved surface longer than their lower (radially inner) curved surface. Accordingly, when the mounting groove 142 of the carrier segment 140 is moved in the radial direction while being mounted on the mounting rib 123 of the dummy flange 120, it can be supported more stably.

In addition, as shown in FIG. 10, a first seal insertion groove 146 is formed in the circumferential direction on the upper surface (outer peripheral surface) of the upper rib part 143, and as shown in FIG. 6, the first seal bar 162 is can be inserted. The first seal bar 162 may be formed of an elastic material such as a rubber band to seal between the inner circumferential surface of the dummy flange 120 and the outer circumferential surface of the carrier segment 140 .

In addition, as shown in FIGS. 10 and 11 , seal member insertion grooves 156 are formed on both circumferential side surfaces of the carrier segment 140 , so that the seal member 160 shown in FIG. 6 can be inserted. The seal member 160 may be disposed along the edges of both circumferential side surfaces of the carrier segment 140 , and may be inserted between the two carrier segments 140 disposed in the circumferential direction by half of the circumferential thickness. Accordingly, the sealing member 160 may be mounted between the plurality of carrier segments 140 to seal between the carrier segments 140 .

And, as shown in Fig. 6, the seal insertion groove is also formed long in the circumferential direction on the inner surface of the casing 110, the second seal bar 164 can be inserted into the seal insertion groove. The second seal bar 164 may also be formed of an elastic material such as a rubber band to seal between the side surface of the carrier segment 140 and the inner surface of the casing 110 .

12 is a partial cross-sectional view showing the flow of cooling air in the tip clearance control device of the present invention.

The cooling air supplied to the vane carrier 200 through the impingement plate 130 , the dummy flange 120 , and the first space 153 of the carrier segment 140 is the air compressed by the compressor 1100 in the casing. (110) It may be supplied to the first space 153 through a flow path connected to the outside. This cooling air may be supplied after being further cooled through a separate heat exchanger. The cooling air introduced into the first space 153 passes through the side outlet hole 148 of the carrier segment 140 and the outlet hole 115 of the casing 110 to be supplied to cool the vane carrier 200 of the next stage. can

The cooling air supplied to the ring segment 170 through the second space 154 of the carrier segment 140 includes a flow path and an inlet hole 113 through which the air compressed in the compressor 1100 is connected to the inside of the casing 110 and It may be supplied to the second space 154 through the side inlet hole 149 of the carrier segment 140 . The cooling air introduced into the second space 154 may be supplied to cool the ring segment 170 through the lower surface outlet hole 150 of the carrier segment 140 .

The temperature of the cooling air supplied to the second space 154 may be 70 ~ 150 ℃ higher than that of the cooling air supplied to the first space 153 . Since the temperature of the cooling air supplied to the second space 154 has a fixed temperature value within a predetermined range, the temperature of the cooling air supplied to the first space 153 may be adjusted by a heat exchanger or the like and then supplied.

According to the tip clearance control device of the present invention, the cold air supply space for controlling the gap and the cold air supply space for cooling the ring segment can be divided and formed independently in one carrier segment.

In addition, the tip clearance can be adjusted by adjusting the deformation amount of the pair of mounting ribs by impingement cooling through the dummy flange and the carrier segment and moving the carrier segment and the ring segment in the radial direction.

In addition, the cooling air flowing into the first space of the carrier segment to adjust the tip clearance may be supplied to the vane carrier of the next stage, and the cooling air flowing into the second space of the carrier segment may be supplied into the ring segment.

