KR102660054B1 - Ring segment and rotary machine including the same - Google Patents

Abstract

The ring segment according to one aspect of the present invention is mounted on a casing that accommodates a blade, and includes a shielding wall facing the inner wall of the casing, a first hook portion protruding from the shielding wall toward the casing and coupled to the casing, and a first hook portion coupled to the casing. 2 hook parts, and a main cavity formed between the first hook part and the second hook part, and a cooling space inside the shielding wall that receives air from the main cavity and stores cooling air, and the cooling A flow path layer including a plurality of cooling channels through which the cooling air moves while receiving cooling air in the space is formed, and the flow path layer and the cooling space may be spaced apart in the thickness direction of the shielding wall.

Description

Ring segment, rotating machine incorporating it {RING SEGMENT AND ROTARY MACHINE INCLUDING THE SAME}

The present invention relates to ring segments and rotating machines incorporating the same.

A gas turbine is a power engine that mixes compressed air and fuel in a compressor, combusts them, and rotates the turbine with the high-temperature gas generated by combustion. Gas turbines are used to drive generators, aircraft, ships, trains, etc.

Generally, a gas turbine includes a compressor, combustor, and turbine. The compressor takes in outside air, compresses it, and then delivers it to the combustor. The air compressed in the compressor is at high pressure and temperature. The combustor mixes compressed air and fuel introduced from the compressor and combusts them. Combustion gases generated by combustion are injected into the turbine. As the injected combustion gas passes through the turbine vanes and turbine blades, it generates rotational force, which causes the turbine rotor to rotate.

A ring segment is installed inside the turbine to prevent leakage of the high-temperature, high-pressure combustion gas that rotates the rotor and consequently increase the efficiency of the gas turbine. The ring segment is installed within the casing that accommodates the blade and is positioned to surround the outer perimeter of the rotating blade. At this time, one side of the ring segment facing the inner space of the casing is exposed to high temperature and high pressure combustion gas, which may generate a high thermal load, and damage to the ring segment may occur due to the thermal load. These ring segments have a plurality of cooling passages formed inside them to prevent damage due to heat load. Research and development of cooling structures that improve cooling efficiency are continuing to prevent damage due to heat load.

KR 2153065B1 (2020.09.01)

Based on the technical background described above, the present invention seeks to provide a ring segment and a rotating machine with improved cooling performance.

The ring segment according to one aspect of the present invention is mounted on a casing that accommodates a blade, and includes a shielding wall facing the inner wall of the casing, a first hook portion protruding from the shielding wall toward the casing and coupled to the casing, and a first hook portion coupled to the casing. 2 hook parts, and a main cavity formed between the first hook part and the second hook part, and a cooling space inside the shielding wall that receives air from the main cavity and stores cooling air, and the cooling A flow path layer including a plurality of cooling channels through which the cooling air moves while receiving cooling air in the space is formed, and the flow path layer and the cooling space may be spaced apart in the thickness direction of the shielding wall.

A ring segment, characterized in that a collision sheet cooled by air flowing into the cooling space is formed between the cooling space and the flow path layer according to an aspect of the present invention.

A plurality of cooling spaces are formed inside the shielding wall according to one aspect of the present invention, and the cooling spaces can each supply cooling air to cooling channels that move the cooling air in different directions.

The cooling space according to one aspect of the present invention is divided into a first cooling space and a second cooling space by a web, and the web may be formed to extend in the longitudinal direction of the first hook portion.

The flow path layer according to one aspect of the present invention includes a plurality of first cooling channels that discharge air to the first side of the shielding wall and a plurality of first cooling channels that discharge air to the second side facing in the opposite direction from the first side. 2 A cooling passage may be formed.

The first cooling passage and the second cooling passage according to one aspect of the present invention may be alternately arranged.

The web according to one aspect of the present invention extends to the flow path layer, so that the first cooling flow path and the second cooling flow path may be separated by the web.

The interior of the shielding wall according to one aspect of the present invention includes a first side channel extending in one direction and a second side spaced apart from the first side channel in the thickness direction of the shielding wall and receiving cooling air from the first side channel. A side spray hole may be formed that is connected to the channel and the second side channel to discharge cooling air to the outside of the shielding wall.

The first side channel and the second side channel according to one aspect of the present invention may extend in a direction intersecting the first hook portion.

According to one aspect of the present invention, the width of the outer end of the first side channel may be formed to be larger than the width of the inner end, and the width of the outer end of the second side channel may be formed to be smaller than the width of the inner end. .

