KR20230039942A - Ring segment and rotary machine including the same - Google Patents

Abstract

The present invention is to provide a ring segment and a rotary machine with improved cooling performance. A ring segment according to one aspect of the present invention is mounted on a casing accommodating blades, and comprises a shielding wall facing the inner wall of the casing, first and second hook parts protruding from the shielding wall toward the turbine casing and coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, and a passage layer formed inside the shielding wall and having a plurality of cooling passages through which cooling air moves, wherein at an outer edge of the cooling passage in the longitudinal direction, a throttle section having a smaller cross-sectional area than the inner side may be formed.

Description

Ring segment, rotary machine including the same {RING SEGMENT AND ROTARY MACHINE INCLUDING THE SAME}

The present invention relates to a ring segment and a rotary machine including the same.

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

Gas turbines generally include a compressor, a combustor and a turbine. The compressor draws in outside air, compresses it, and delivers it to the combustor. The air compressed in the compressor becomes a high-pressure and high-temperature state. The combustor mixes the compressed air introduced from the compressor with the fuel and combusts it. Combustion gases generated by combustion are injected into the turbine. The injected combustion gas generates rotational force while passing through the turbine vanes and turbine blades, thereby causing the turbine rotor to rotate.

A ring segment is installed inside the turbine to prevent leakage of high-temperature and high-pressure combustion gas that rotates the rotor and consequently increase the efficiency of the gas turbine. The ring segment is installed in the turbine casing accommodating the blade and positioned to surround the rotating blade periphery. At this time, one surface of the ring segment facing the inner space of the turbine casing is exposed to high-temperature and high-pressure combustion gas, and a high thermal load may be generated, and damage to the ring segment may occur due to the thermal load. A plurality of cooling passages are formed inside the ring segment to prevent damage due to heat load. In order to prevent damage due to heat load, research and development of a cooling structure that improves cooling efficiency is ongoing.

KR 2153065B1 (2020.09.01)

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

A ring segment according to one aspect of the present invention is mounted on a casing accommodating blades, a shielding wall facing the inner wall of the casing, and a first hook portion protruding from the shielding wall toward the turbine casing and coupled to the turbine casing. And a second hook part, a main cavity formed between the first hook part and the second hook part, and a passage layer formed inside the shield wall and having a plurality of cooling passages through which cooling air moves, wherein the A throttle section having a smaller cross-sectional area than the inner side may be formed at an outer edge of the cooling passage in the longitudinal direction.

The cooling passage according to one aspect of the present invention may include a first cooling passage and a second cooling passage moving in opposite directions.

According to one aspect of the present invention, the first cooling passage and the second cooling passage may be spaced apart from each other with a web erected in a thickness direction of the shield wall interposed therebetween.

The cooling passage according to one aspect of the present invention may have a width extending in a lateral direction of the shielding wall greater than a height extending in a thickness direction of the shielding wall.

According to one aspect of the present invention, a longitudinal section of the cooling passage may include a central portion having a uniform height and an outer portion having a width gradually decreasing toward the outside.

The outer portion according to an aspect of the present invention may be continued in an arc shape.

According to one aspect of the present invention, the outer portion may be formed of two inclined surfaces inclined with respect to the central portion.

According to one aspect of the present invention, the first cooling passage and the second cooling passage may meander.

According to one aspect of the present invention, a first intermediate passage extending from the first passage for supplying air to the first cooling passage to one side of the shielding wall and a first discharge extending from the first intermediate passage to the other side of the shielding wall It may include a curved first connection passage connecting the passage, the first intermediate passage, and the first discharge passage.

According to one aspect of the present invention, a cooling space receiving air from the main cavity and storing cooling air is formed inside the shielding wall, and the cooling space is connected to the cooling passages to supply cooling air to the cooling passages. However, the cooling space and the passage layer may be spaced apart from each other in a thickness direction of the shielding wall.