In the above, an embodiment of the present invention has been described, but those of ordinary skill in the art can add, change, delete or add components within the scope that does not depart from the spirit of the present invention described in the claims. Various modifications and changes of the present invention will be possible by this, and this will also be 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
1200: combustor 1300: turbine
1310: turbine stator 1312: turbine casing
1314: turbine vane 1320: turbine rotor
1322: turbine rotor disk 1324: turbine blades
1400: diffuser 1450: fixing nut
1500: torque tube unit 1600: tie rod
1800: branch flow path 1820: valve
110: casing 111: concave groove
113: inlet hole 115: outlet hole
117: mounting groove 120: dummy flange
121: curved plate 122: cooling hole
123: mounting rib 124: cooling fin part
125: support rib 130: impingement plate
133: first cooling hole 135: second cooling hole
140: carrier segment 141: body portion
142: mounting groove 143: upper rib portion
144: upper surface groove 145: pin insertion groove
146: first seal insertion groove 147: upper surface inlet hole
148: side outlet hole 149: side inlet hole
150: bottom outlet hole 151: mounting rib portion
152: side rib portion 153: first space
154: second space 155: partition wall
156: sealing member insertion groove 160: sealing member
162: first seal bar 164: second seal bar
170: ring segment 200: vane carrier

Claims (20)