According to one aspect of the present invention, the first side channel may be formed to have a width that gradually decreases from the outside to the inside, and the second side channel may be formed to have a width that gradually increases from the outside to the inside.

In the shielding wall according to one aspect of the present invention, a plurality of side cooling holes connecting the main cavity and the first side channel and side connection holes connecting the first side channel and the second side channel are formed, The first side channel has an outer surface connected to the side cooling hole, an inner surface facing the outer surface, a first inner surface connecting the inner surface and the outer surface, and a second inner surface connecting the outer surface and the inner surface and being inclined with respect to the inner surface. It includes a side surface, and the side connection hole may be connected to the second inner surface.

Tapered portions whose width gradually decreases toward the outside may be formed on both longitudinal edges of the second side channel according to one aspect of the present invention.

The second side channel according to one aspect of the present invention may be located outside the cooling passages in a lateral direction of the shielding wall.

The second side channel according to one aspect of the present invention may be located further outside the first side channel in the lateral direction of the shielding wall.

The side spray hole according to one aspect of the present invention may be formed so that its inner diameter gradually decreases toward the outside of the shielding wall.

A rotating machine according to an aspect of the present invention includes a rotatable rotor disk, a plurality of blades installed on the rotor disk, a casing for accommodating the blades, and a plurality of ring segments coupled to the casing and located outside the blades. And

The ring segment includes a shielding wall facing the inner wall of the casing, a first hook part and a second hook part protruding from the shielding wall toward the casing and coupled to the casing, and the first hook part and the second hook. It includes a main cavity formed between the parts, and inside the shielding wall, a cooling space that receives air from the main cavity and stores cooling air, and a plurality of cooling units through which cooling air moves while receiving cooling air from the cooling space. A flow path layer with a flow path may be formed, and the flow path layer and the cooling space may be spaced apart in the thickness direction of the shielding wall.

A collision sheet cooled by air flowing into the cooling space may be formed between the cooling space and the flow path layer according to one aspect of the present invention.

A plurality of cooling spaces are formed inside the shielding wall according to one aspect of the present invention, and the cooling spaces can each supply cooling air to cooling channels that move the cooling air in different directions.

The cooling space according to one aspect of the present invention is divided into a first cooling space and a second cooling space by a web, the web is formed extending in the longitudinal direction of the first hook portion, and the first cooling space is provided in the flow path layer. a plurality of first cooling passages connected to the space and discharging air to the first side of the shielding wall, and a plurality of first cooling channels connected to the second cooling space and discharging air to a second side facing in an opposite direction to the first side. A second cooling passage may be formed.

The interior of the shielding wall according to one aspect of the present invention includes a first side channel extending in one direction and a second side spaced apart from the first side channel in the thickness direction of the shielding wall and receiving cooling air from the first side channel. A side spray hole may be formed that is connected to the channel and the second side channel to discharge cooling air to the outside of the shielding wall.

According to the ring segment and rotating machine according to one aspect of the present invention, the cooling space and flow path layer are formed inside the shielding wall spaced apart in the thickness direction of the shielding wall, so the weight of the shielding wall is reduced and shock cooling and flow path cooling are performed simultaneously. Cooling efficiency can be improved.

1 is a diagram showing the interior of a gas turbine according to a first embodiment of the present invention.
FIG. 2 is a longitudinal cross-sectional view of a portion of the gas turbine of FIG. 1.
Figure 3 is a perspective view showing a ring segment according to the first embodiment of the present invention.
Figure 4 is a cut-away perspective view of the ring segment according to the first embodiment of the present invention.
Figure 5 is a cross-sectional view of the shielding plate according to the first embodiment of the present invention.
Figure 6 is a diagram showing a cross section of a cooling passage according to the first embodiment of the present invention.
Figure 7 is a longitudinal cross-sectional view of a ring segment according to the first embodiment of the present invention.
Figure 8 is an enlarged view of A1 in Figure 6.
Figure 9 is a diagram showing a web according to a second embodiment of the present invention.
Figure 10 is a diagram showing a side spray hole according to a third embodiment of the present invention.

Since the present invention can be modified in various ways and can have various embodiments, specific embodiments will be exemplified and explained 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 transformations, equivalents, and substitutes included in the spirit and technical 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. Singular expressions include plural expressions unless the context clearly dictates otherwise. In the present invention, terms such as 'include' or 'have' are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. At this time, note that in the attached drawings, like components are indicated by the same symbols whenever possible. Additionally, 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 shown in the accompanying drawings.