According to one aspect of the present invention, the web is connected to the cooling space, and the cooling space is divided into a first cooling space and a second cooling space by the web, and the first cooling space includes a plurality of the first cooling passages and connected, and the second cooling space may be connected to a plurality of the second cooling spaces.

According to one aspect of the present invention, the throttle section may include a variable section in which an inner diameter gradually decreases toward the outside and an injection guide section connected to an end of the variable section and having a uniform inner diameter and injecting air to the outside.

A rotary machine according to one aspect of the present invention includes 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 positioned outside the blades. 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 turbine casing and coupled to the turbine casing, the first hook part A main cavity formed between the second hook parts and a passage layer formed inside the shield wall and having a plurality of cooling passages through which cooling air moves, wherein an outer edge of the cooling passage in a longitudinal direction has a smaller cross-sectional area than an inner edge of the cooling passage. A throttle section having may be formed.

The cooling passage according to one aspect of the present invention may include a first cooling passage and a second cooling passage moving in opposite directions.

According to one aspect of the present invention, the first cooling passage and the second cooling passage may be spaced apart from each other with a web erected in a thickness direction of the shield wall interposed therebetween.

The cooling passage according to one aspect of the present invention may have a width extending in a lateral direction of the shielding wall greater than a height extending in a thickness direction of the shielding wall.

According to one aspect of the present invention, a longitudinal section of the cooling passage may include a central portion having a uniform height and an outer portion having a width gradually decreasing toward the outside.

According to one aspect of the present invention, a first intermediate passage extending from the first passage for supplying air to the first cooling passage to one side of the shielding wall and a first discharge extending from the first intermediate passage to the other side of the shielding wall It may include a curved first connection passage connecting a passage, the first intermediate passage, and the first discharge passage.

According to one aspect of the present invention, a cooling space receiving air from the main cavity and storing cooling air is formed inside the shielding wall, and the cooling space is connected to the cooling passages to supply cooling air to the cooling passages. However, the cooling space and the passage layer are spaced apart in the thickness direction of the shielding wall, and the web is connected to the cooling space so that the cooling space can be divided into a first cooling space and a second cooling space by the web. there is.

According to one aspect of the present invention, the throttle section may include a variable section in which an inner diameter gradually decreases toward the outside and an injection guide section connected to an end of the variable section and having a uniform inner diameter and injecting air to the outside.

According to an aspect of the present invention, since a throttle section is formed at the longitudinal end of the ring segment and the cooling passage to inject cooling air at a strong speed and pressure, cooling efficiency can be improved.

1 is a view showing the inside of a gas turbine according to a first embodiment of the present invention.
FIG. 2 is a longitudinal cross-sectional view of a part of the gas turbine of FIG. 1 .
3 is a perspective view showing a ring segment according to a first embodiment of the present invention.
4 is a cutaway perspective view of a ring segment according to a first embodiment of the present invention.
5 is a cross-sectional view of a shield plate according to a first embodiment of the present invention when cut.
6 is a longitudinal cross-sectional view of a cooling passage according to a first embodiment of the present invention.
7 is a longitudinal cross-sectional view of a ring segment according to the first embodiment of the present invention.
FIG. 8 is an enlarged view of A1 in FIG. 7 .
9 is a diagram illustrating a first side channel, a second side channel, and a side spray hole according to the first embodiment of the present invention.
10 is a view showing a longitudinal cross-section of a cooling passage according to a second embodiment of the present invention.
11 is a diagram showing a throttle section according to a third embodiment of the present invention.

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

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 'having' are intended to designate that there is a feature, number, step, operation, component, part, or combination thereof described in the specification, but one or more other features It should be understood that the presence or addition of numbers, steps, operations, components, parts, or combinations thereof is not precluded.

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 indicated 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, in the accompanying drawings, some components are exaggerated, omitted, or schematically illustrated.

