KR102155797B1 - Turbine blade, turbine including the same - Google Patents

Abstract

The present invention aims to provide an air foil which has a turbine blade tip with an improved cooling performance, and a turbine. According to one aspect of the present invention, a turbine blade comprises: an air foil made in a wing shape to have an absorption surface and a pressure surface; a platform unit coupled to a lower side of the air foil; and a route unit protruding from the platform unit downwards to be coupled to a rotor disc. The air foil is connected to the absorption surface and the pressure surface, and includes: a tip plate placed on an external side facing the platform unit; and a plurality of cooling ribs protruding from the tip plate. The cooling ribs include: a first side rib connected to the absorption surface; and a plurality of guide ribs distanced from a leading edge towards a trailing edge and connected from the pressure surface towards the absorption surface.

Description

Turbine blade and turbine including the same {TURBINE BLADE, TURBINE INCLUDING THE SAME}

The present invention relates to a turbine blade, and a turbine comprising the same.

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

Gas turbines generally include compressors, combustors and turbines. The compressor sucks in outside air, compresses it, and delivers it to the combustor. The air compressed by the compressor is in a state of high pressure and high temperature. The combustor combusts by mixing fuel and compressed air introduced from the compressor. The combustion gases generated by combustion are discharged to the turbine. The turbine blades inside the turbine are rotated by the combustion gas, and power is generated through this. The generated power is used in various fields such as power generation and driving of mechanical devices.

In recent years, in order to increase turbine efficiency, the temperature of the gas flowing into the turbine (Turbine Inlet Temperature: TIT) has been constantly increasing, and for this reason, the importance of heat resistance treatment and cooling of the turbine blades has emerged.

Methods for cooling turbine blades include film cooling and internal cooling. In the film cooling method, a coating film is formed on the outer surface of the turbine blade to prevent heat transfer from the outside to the blade. According to the film cooling method, the heat-resistant paint applied to the blade determines the heat resistance and mechanical durability of the blade.

The internal cooling method cools the blade through heat exchange between the cooling fluid and the blade. In general, turbine blades are cooled using compressed cooling air extracted from a compressor of a gas turbine.

The airfoil tip, which is located at the outermost part of the turbine blade in the radial direction, is disposed adjacent to the turbine shroud, so that cooling is very difficult. To this end, in the related art, a tip rib connected in the circumferential direction of the airfoil tip was formed, and air was injected from the tip plate in a state in which the tip plate of the airfoil was formed to surround the tip rib to cool the airfoil tip. However, this tip rib cooling structure has a problem of not only obstructing flow, but also low cooling efficiency.

Republic of Korea Patent Publication No. 10-2010-0076891 (2010. 07. 06)

Based on the technical background as described above, the present invention is to provide a turbine blade and a turbine with improved cooling performance of the turbine blade tip.

A turbine blade according to an aspect of the present invention includes an airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to the lower portion of the airfoil, and protruding downward from the platform portion and coupled to the rotor disk. Including a root portion, the airfoil is connected to the suction surface and the pressure surface, and includes a tip plate disposed outside the platform portion and a plurality of cooling ribs protruding from the tip plate, The cooling rib includes a first side rib connected to the suction surface and a plurality of guide ribs spaced apart from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface.

Here, the guide rib is formed to guide the flow in a direction from the pressure surface toward the first side rib, and the upper space of the pressure surface may be opened laterally.

In addition, the guide rib may include a collision portion facing the pressure surface and a discharge portion bent obliquely toward the suction surface from the collision portion.

In addition, among the guide ribs, a guide rib disposed closest to the leading edge is a front end extending from the leading edge in a direction toward the suction surface and bent at the front end to face the pressure surface at the collision part and the collision part. It may include a discharge portion bent obliquely toward the suction surface.

In addition, among the guide ribs, a guide rib disposed closest to the trailing edge may be formed to be connected along a center line in the width direction of the tip plate.

In addition, a first upper cooling hole may be formed between the guide ribs in the tip plate, and a second upper cooling hole may be formed between the guide rib and the first side rib in the tip plate.

In addition, a plurality of side cooling holes and guide grooves may be formed on the pressure surface to guide air discharged from the side cooling holes to the tip plate by connecting the side cooling holes and the tip plate.

In addition, the cooling rib may further include a second side rib connected to the pressure surface, and the guide rib may be disposed between the first side rib and the second side rib.

In addition, a plurality of side openings connected to the induction groove may be formed in the second side rib.

Further, an inlet opening positioned on a leading edge and an outlet opening positioned on the trailing edge may be formed between the first side rib and the second side rib.

In addition, the guide rib may extend from the pressure surface toward the suction surface and include two bent portions.