Hereinafter, a gas turbine according to the first embodiment of the present invention will be described.

FIG. 1 is a diagram showing the interior of a gas turbine according to an embodiment of the present invention, and FIG. 2 is a longitudinal cross-sectional view of a portion of the gas turbine of FIG. 1.

1 and 2, the thermodynamic cycle of the gas turbine 1000 according to this embodiment may ideally follow the Brayton cycle. The Brayton cycle can be composed of four processes: isentropic compression (adiabatic compression), constant pressure rapid heating, isentropic expansion (adiabatic expansion), and constant pressure heat dissipation. In other words, it sucks in atmospheric air, compresses it to high pressure, burns fuel in a positive pressure environment to release heat energy, expands this high-temperature combustion gas, converts it into kinetic energy, and releases exhaust gas containing the remaining energy into the atmosphere. You can. In other words, the cycle can be accomplished through four processes: compression, heating, expansion, and heat dissipation.

The gas turbine 1000 realizing the above Brayton cycle may include a compressor 1100, a combustor 1200, and a turbine 1300, as shown in FIG. 1. The following description will refer to FIG. 1, but the description of the present invention can be broadly applied to a turbine engine having a configuration equivalent to the gas turbine 1000 exemplarily shown in FIG. 1.

Referring to FIG. 1, the compressor 1100 of the gas turbine 1000 can suck air from the outside and compress it. The compressor 1100 may supply compressed air compressed by the compressor blade 1130 to the combustor 1200 and may also supply cooling air to a high temperature area in the gas turbine 1000 that requires cooling. At this time, the sucked air undergoes an adiabatic compression process in the compressor 1100, so the pressure and temperature of the air passing through the compressor 1100 increase.

The compressor 1100 is designed as a centrifugal compressor or an axial compressor. While a centrifugal compressor is used in small gas turbines, a large gas turbine 1000 as shown in FIG. 1 uses a large amount of air. Since it is necessary to compress, a multi-stage axial flow compressor (1100) is generally applied. At this time, in the multi-stage axial compressor 1100, the blades 1130 of the compressor 1100 rotate according to the rotation of the center tie rod 1120 and the rotor disk to compress the inflow air and transfer the compressed air to the rear compressor vane ( 1140). The air is compressed to increasingly higher pressure as it passes through the multi-stage blades 1130.

The compressor vane 1140 is mounted inside the housing 1150, and a plurality of compressor vanes 1140 may be mounted to form a stage. The compressor vane 1140 guides the compressed air moved from the front compressor blade 1130 to the rear blade 1130. In one embodiment, at least some of the plurality of compressor vanes 1140 may be mounted to rotate within a predetermined range for controlling the inflow amount of air.

The compressor 1100 may be driven using a portion of the power output from the turbine 1300. To this end, as shown in FIG. 1, the rotation axis of the compressor 1100 and the rotation axis of the turbine 1300 may be directly connected by the torque tube 1170. In the case of a large gas turbine 1000, approximately half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100.

Meanwhile, the combustor 1200 can produce high-energy combustion gas by mixing compressed air supplied from the outlet of the compressor 1100 with fuel and performing isobaric combustion. The combustor 1200 mixes and combusts the incoming compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is raised to the heat resistance limit that the combustor and turbine parts can withstand through the isobaric combustion process. .

A plurality of combustors 1200 may be arranged in a housing formed in a cell shape, and may include a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a connection portion between the combustor and the turbine. It is composed of a transition piece.

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor 1200 is supplied to the turbine 1300. As the supplied high-temperature, high-pressure combustion gas expands, it gives impulse and reaction force to the turbine blade 1400 of the turbine 1300, causing rotational torque, and the rotational torque thus obtained is transmitted to the compressor 1100 through the torque tube 1170 described above. The power exceeding the power required to drive the compressor 1100 is used to drive a generator, etc.

The turbine 1300 includes a rotor disk 1310, a casing 1800, a plurality of turbine blades 1400 radially disposed on the rotor disk 1310, a vane 1500, and a plurality of ring segments surrounding the turbine blade 1400. Includes (1600).

The rotor disk 1310 has a substantially disk shape, and a plurality of grooves are formed on its outer periphery. The groove is formed to have a curved surface, and the turbine blade 1400 and vane 1500 are inserted into the groove. The casing 1800 is made of a truncated cone-shaped tube, and a turbine blade 1400, a vane 1500, and a ring segment 1600 are accommodated within the casing 1800.