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

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

Referring to FIGS. 1 and 2 , the thermodynamic cycle of the gas turbine 1000 according to the present embodiment may ideally follow a Brayton cycle. The Brayton cycle can be composed of four processes leading to isentropic compression (adiabatic compression), constant pressure rapid heat, isentropic expansion (adiabatic expansion), and constant pressure heat dissipation. In other words, atmospheric air is sucked in and compressed to high pressure, and fuel is burned in a constant pressure environment to release thermal energy. can That is, the cycle may be made in four processes of compression, heating, expansion, and heat dissipation.

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

Referring to FIG. 1 , the compressor 1100 of the gas turbine 1000 may intake and compress air from the outside. The compressor 1100 may supply compressed air compressed by the compressor blades 1130 to the combustor 1200 and may also supply cooling air to a high-temperature region in the gas turbine 1000 requiring cooling. At this time, since the sucked air undergoes an adiabatic compression process in the compressor 1100, the pressure and temperature of the air passing through the compressor 1100 increase.

The compressor 1100 is designed as centrifugal compressors or axial compressors. In a small gas turbine, a centrifugal compressor is applied, whereas in a large gas turbine 1000 as shown in FIG. 1, a large amount of air Since it is necessary to compress the multi-stage axial flow compressor 1100 is generally applied. At this time, in the multi-stage axial flow 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 introduced air while passing the compressed air to the compressor vanes at the rear ( 1140). The air is compressed to a higher pressure while passing through the blades 1130 formed in multiple stages.

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 compressor blade 1130 at the front to the blade 1130 at the rear. In one embodiment, at least some of the plurality of compressor vanes 1140 may be mounted to be rotatable within a predetermined range for adjusting the inflow of air.

The compressor 1100 may be driven using some 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 a torque tube 1170 . In the case of the large gas turbine 1000, about half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100.

Meanwhile, the combustor 1200 may mix compressed air supplied from the outlet of the compressor 1100 with fuel and perform constant pressure combustion to generate high-energy combustion gas. In the combustor 1200, the introduced compressed air is mixed with fuel and combusted to produce high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is raised to the 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 a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a connection between the combustor and the turbine It is composed of including a transition piece to be.

Meanwhile, high-temperature, high-pressure combustion gas from the combustor 1200 is supplied to the turbine 1300. As the supplied high-temperature and high-pressure combustion gas expands, impulse and reaction force are applied to the turbine blades 1400 of the turbine 1300 to generate rotational torque. , and power exceeding the power required to drive the compressor 1100 is used to drive a generator or the like.

The turbine 1300 includes a rotor disk 1310, a turbine casing 1800, a plurality of turbine blades 1400 radially disposed on the rotor disk 1310, a vane 1500, and a plurality of rings surrounding the turbine blades 1400. segment 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 the vane 1500 are inserted into the groove. The turbine casing 1800 is formed of a truncated conical tube, and the turbine blade 1400, the vane 1500, and the ring segment 1600 are accommodated in the turbine casing 1800.

The turbine blades 1400 may be coupled to the rotor disk 1310 in a dovetail or the like. The vanes 1500 are fixed so as not to rotate and guide the flow direction of the combustion gas passing through the turbine blades 1400 .

3 is a perspective view showing a ring segment according to the first embodiment of the present invention, and FIG. 4 is a cut-away 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 turbine casing 1800, and the plurality of ring segments 1600 are continuously arranged along the circumferential direction (x-axis direction) of the turbine 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, the rotary machine means a device having rotating blades, and is a concept including a compressor, a turbine, and the like.

The ring segments 1600 forming an annular shape surround the turbine blades 1400 from the outside of the turbine blades 1400 and prevent leakage of combustion gas. In addition, the ring segments 1600 are alternately arranged 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 Face (1500).

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

In addition, the shielding wall 1611 includes a first side surface S1 and a second side surface S2 facing the turbine vane 1500, and a third side surface S3 and a fourth side surface S4 facing adjacent ring segments. can do. The first side surface S1 and the second side surface S2 extend in a direction parallel to the first hook portion 1612 (x-axis direction), and the third side surface S3 and the fourth side surface S4 extend along the first side surface S3 and the fourth side surface S4. It continues in a direction (y-axis direction) intersecting with (S1).

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 part 1612 .