A device for controlling tip clearance formed between a turbine casing and a turbine blade, comprising:
a casing surrounding the turbine blades;
a dummy flange mounted in a concave groove formed on the outer circumferential surface of the casing and including a plurality of cooling fins on the outer circumferential surface;
a mounting rib formed on an inner circumferential surface of the dummy flange;
a carrier segment movably mounted to the casing and having a space in which cooling air flows; and
and a ring segment mounted on a mounting rib formed on an inner circumferential surface of the carrier segment,
The carrier segment is radially moved by the cooling air passing through the dummy flange by deforming the mounting rib formed on the inner circumferential surface of the dummy flange. According to claim 1,
The space inside the carrier segment is
a first space in which cooling air supplied from the outside of the casing flows in through the dummy flange and supplies the introduced cooling air to the vane carrier;
and a second space through which cooling air supplied through the casing is introduced and supplied to the ring segment. 3. The method of claim 2,
The dummy flange is
A curved plate portion having a pair of support rib portions mounted in the concave groove of the casing on both sides in the width direction;
A plurality of cooling fins formed on the outer peripheral surface of the curved plate portion,
A plurality of cooling holes formed through the curved plate portion,
and a pair of mounting ribs formed on the inner circumferential surface of the curved plate portion and thermally deformed by cooling air supplied from the outside of the casing. 4. The method of claim 3,
The dummy flange is deformed so that the width direction center of the curved plate part is deformed radially inwardly and the pair of mounting ribs are spread by the cooling air supplied from the outside of the casing, so that the carrier segment is moved radially inward. Features a tip clearance control. 4. The method of claim 3,
Tip clearance control device, characterized in that it further comprises an impingement plate mounted to be spaced apart a predetermined distance from the outer peripheral surface of the dummy flange. 6. The method of claim 5,
The impingement plate is a tip clearance control device, characterized in that provided with a plurality of cooling holes formed so that the cooling air supplied from the outside of the casing is cooled by collision on the outer peripheral surface of the dummy flange. 7. The method of claim 6,
The plurality of cooling holes of the impingement plate are
a plurality of first cooling holes formed through the curved plate portion of the dummy flange;
Tip clearance control device, characterized in that it comprises a plurality of second cooling holes formed through each cooling fin portion of the dummy flange. 4. The method of claim 3,
The carrier segment is
a body part having a rectangular cross section;
A pair of side ribs protruding from the lower portion of the outer surface of the main body and inserted into and mounted in the mounting groove of the casing;
a pair of mounting grooves formed concavely on the upper outer surface of the main body and mounted on a pair of mounting ribs of the dummy flange;
and a pair of mounting ribs formed on the inner circumferential surface of the main body to which the ring segment is mounted. 9. The method of claim 8,
The carrier segment is
a plurality of upper surface inlet holes which are formed through the upper surface of the main body to introduce cooling air that has passed through the dummy flange into the first space;
A plurality of side outlet holes formed through one side of the main body to discharge the cooling air introduced into the first space toward the vane carrier;
a plurality of side inlet holes formed through the other side of the main body to introduce cooling air supplied through the inside of the casing into the second space;
The tip clearance control device according to claim 1, further comprising: a plurality of lower surface outlet holes formed through the lower surface of the main body to discharge the cooling air introduced into the second space toward the ring segment. 10. The method of claim 9,
The carrier segment further comprises an upper rib portion extending outwardly from the upper surface edge portion of the main body portion to form an upper surface groove on the outer peripheral surface of the main body portion. a compressor that sucks in and compresses outside air;
a combustor for mixing fuel with the air compressed by the compressor and combusting it;
The turbine blade is mounted inside the turbine casing, the turbine blade is rotated by the combustion gas discharged from the combustor; and
a device for controlling tip clearance formed between the turbine casing and the turbine blades;
The device for controlling the tip clearance comprises:
a casing surrounding the turbine blades;
a dummy flange mounted in a concave groove formed on the outer circumferential surface of the casing and including a plurality of cooling fins on the outer circumferential surface;
a mounting rib formed on an inner circumferential surface of the dummy flange;
a carrier segment movably mounted to the casing and having a space in which cooling air flows; and
and a ring segment mounted on a mounting rib formed on an inner circumferential surface of the carrier segment,
The carrier segment is moved in a radial direction by deforming a mounting rib formed on an inner circumferential surface of the dummy flange by cooling air passing through the dummy flange. 12. The method of claim 11,
The space inside the carrier segment is
a first space in which cooling air supplied from the outside of the casing flows in through the dummy flange and supplies the introduced cooling air to the vane carrier;
and a second space in which cooling air supplied through the casing is introduced and the introduced cooling air is supplied to the ring segment. 13. The method of claim 12,
The dummy flange is
A curved plate portion having a pair of support rib portions mounted in the concave groove of the casing on both sides in the width direction;
A plurality of cooling fins formed on the outer peripheral surface of the curved plate portion,
A plurality of cooling holes formed through the curved plate portion,
and a pair of mounting ribs formed on the inner circumferential surface of the curved plate portion and thermally deformed by cooling air supplied from the outside of the casing. 14. The method of claim 13,
The dummy flange is deformed so that the width direction center of the curved plate part is deformed radially inwardly and the pair of mounting ribs are spread by the cooling air supplied from the outside of the casing, so that the carrier segment is moved radially inward. Characterized by a gas turbine. 14. The method of claim 13,
The gas turbine further comprising an impingement plate mounted to be spaced apart a predetermined distance from the outer circumferential surface of the dummy flange. 16. The method of claim 15,
The impingement plate is a gas turbine, characterized in that provided with a plurality of cooling holes formed so that the cooling air supplied from the outside of the casing collision cooling on the outer peripheral surface of the dummy flange. 17. The method of claim 16,
The plurality of cooling holes of the impingement plate are
a plurality of first cooling holes formed through the curved plate portion of the dummy flange;
and a plurality of second cooling holes formed through each cooling fin portion of the dummy flange. 14. The method of claim 13,
The carrier segment is
a body part having a rectangular cross section;
A pair of side ribs protruding from the lower portion of the outer surface of the main body and inserted into and mounted in the mounting groove of the casing;
a pair of mounting grooves formed concavely on the upper outer surface of the main body and mounted on a pair of mounting ribs of the dummy flange;
and a pair of mounting ribs formed on an inner circumferential surface of the main body to which the ring segment is mounted. 19. The method of claim 18,
The carrier segment is
a plurality of upper surface inlet holes which are formed through the upper surface of the main body to introduce cooling air that has passed through the dummy flange into the first space;
A plurality of side outlet holes formed through one side of the main body to discharge the cooling air introduced into the first space toward the vane carrier;
a plurality of side inlet holes formed through the other side of the main body to introduce cooling air supplied through the inside of the casing into the second space;
The gas turbine according to claim 1, further comprising: a plurality of lower surface outlet holes formed through the lower surface of the main body to discharge the cooling air introduced into the second space toward the ring segment. 20. The method of claim 19,
The carrier segment further comprises an upper rib portion extending outwardly from the upper surface edge portion of the body portion to form an upper surface groove on the outer peripheral surface of the main body portion.

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