The turbine blade 1400 may be coupled to the rotor disk 1310 in a dovetail manner or the like. The vane 1500 is fixed so as not to rotate and guides the flow direction of combustion gas passing through the turbine blade 1400.

Figure 3 is a perspective view showing a ring segment according to the first embodiment of the present invention, and Figure 4 is a cutaway perspective view of the ring segment according to the first embodiment of the present invention.

The ring segment 1600 is mounted on the inner wall of the casing 1800, and the plurality of ring segments 1600 are continuously arranged along the circumferential direction (x-axis direction) of the casing 1800 to form a ring shape.

In this embodiment, the ring segment 1600 is illustrated as being mounted on the turbine 1300, but the present invention is not limited thereto, and the ring segment 1600 may be mounted on a rotating machine such as a compressor 1100. . Here, a rotating machine refers to a device with rotating blades and includes compressors, turbines, etc.

Ring segments 1600 forming a ring shape surround the turbine blade 1400 on the outside of the turbine blade 1400 and prevent leakage of combustion gas. In addition, the ring segments 1600 are arranged alternately with the vanes 1500 in the longitudinal direction (y-axis direction) of the central axis of the turbine 1300, and the ring segments 1600 are inserted between the outer shrouds of the vanes 1500 to form the vanes. Facing (1500).

The ring segment 1600 may include a shielding wall 1611, a first hook portion 1612, a second hook portion 1613, a main cavity (CA), a cooling space 1620, and a flow path layer (PL1). . The shielding wall 1611 is made of a square plate, and the first hook portion 1612 and the second hook portion 1613 are formed from the outer surface of the shielding wall 1611 toward the casing 1800 in the radial direction (z) of the turbine 1300. It protrudes in the axial direction and is inserted into a groove formed in the casing 1800.

In addition, the shield wall 1611 includes a first side (S1) and a second side (S2) facing the turbine vane 1500, and a third side (S3) and a fourth side (S4) facing the neighboring ring segment. can do. The first side (S1) and the second side (S2) are connected in a direction parallel to the first hook portion (1612) (x-axis direction), and the third side (S3) and fourth side (S4) are connected to the first side (S3) and the fourth side (S4). It continues in the direction that intersects (S1) (y-axis direction).

The main cavity (CA) is formed between the first hook part 1612 and the second hook part 1613, and air for cooling is supplied to the main cavity (CA). An auxiliary hook 1618 may be formed outside the first hook portion 1612.

The reinforcing protrusion 1615 protrudes from the shielding wall 1611 and extends from the first hook 1612 toward the second hook 1613. Two reinforcing protrusions 1615 are formed on the shielding wall 1611, and the reinforcing protrusions 1615 protrude from both side ends of the shielding wall 1611. The reinforcing protrusion 1615 extends from the first hook portion 1612 to the second hook portion 1613 and may connect the first hook portion 1612 and the second hook portion 1613. The main cavity CA is formed surrounded by a first hook portion 1612, a second hook portion 1613, and reinforcing protrusions 1615.

A cooling space 1620, a flow path layer PL1, and a collision sheet 1628 may be formed inside the shielding wall 1611. The cooling space 1620 is formed inside the shielding wall 1611 and receives air from the main cavity (CA) to store cooling air. The cooling space 1620 is divided into a first cooling space 1621 and a second cooling space 1622 by a web 1625, and the web 1625 is formed by extending in the longitudinal direction of the first hook portion 1612. . A plurality of impact holes 1627 are formed in the shielding wall 1611 to transmit cooling air from the main cavity (CA) to the cooling space 1620. The web 1625 extends to the flow path layer PL1 to divide the cooling flow path 1630.

A collision sheet 1628 that is cooled by air flowing into the cooling space 1620 is formed between the cooling space 1620 and the flow path layer PL1. The air flowing into the cooling space 1620 through the impact hole 1627 impacts the impact sheet 1628 and cools it.

The cooling space 1620 is located between the first hook portion 1612 and the second hook portion 1613, and is located outside the flow path layer PL1 in the thickness direction of the shielding wall 1611. Cooling space 1620 may have a rectangular cross-section. It is formed to have a first thickness (CT1) between the first hook part 1612 and the second hook part 1613, and the sides of the first hook part 1612 and the second hook part 1613 have a first thickness (CT1). It is formed to have a second thickness (CT2) smaller than CT1). The cooling space 1620 is located in a portion having the first thickness CT1.