The reinforcing protrusion 1615 protrudes from the shielding wall 1611 and continues from the first hook part 1612 toward the second hook part 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 may extend from the first hook part 1612 to the second hook part 1613 to connect the first hook part 1612 and the second hook part 1613 . The main cavity CA is formed surrounded by the first hook part 1612 , the second hook part 1613 , and the reinforcing protrusion part 1615 .

A cooling space 1620 , a passage layer PL1 , and an impact 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 the cooling air. The cooling space 1620 is separated into a first cooling space 1621 and a second cooling space 1622 by a web 1625, and the web 1625 is formed by continuing in the longitudinal direction of the first hook part 1612. . In addition, the web 1625 is erected and disposed in the thickness direction of the shield wall 1611 .

A plurality of impact holes 1627 are formed in the shielding wall 1611 to transfer cooling air from the main cavity CA to the cooling space 1620 . The web 1625 may extend to the passage layer PL1 and divide the cooling passage 1630 .

An impact sheet 1628 cooled by air introduced into the cooling space 1620 is formed between the cooling space 1620 and the passage layer PL1 . The air introduced into the cooling space 1620 through the impact hole 1627 impacts the impact sheet 1628 to cool the impact sheet 1628 .

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

As shown in FIGS. 5 and 6 , a plurality of cooling passages 1630 through which cooling air is transferred while receiving cooling air from the cooling space 1620 are formed in the passage layer PL1 . The cooling passage 1630 may be formed to continue in a direction (y-axis direction) crossing the longitudinal direction of the first hook part 1612 .

The passage layer PL1 and the cooling space 1620 are spaced apart in the thickness direction of the shielding wall 1611 , and the passage layer PL1 is located inside the cooling space 1620 . In addition, the passage layer PL1 is formed wider than the cooling space 1620 and may be formed extending from the first side surface S1 to the second side surface S2.

The passage layer PL1 includes a plurality of first cooling passages 1630a discharging air to the first side surface S1 of the shielding wall 1611 and a second side surface S2 facing the opposite direction to the first side surface S1. A plurality of second cooling passages 1630b discharging air are formed. The first cooling passage 1630a and the second cooling passage 1630b may be separated by a web 1625, and thus the longitudinal ends of the first cooling passage 1630a and the second cooling passage 1630b are formed by the web 1625. (1625) is spaced apart.

Here, the cooling passage 1630 has a concept including 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 connecting the first cooling passages 1630a and the first cooling space 1621, the second cooling passages 1630b, and the second cooling space 1622. ) A plurality of second passages 1652 connecting them are formed. The first passage 1651 and the second passage 1652 may be spaced apart with a web 1625 therebetween and disposed adjacent to the web 1625 . Accordingly, the air introduced into the first cooling space 1621 and the second cooling space 1622 cools the web 1625 and the impact sheet 1628, and then moves through the first passage 1651 or the second passage 1652. It can be supplied to the cooling passage through. Also, the plurality of first passages 1630a may be spaced apart from each other in the longitudinal direction of the web 1625, and the plurality of second passages 1630b may be spaced apart from each other in the length direction of the web 1625.

The first cooling passage 1630a and the second cooling passage 1630b have the same structure and are symmetrically disposed. The cooling passage 1630 has a structure in which the width PW1 of the shield wall 1611 in the lateral direction is greater than the height PH1 of the shield wall 1611 in the thickness direction. A longitudinal section of the cooling passage 1630 may have a section including a central portion FL11 having a uniform height and an outer portion FL12 whose width gradually decreases toward the outside. Here, the outer part may be continued in an arc shape.

In this way, when the cooling passage 1630 has a structure in which the width is greater than the height, the cold heat can be more efficiently transferred in one direction compared to a circular structure, and accordingly, the inner portion of the ring segment 1600 (the surface facing the blade) ) can efficiently cool the heat generated in In addition, if the cross section of the cooling passage 1630 has a track structure having a parallel central portion FL11 and an arc-shaped outer portion FL12, cooling efficiency may be further improved.