In addition, one end of the guide rib in the longitudinal direction may be connected to the pressure surface, and the other end of the guide rib in the longitudinal direction may be spaced apart from the suction surface.

A turbine including a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk according to another aspect of the present invention, wherein the turbine blade is formed in a blade shape and has an airfoil having a suction surface and a pressure surface, the air A platform portion coupled to a lower portion of the foil, a root portion protruding downward from the platform portion and coupled to the rotor disk, the airfoil being connected to the suction surface and the pressure surface, and a tip plate facing the platform portion And a plurality of cooling ribs protruding from the tip plate, wherein the cooling rib includes a first side rib connected to the suction surface and a flow in a direction from the pressure surface toward the first side rib. It is formed between the pressure surface and the suction surface so as to guide, and includes a guide rib divided into a plurality.

Here, the guide rib may include a collision portion facing the pressure surface and a discharge portion bent obliquely toward the suction surface from the collision portion.

In addition, the air foil includes a leading edge and a trailing edge, and the guide rib disposed closest to the leading edge among the guide ribs is bent at the leading edge toward the suction surface and at the leading edge. It may include a collision portion facing the pressure surface and a discharge portion bent obliquely toward the suction surface from the collision portion.

In addition, a first upper cooling hole may be formed between the guide ribs in the tip plate, and a second upper cooling hole may be formed between the guide rib and the first side rib in the tip plate.

In addition, a plurality of side cooling holes and guide grooves may be formed on the pressure surface to guide air discharged from the side cooling holes to the tip plate by connecting the side cooling holes and the tip plate.

In addition, the cooling rib further includes a second side rib connected to the pressure surface, the guide rib is disposed between the first side rib and the second side rib, and a plurality of side openings in the second side rib Is formed, and the side opening may be connected to the induction groove.

In addition, the guide rib may extend from the pressure surface toward the suction surface and include two bent portions.

In addition, one end of the guide rib in the longitudinal direction may be connected to the pressure surface, and the other end of the guide rib in the longitudinal direction may be spaced apart from the suction surface.

According to an airfoil and a turbine according to an aspect of the present invention, a plurality of guide ribs spaced apart from the first side ribs may be provided, so that the cooling efficiency of the tip portion may be improved.

1 is a view 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 part of the gas turbine of FIG. 1.
3 is a perspective view showing a turbine blade according to a first embodiment of the present invention.
4 is a perspective view showing a part of a turbine blade according to a first embodiment of the present invention.
5 is a plan view of the turbine blade according to the first embodiment of the present invention.
6 is a perspective view showing a part of a turbine blade according to a second embodiment of the present invention.
7 is a top plan view of a turbine blade according to a second embodiment of the present invention.
8 is a perspective view showing a part of a turbine blade according to a third embodiment of the present invention.
9 is a top plan view of a turbine blade according to a third embodiment of the present invention.

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

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

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this case, it should be noted that in the accompanying drawings, the same components are indicated by the same reference numerals as possible. In addition, detailed descriptions of known functions and configurations that may obscure the subject matter of the present invention will be omitted. For the same reason, some components in the accompanying drawings 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 interior 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 the Brayton cycle. The Brayton cycle can consist of four processes leading to isentropic compression (thermal compression), static pressure rapid heating, isentropic expansion (thermal expansion), and static pressure heat dissipation. In other words, after inhaling atmospheric air and compressing it to high pressure, it burns fuel in a static pressure environment to release thermal energy, expands the high-temperature combustion gas and converts it into kinetic energy, and then releases exhaust gas containing residual energy into the atmosphere. I can. That is, the cycle can be performed in four processes of 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. Although the following description will refer to FIG. 1, the description of the present invention can be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine 1000 illustrated in FIG. 1 by way of example.

Referring to FIG. 1, a compressor 1100 of a gas turbine 1000 may 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 region requiring cooling in the gas turbine 1000. 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 are increased.

The compressor 1100 is designed as centrifugal compressors or axial compressors. While a centrifugal compressor is applied in a small gas turbine, a large gas turbine 1000 as shown in FIG. 1 is a large amount of air. It is common to apply the multi-stage axial compressor 1100 because it must be compressed. At this time, in the multi-stage axial compressor 1100, the blade 1130 of the compressor 1100 rotates according to the rotation of the center tie rod 1120 and the rotor disk, compressing the introduced air, and compressing the compressed air into the rear compressor vane ( 1140). As the air passes through the blades 1130 formed in multiple stages, it is compressed with more and more high pressure.