As shown in FIG. 5 , a plurality of cooling channels 1630 through which cooling air moves while receiving cooling air from the cooling space 1620 are formed in the flow path layer PL1. The cooling passage 1630 may be formed along a direction (y-axis direction) that intersects the longitudinal direction of the first hook portion 1612.

The flow path layer PL1 and the cooling space 1620 are spaced apart in the thickness direction of the shielding wall 1611, and the flow path layer PL1 is located inside the cooling space 1620. Additionally, the flow path layer PL1 is formed wider than the cooling space 1620 and may extend from the first side S1 to the second side S2.

The flow path layer PL1 includes a plurality of first cooling flow paths 1630a that discharge air to the first side S1 of the shielding wall 1611 and a second side S2 facing in the opposite direction to the first side S1. A plurality of second cooling passages 1630b that discharge air are formed. The first cooling passage 1630a and the second cooling passage 1630b may be separated by a web 1625. Here, the cooling passage 1630 is a concept that includes a first cooling passage 1630a and a second cooling passage 1630b. Cooling air moves in opposite directions in the first cooling passage 1630a and the second cooling passage 1630b to cool the shielding wall.

The shielding wall 1611 includes a plurality of first passages 1651 and second cooling passages 1630b connecting the first cooling passages 1630a and the first cooling space 1621, and the second cooling space 1622. ) A plurality of second passages 1652 connecting ) are formed. The first passage 1651 and the second passage 1652 are spaced apart from each other with the web 1625 therebetween, and may be disposed adjacent to the web 1625. Accordingly, the air flowing into the first cooling space 1621 and the second cooling space 1622 cools the web 1625 and the collision sheet 1628 and then flows through the first passage 1651 or the second passage 1652. It can be supplied to the cooling channel through . Additionally, the plurality of first passages 1630a may be spaced apart in the longitudinal direction of the web 1625, and the plurality of second passages 1630b may be spaced apart in the longitudinal direction of the web 1625.

The first cooling passage 1630a and the second cooling passage 1630b have the same structure and are arranged symmetrically. The first cooling passage 1630a and the second cooling passage 1630b have a structure in which the width is greater than the height, and preferably have a central portion with a uniform height and an outer portion whose width gradually decreases toward the outside. It may have a cross section containing. Here the outer part may lead to an arc shape.

The first cooling passage 1630a and the second cooling passage 1630b may have a serpentine structure in which convex portions and convex portions are alternately formed. The first cooling passage 1630a and the second cooling passage 1630b may be connected in the form of a wave wave or a sinusoidal wave. If the first cooling passage 1630a and the second cooling passage 1630b are formed in a tortuous manner, the contact area and residence time of the cooling air may increase, thereby improving cooling efficiency.

As shown in FIG. 5, the first cooling passage 1630a includes a first intermediate passage 1631 extending from the first passage 1651 toward the second side S2 of the shielding wall 1611, and a first intermediate passage ( 1631), the first discharge passage 1632, which connects to the first side S1 of the shielding wall 1611 and discharges cooling air, and connects the first middle passage 1631 and the first discharge passage 1632 to form an arc shape. It may include a first connection passage 1633 curved.

In addition, the second cooling passage 1630b includes a second intermediate passage 1634 extending from the second passage 1652 toward the first side S1 of the shielding wall 1611 and a shielding wall in the second intermediate passage 1634. When the second discharge passage 1636, which leads to the second side S2 and discharges cooling air, and the second middle passage 1634 and the second discharge passage 1636 are connected, a second connection passage curved in an arc shape ( 1635).

Accordingly, the first cooling passage 1630a and the second cooling passage 1630b can efficiently cool the shielding wall 1611 using a smaller amount of air, and thus the consumption of cooling air is reduced, thereby reducing the turbine ( 1300), the overall efficiency can be improved.

Meanwhile, a throttle section TH1 having a smaller cross-sectional area than the inner side is formed at the longitudinal outer edges of the first cooling passage 1630a and the second cooling passage 1630b. When the throttle section TH1 is formed in this way, cooling air can be sprayed more strongly from the first cooling passage 1630a and the second cooling passage 1630b, thereby improving cooling efficiency and stably preventing combustion gas leakage. can do.

FIG. 6 is a longitudinal cross-sectional view of a ring segment according to the first embodiment of the present invention, FIG. 7 is an enlarged view of A1 in FIG. 6, and FIG. 8 is a first side view according to the first embodiment of the present invention. This is a diagram showing a channel, a second side channel, and a side injection hole.