The first cooling passage 1630a and the second cooling passage 1630b may have a meandering structure by alternately forming concave and convex portions. The first cooling channel 1630a and the second cooling channel 1630b may be connected in the form of a water wave or a sine wave. In this way, when the first cooling passage 1630a and the second cooling passage 1630b are meanderingly formed, 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 surface S2 of the shielding wall 1611 and a first intermediate passage ( 1631) to the first side surface S1 of the shielding wall 1611 and connecting the first discharge passage 1632 for discharging cooling air, the first intermediate passage 1631, and the first discharge passage 1632 to form an arc shape. It may include a first connection passage 1633 curved as .

In addition, the second cooling passage 1630b includes a second intermediate passage 1634 extending from the second passage 1652 toward the first side surface S1 of the shielding wall 1611 and a shielding wall in the second intermediate passage 1634. Connecting the second discharge passage 1636 leading to the second side surface S2 and discharging cooling air, the second intermediate passage 1634, and the second discharge passage 1636, the second connection passage curved in an arc shape ( 1635) may be included.

Accordingly, the first cooling passage 1630a and the second cooling passage 1630b can efficiently cool the shield wall 1611 using a smaller amount of air, and accordingly, the consumption of cooling air is reduced and the turbine ( 1300) can be improved.

Meanwhile, a throttle section TH1 having a smaller cross-sectional area than the inner side is formed at outer edges in the longitudinal direction of the first cooling passage 1630a and the second cooling passage 1630b, and each throttle section TH1 is a discharge passage 1632. , 1636) is formed at the longitudinal end. The throttle section TH1 may be formed in a cylindrical shape, and a step may be formed at a portion where the throttle section TH1 and the discharge passages 1632 and 1636 are connected.

In this way, when the throttle section TH1 is formed, cooling air is more strongly injected from the first cooling passage 1630a and the second cooling passage 1630b, thereby improving cooling efficiency and stably preventing leakage of combustion gas. can do.

7 is a longitudinal cross-sectional view of a ring segment according to the first embodiment of the present invention, FIG. 8 is an enlarged view of A1 in FIG. 6, and FIG. 9 is a first side view according to the first embodiment of the present invention. It is a drawing showing a channel, a second side channel, and a side injection hole.

Referring to FIGS. 7 to 9 , inside the shielding wall 1611, the first side channel 1641 connected in one direction and further inside in the thickness direction of the shielding wall 1611 than the first side channel 1641 A second side channel 1643 located there and receiving cooling air from the first side channel 1641 and a plurality of side jets connected to the second side channel 1643 and discharging cooling air to the outside of the shield wall 1611 A hole 1645 may be formed.

The first side channel 1641 and the second side channel 1643 are connected in a direction crossing the first hook part 1612, and the side spray hole 1645 is connected in parallel with the first hook part 1612. can be formed Meanwhile, the first side channel 1641 is located outside the cooling space 1620 in the lateral direction of the shield wall 1611, and the second side channel 1643 is a cooling passage in the lateral direction of the shield wall 1611. (1630) may be located further outside.

The longitudinal cross-section of the first side channel 1641 may be formed such that the width of the outer end is greater than the width of the inner end, and the width gradually decreases from the outer side to the inner side. The first side channel 1641 includes an outer surface 1641a connected to the supply channel, an inner surface 1641b spaced apart from the outer surface 1641a, and a first inner surface 1641c connecting the inner surface 1641b and the outer surface 1641a. and a second inner surface 1641d connecting the outer surface 1641a and the inner surface 1641b and inclined with respect to the inner surface. The first inner surface 1641c may extend vertically to the outer surface 1641a and the inner surface 1641b.

In addition, the first side channel 1641 is connected to the main cavity CA through a side cooling hole 1647 to receive cooling air from the main cavity CA, and the side cooling hole 1647 is connected to the outer surface 1641a. connected with 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 formed by being bent 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. 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 passes through the side connection hole 1642 formed on the inclined second side surface S2 to the second side channel 1641. Move to side channel 1643.

The longitudinal cross-section of the second side channel 1643 may be formed such that the width of the outer end is smaller than the width of the inner end, and the width gradually increases from the outer side to the inner side. The second side channel 1643 may have a diamond-shaped cross section with an outer side narrower than an inner side. Accordingly, the entire second side channel 1643 can be cooled while the cooling air supplied from the top spreads inward.

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

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

The side injection hole 1645 is formed such that the inner diameter gradually decreases toward the outside, and accordingly, air is injected at high pressure and high speed through the side injection hole 1645 to improve cooling efficiency and prevent leakage of combustion gas. can be reliably prevented.

In addition, since the tapered portion 1643b is formed at both edges of the second side channel 1643 in the longitudinal direction, air is sprayed at a high speed in the area where the tapered portion 1643b is formed to efficiently cool the high-temperature area at both edges. there is.

As described above, according to the present embodiment, since the cooling space 1620 and the passage layer PL1 are spaced apart in the thickness direction of the shield wall 1611 inside the shield wall 1611, impact cooling and passage cooling are performed simultaneously. Cooling efficiency may be improved, and the weight of the shielding wall 1611 may be reduced.

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

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

10 is a view showing a longitudinal cross-section of a cooling passage according to a second embodiment of the present invention.

Referring to FIG. 10, since the ring segment according to the present embodiment has the same structure as the ring segment according to the first embodiment except for the cooling passage 2670, redundant description of the same configuration will be omitted. .

The cooling passage 2670 has a structure in which the width is greater than the height. A longitudinal section of the cooling passage 2670 may have a section including a central portion 2671 having a uniform height and an outer portion 2672 whose width gradually decreases toward the outside. The outer portion 2672 may be formed of two inclined surfaces inclined with respect to the central portion 2671 .

In this way, when the cooling passage 2670 has a structure in which the width is greater than the height, cooling and heat can be more efficiently transferred in one direction compared to a circular structure.

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

10 is a diagram showing a side throttle section according to a third embodiment of the present invention.

Referring to FIG. 10, since the ring segment according to the present embodiment has the same structure as the ring segment according to the first embodiment except for the throttle section 3640, redundant description of the same configuration will be omitted. .

A throttle section 3640 having a smaller cross-sectional area than the inner side is formed at the longitudinal end of the cooling passage, and the throttle section 3640 is formed at the longitudinal end of the discharge passage. The throttle section 3640 includes a variable section 3641 whose inner diameter gradually decreases toward the outside and an injection guide section 3642 connected to the end of the variable section 3641 and having a uniform inner diameter and injecting air to the outside. can do. The moving speed of air increases while passing through the variable section 3641, and the flow of air can be uniformized and sprayed while passing through the spray guide section 3642. Accordingly, cooling efficiency may be further improved.

In the above, one embodiment of the present invention has been described, but those skilled in the art can add, change, delete, or add components within the scope not departing from the spirit of the present invention described in the claims. The present invention can be variously modified and changed by the like, and this will also be said to be included within the scope 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: vane
1600: ring segment
1611: shielding wall
1612: first hook part
1613: second hook part
1615: reinforcing protrusion
1620: cooling space
1625: Web
1621: first cooling space
1622: second cooling space
1627: impact hole
1628: crash seat
1630, 2670: cooling passage
1630a: first cooling passage
1630b: second cooling passage
1631 First intermediate flow path
1632: first discharge passage
1633: first connection passage
1634 Second intermediate flow path
1635: second connection passage
1636: second discharge passage
1641: first side channel
1642: side connection hole
1643: second side channel
1645: side injection hole
1647: side cooling hole
1651: first passage
1652: second passage
1800: turbine casing
TH1, 3640: throttle section
3641: variable interval
3642: injection guidance section