6 to 8, inside the shielding wall 1611, there is a first side channel 1641 extending in one direction and a wall further inward in the thickness direction of the shielding wall 1611 than the first side channel 1641. A second side channel 1643 is located and receives cooling air from the first side channel 1641, and a plurality of side sprays are connected to the second side channel 1643 and discharge cooling air to the outside of the shielding wall 1611. A hole 1645 may be formed.

The first side channel 1641 and the second side channel 1643 are formed by extending in a direction intersecting the first hook portion 1612, and the side injection hole 1645 is formed parallel to the first hook portion 1612. can be formed. Meanwhile, the first side channel 1641 is located further outside the cooling space 1620 in the lateral direction of the shielding wall 1611, and the second side channel 1643 is located in the cooling flow path in the lateral direction of the shielding wall 1611. It can be located further outside than (1630).

The longitudinal cross-section of the first side channel 1641 may be formed so that the width of the outer end is larger than the width of the inner end, and the width gradually decreases from the outside to the inside. The first side channel 1641 has an outer surface 1641a connected to the supply channel, an inner surface 1641b facing away from the outer surface 1641a, and a first inner surface 1641c connecting the inner surface 1641b and the outer surface 1641a. It may include a second inner surface (1641d) that connects the outer surface (1641a) and the inner surface (1641b) and is inclined with respect to the inner surface. The first inner surface 1641c may extend perpendicularly to the outer surface 1641a and the inner surface 1641b.

In addition, the first side channel 1641 is connected to the main cavity (CA) and the side cooling hole 1647 to receive cooling air from the main cavity (CA), and the side cooling hole 1647 is formed on the outer surface 1641a. is connected to Here, the side cooling hole 1647 may be disposed adjacent to the first inner surface 1641c.

The first side channel 1641 and the second side channel 1643 are connected to each other through a side connection hole 1642, and the side connection hole 1642 is curved and has an inclined second inner surface (1641d). connected to The side connection hole 1642 may be formed in an arc shape. Accordingly, the air introduced through the first side channel 1641 is guided by the inclined second inner surface 1641d after cooling the inside of the first side channel 1641 and is discharged through the side connection hole 1642. You can.

Accordingly, the cooling air introduced through the side cooling hole 1647 impacts and cools the inner surface of the first side channel 1641, and then cools the second side channel 1641 through the side connection hole 1642 formed on the inclined second side S2. Go to side channel (1643).

The longitudinal cross-section of the second side channel 1643 may be formed so that the width of the outer end is smaller than the width of the inner end, and the width gradually increases from the outside to the inside. The second side channel 1643 may have a diamond-shaped cross-section where the outer side is narrower than the inner side. Accordingly, the cooling air supplied from the top spreads inward, thereby cooling the second side channel 1643 as a whole.

In addition, the width (W12) of both longitudinal ends of the second side channel 1643 is smaller than the width (W11) of the longitudinal center of the second side channel 1643. Taper portions 1643b whose width gradually decreases toward the outside may be formed on both edges in the longitudinal direction. Additionally, a uniform portion 1643a with a constant width may be formed between the tapered portions 1643b.

A plurality of side injection holes 1645 are connected to the side of the second side channel 1643 and discharge the cooling air supplied from the second side channel 1643 to the third side S3. The third side S3 extends in a direction crossing the first side S1 and the second side S2. The air injected through the side injection hole 1645 performs cooling while preventing combustion gas from flowing between the turbine vanes 1500.

The side injection hole 1645 is formed so that its inner diameter gradually decreases as it goes outward. Accordingly, air is sprayed at high pressure and high speed through the side injection hole 1645, improving cooling efficiency and preventing combustion gas leakage. It can be reliably prevented.

In addition, since tapered portions 1643b are formed on both longitudinal edges of the second side channel 1643, air is sprayed at high speed from the area where the tapered portion 1643b is formed, thereby efficiently cooling the high temperature areas on both edges. there is.

As described above, according to this embodiment, the cooling space 1620 and the flow path layer PL1 are formed inside the shielding wall 1611 to be spaced apart in the thickness direction of the shielding wall 1611, so impact cooling and flow path cooling are performed simultaneously. Cooling efficiency can be improved, and the weight of the shielding wall 1611 can be reduced.

In addition, since the first side channel 1641 and the second side channel 1643 are connected in a waterfall shape through the side connection hole 1642, the edge of the relatively high temperature ring segment 1600 is cooled twice through shock cooling. It can be cooled efficiently.

Hereinafter, a ring segment according to a second embodiment of the present invention will be described.

Figure 9 is a diagram showing a web according to a second embodiment of the present invention.

Referring to FIG. 9, the ring segment according to this embodiment has the same structure as the ring segment according to the first embodiment described above except for the web, so duplicate description of the same structure will be omitted.

The cooling space 2620 is divided into a first cooling space 2621 and a second cooling space 2622 by a web 2625. The shielding wall 2611 includes a plurality of first passages 2651 connecting the cooling passages 2630 and the first cooling space 2621 and a plurality of first passages 2651 connecting the cooling passages 2630 and the second cooling space 2622. A second passage 2652 is formed. The first passage 2651 and the second passage 2652 are spaced apart from each other with the web 2625 therebetween, and may be disposed adjacent to the web 2625. The web 2625 is formed extending in the longitudinal direction of the first hook portion, and extends to the flow path layer, so that the cooling flow path 2630 can be divided by the web 2625.

The thickness WT11 of the outer end of the web 2625 is greater than the thickness WT12 of the inner end of the web, and the web 2625 may be formed so that the thickness gradually decreases from the outside to the inside. Accordingly, the outer surface of the web 2625 is formed to be inclined with respect to the outer surface of the cooling space, and the web 2625 guides the cooling air moving in the cooling space to the first passage 2651 and the second passage 2652. The cross-sectional area of the first passage 2651 and the second passage 2652 gradually increases toward the inside, allowing cooling air to diffuse more easily.

As described above, according to the second embodiment, the thickness of the web 2625 gradually decreases from the outside to the inside, and the outer surface of the web 2625 is formed to be inclined, so that cooling air flows into the cooling passages 2630. Cooling efficiency can be improved by supplying it more easily.

Hereinafter, a ring segment according to a third embodiment of the present invention will be described.

Figure 10 is a diagram showing a side spray hole according to a third embodiment of the present invention.

Referring to FIG. 10 , the ring segment according to this embodiment has the same structure as the ring segment according to the first embodiment described above except for the side spray hole, so duplicate description of the same structure will be omitted.

A plurality of side spray holes 3640 are connected to the second side channel and discharge cooling air to the outside of the shielding wall. The side spray hole 3640 includes a variable hole 3641 whose inner diameter gradually decreases toward the outside, and a guide hole 3642 that is connected to the end of the variable hole 3641 and has a uniform inner diameter and sprays air to the outside. can do. The moving speed of air increases as it passes through the variable hole 3641, and as it passes through the guide hole 3642, the flow of air can be uniformized and sprayed. Accordingly, cooling efficiency can be further improved.

Above, an embodiment of the present invention has been described, but those skilled in the art can add, change, delete or add components without departing from the spirit of the present invention as set forth in the patent claims. The present invention may be modified and changed in various ways, and this will also be included within the scope of rights of the present invention.

1000: gas turbine
1100: Compressor
1130: Compressor blade
1140: Bane
1150: housing
1170: Torque tube
1200: Combustor
1300: turbine
1310: rotor disk
1400: turbine blade
1500: Bane
1600: Ring segment
1611: Shielding wall
1612: first hook portion
1613: Second hook part
1615: Reinforcement protrusion
1620: Cooling space
1625, 2625: web
1621: First cooling space
1622: Second cooling space
1627: Impact Hole
1628: Crash Sheet
1641: first side channel
1642: Side connection hole
1643: second side channel
1645, 3640: Side spray hole
1647: Side cooling hole
1630, 2630: Cooling flow path
1630a: first cooling passage
1630b: Second cooling passage
1631: 1st intermediate euro
1632: First discharge flow path
1633: First connection flow path
1634: Second intermediate euro
1635: Second connection flow path
1636: Second discharge flow path
1651, 2651: First Passage
1652, 2652: Second Passage
1800: Casing
3641: Variable hole
3642: Information hall

Claims (20)