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 shield wall toward the turbine casing and coupled to the turbine casing;
a main cavity formed between the first hook part and the second hook part;
a passage layer formed inside the shielding wall and having a plurality of cooling passages through which cooling air moves;
including,
A ring segment, characterized in that a throttle section having a smaller cross-sectional area than the inner edge is formed at an outer edge in the longitudinal direction of the cooling passage. According to claim 1,
The ring segment, characterized in that the cooling passage comprises a first cooling passage and a second cooling passage moving in opposite directions to each other. According to claim 2,
The ring segment, characterized in that the first cooling passage and the second cooling passage are spaced apart with a web erected in the thickness direction of the shield wall therebetween. According to claim 2,
The cooling channel is a ring segment, characterized in that the width of the shielding wall in the lateral direction is larger than the height of the shielding wall in the thickness direction. According to claim 4,
The ring segment characterized in that the longitudinal section of the cooling passage comprises a central portion having a uniform height and an outer portion whose width gradually decreases toward the outside. According to claim 5,
The outer portion is a ring segment, characterized in that connected to the arc. According to claim 5,
The ring segment, characterized in that the outer portion consists of two inclined surfaces inclined with respect to the central portion. According to claim 2,
The ring segment, characterized in that the first cooling passage and the second cooling passage are meanderingly connected. According to claim 2,
A first intermediate passage extending from the first passage for supplying air to the first cooling passage to one side of the shield wall, a first discharge passage extending from the first intermediate passage to the other side of the shield wall, and the first intermediate passage And a ring segment characterized in that it comprises a curved first connection passage connecting the first discharge passage. According to claim 2,
A cooling space receiving air from the main cavity and storing cooling air is formed inside the shielding wall, and the cooling space is connected to the cooling passages to supply cooling air to the cooling passages. The passage layer is a ring segment, characterized in that spaced apart in the thickness direction of the shield wall. According to claim 10,
The web is connected to the cooling space, and the cooling space is divided into a first cooling space and a second cooling space by the web,
The ring segment, characterized in that the first cooling space is connected to a plurality of the first cooling passages, and the second cooling space is connected to a plurality of the second cooling spaces. According to claim 2,
The throttle section includes a variable section in which an inner diameter gradually decreases toward the outside and an injection guide section connected to an end of the variable section and having a uniform inner diameter and injecting air to the outside. A rotating 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,
a shielding wall facing the inner wall of the casing;
a first hook part and a second hook part protruding from the shield wall toward the turbine casing and coupled to the turbine casing;
a main cavity formed between the first hook part and the second hook part;
a passage layer formed inside the shielding wall and having a plurality of cooling passages through which cooling air moves;
including,
A rotating machine, characterized in that a throttle section having a smaller cross-sectional area than the inner side is formed at an outer edge in the longitudinal direction of the cooling passage. According to claim 13,
The rotating machine according to claim 1 , wherein the cooling passage includes a first cooling passage and a second cooling passage moving in opposite directions. According to claim 14,
The first cooling passage and the second cooling passage are spaced apart from each other with a web erected in the thickness direction of the shield wall interposed therebetween. According to claim 14,
The cooling passage is characterized in that the width of the shielding wall in the lateral direction is larger than the height of the shielding wall in the thickness direction. According to claim 16,
The longitudinal section of the cooling passage includes a central portion having a uniform height and an outer portion whose width gradually decreases toward the outside. According to claim 14,
A first intermediate passage extending from the first passage for supplying air to the first cooling passage to one side of the shield wall, a first discharge passage extending from the first intermediate passage to the other side of the shield wall, and the first intermediate passage and a curved first connecting passage connecting the first discharge passage to the rotary machine. According to claim 14,
A cooling space receiving air from the main cavity and storing cooling air is formed inside the shielding wall, and the cooling space is connected to the cooling passages to supply cooling air to the cooling passages. The passage layer is spaced apart in the thickness direction of the shielding wall,
The web is connected to the cooling space, and the cooling space is divided into a first cooling space and a second cooling space by the web. According to claim 14,
The throttle section includes a variable section in which an inner diameter gradually decreases toward the outside and an injection guide section connected to an end of the variable section and having a uniform inner diameter and injecting air to the outside.

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