In the ring segment mounted on the casing accommodating the blade,
a shielding wall facing the inner wall of the casing;
a first hook part and a second hook part protruding from the shielding wall toward the casing and coupled to the casing;
a main cavity formed between the first hook portion and the second hook portion;
Including,
A flow path layer is formed in the shielding wall, including a cooling space that receives air from the main cavity and stores cooling air, and a plurality of cooling passages through which cooling air moves while receiving cooling air from the cooling space,
The flow path layer and the cooling space are formed inside the integrally formed shielding wall and are spaced apart in the thickness direction of the shielding wall,
The thickness of the portion of the shielding wall where the cooling space is formed is larger than that of other portions,
A collision sheet cooled by air flowing into the cooling space is formed between the cooling space and the flow path layer,
The cooling space is divided into a first cooling space and a second cooling space by a web,
A plurality of first cooling passages for discharging air to a first side of the shielding wall and a plurality of second cooling passages for discharging air to a second side facing in a direction opposite to the first side are formed in the flow path layer,
The web penetrates the collision sheet to connect surfaces formed inside the cooling channels and surfaces formed outside the cooling space, wherein the first cooling channel and the second cooling channel are separated by the web,
A first passage connecting the first cooling space and the flow passages and a plurality of second passages connecting the second cooling space and the flow passages are formed inside the shielding wall, and the first passage and the second passage are the It is formed to contact the web,
A ring segment, wherein the web is formed to gradually decrease in thickness from the outside to the inside. delete delete delete delete According to claim 1,
A ring segment, characterized in that the first cooling passage and the second cooling passage are arranged alternately. delete According to claim 1,
Inside the shielding wall, there is a first side channel extending in one direction, a second side channel spaced apart from the first side channel in the thickness direction of the shielding wall, and receiving cooling air from the first side channel. A ring segment connected to a side spray hole that discharges cooling air to the outside of the shielding wall. According to clause 8,
A ring segment, wherein the first side channel and the second side channel are connected in a direction intersecting the first hook portion. According to clause 8,
A ring segment, characterized in that the width of the outer end of the first side channel is formed to be larger than the width of the inner end, and the width of the second side channel is formed to be smaller than the width of the inner end. According to clause 8,
The first side channel is formed to gradually decrease in width from the outside to the inside, and the second side channel is formed to gradually increase in width from the outside to the inside. According to claim 11,
A plurality of side cooling holes connecting the main cavity and the first side channel and side connection holes connecting the first side channel and the second side channel are formed in the shielding wall,
The first side channel has an outer surface connected to the side cooling hole, an inner surface facing the outer surface, a first inner surface connecting the inner surface and the outer surface, and a second inner surface connecting the outer surface and the inner surface and being inclined with respect to the inner surface. A ring segment including a side surface, wherein the side connection hole is connected to the second inner surface. According to clause 8,
A ring segment, characterized in that tapered portions whose width gradually decreases toward the outside are formed on both longitudinal edges of the second side channel. According to clause 8,
The second side channel is a ring segment located further outside the first side channel in the lateral direction of the shielding wall. According to clause 8,
A ring segment wherein the side spray hole is formed so that its inner diameter gradually decreases toward the outside of the shielding wall. A rotary machine comprising a rotatable rotor disk, a plurality of blades installed on the rotor disk, a casing accommodating the blades, and a plurality of ring segments coupled to the casing and located outside the blades,
The ring segment is,
a shielding wall facing the inner wall of the casing;
a first hook part and a second hook part protruding from the shielding wall toward the casing and coupled to the casing;
a main cavity formed between the first hook portion and the second hook portion;
Including,
A flow path layer is formed in the shielding wall, including a cooling space that receives air from the main cavity and stores cooling air, and a plurality of cooling channels through which cooling air moves while receiving cooling air from the cooling space,
The flow path layer and the cooling space are formed inside the integrally formed shielding wall and are spaced apart in the thickness direction of the shielding wall,
The thickness of the portion where the cooling space is formed in the shielding wall is greater than that of other portions,
A collision sheet cooled by air flowing into the cooling space is formed between the cooling space and the flow path layer,
The cooling space is divided into a first cooling space and a second cooling space by a web,
A plurality of first cooling passages for discharging air to a first side of the shielding wall and a plurality of second cooling passages for discharging air to a second side facing in an opposite direction to the first side are formed in the flow path layer,
The web penetrates the collision sheet to connect surfaces formed inside the cooling channels and surfaces formed outside the cooling space, wherein the first cooling channel and the second cooling channel are separated by the web,
A first passage connecting the first cooling space and the flow passages and a plurality of second passages connecting the second cooling space and the flow passages are formed inside the shielding wall, and the first passage and the second passage are the It is formed to contact the web,
A rotating machine, wherein the web is formed to gradually decrease in thickness from the outside to the inside. delete delete delete According to claim 16,
Inside the shielding wall, there is a first side channel extending in one direction, a second side channel spaced apart from the first side channel in the thickness direction of the shielding wall, and receiving cooling air from the first side channel. A rotating machine characterized in that a side injection hole is formed that is connected to and discharges cooling air to the outside of the shielding wall.

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