The compressor vane 1140 is mounted inside the housing 1150, and a plurality of compressor vanes 1140 may be mounted to form stages. The compressor vane 1140 guides the compressed air moved from the compressor blade 1130 at the front to the blade 1130 at the rear end. In one embodiment, at least some of the plurality of compressor vanes 1140 may be mounted so as to be rotatable within a predetermined range for adjusting 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 shaft of the compressor 1100 and the rotation shaft of the turbine 1300 may be directly connected by a torque tube 1170. In the case of the large gas turbine 1000, almost half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100.

On the other hand, the combustor 1200 may mix compressed air supplied from the outlet of the compressor 1100 with fuel and burn at an isostatic pressure to produce a high-energy combustion gas. In the combustor 1200, the introduced compressed air is mixed with fuel and combusted to produce high-energy high-temperature and 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 iso-rolling process. .

A number of combustors 1200 may be arranged in a housing formed in a cell shape, and a burner including a fuel injection nozzle, etc., a combustor liner forming a combustion chamber, and a connection portion between the combustor and the turbine It is configured to include a transition piece (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 and high-pressure combustion gas expands, impulses and reaction forces are applied to the turbine blades 1400 of the turbine 1300 to generate rotational torque, and the obtained rotational torque is passed through the torque tube 1170 and the compressor 1100. Power that is transmitted to and exceeds 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 and a plurality of turbine blades 1400 and vanes radially disposed on the rotor disk 1310. The rotor disk 1310 has a substantially disk shape, and a plurality of grooves are formed in its outer circumferential portion. The groove is formed to have a curved surface, and the turbine blade 1400 and vanes are inserted into the groove. The turbine blade 1400 may be coupled to the rotor disk 1310 in a manner such as a dovetail. The vane is fixed so as not to rotate and guides the flow direction of the combustion gas passing through the turbine blade 1400.

Figure 3 is a perspective view showing a turbine blade according to the first embodiment of the present invention, Figure 4 is a perspective view showing a part of the turbine blade according to the first embodiment of the present invention, Figure 5 is a first embodiment of the present invention This is a plan view of the turbine blade according to the embodiment.

Referring to Figures 3 to 5, the turbine blade 1400 is lower than the platform portion 1420 and the platform portion 1420 coupled to the lower portion of the airfoil 1410 and the airfoil 1410 in the shape of a wing. It includes a root portion 1425 protruding and coupled to the rotor disk. The airfoil 1410 may be formed of a curved surface plate in the shape of a wing, and may be formed to have an optimized airfoil shape according to the specifications of the gas turbine 1000.

The platform portion 1420 is positioned between the airfoil 1410 and the root portion 1425 and may be formed in a substantially square plate or square pillar shape. The platform unit 1420 serves to maintain a gap between the turbine blades 1400 by contacting the platform unit 1420 of the adjacent turbine blade 1400 and its side surfaces.

The root portion 1425 has an approximately fir-shaped bent portion, which is formed to correspond to the shape of the bent portion formed in the slot of the rotor disk 1310. Here, the coupling structure of the root portion 1425 does not necessarily have a fir shape, and may be formed to have a dovetail shape. Inlets for supplying cooling air may be formed at the lower end of the root portion 1425.

The airfoil 1410 may include a leading edge LE disposed on an upstream side and a trailing edge TE disposed on a downstream side based on the flow direction of the combustion gas. In addition, the airfoil 1410 has a convexly curved surface on the front surface of the airfoil 1410 and a protruding suction surface (S1), and a pressure surface that forms a curved surface concavely toward the suction surface on the rear surface of the airfoil. (S2) is formed. A pressure difference between the suction surface S1 and the pressure surface S2 of the air foil 1410 is generated, so that the turbine 1300 rotates.

A plurality of side cooling holes 1411 are formed on the side of the air foil 1410, and the side cooling holes 1411 communicate with a cooling passage formed inside the air foil 1410 to transfer cooling air to the air foil 1410. To the surface of the.

A plurality of cooling passages may be formed in the air foil 1410, and air as a refrigerant may be supplied to the cooling passages. Meanwhile, the airfoil 1410 is formed at an outer end in the radial direction and includes a tip plate 1430 facing the platform portion 1420 and a cooling rib CR1 protruding from the tip plate 1430.

The tip plate 1430 is disposed outside the radial reflection of the airfoil 1410 and is spaced apart from the shroud 1350 of the turbine 1300 at an interval. The tip plate 1430 is fixed to the sidewall of the airfoil 1410 to form a cooling space inside the sidewall. The tip plate 1430 has a shape corresponding to the cross section of the airfoil 1410.

The cooling rib (CR1) protrudes radially outward from the tip plate (1430) and is formed between the first side rib (1450) connected to the suction surface (S1) and the pressure surface (S2) and the suction surface (S1). It includes a guide rib 1460 divided into. The cooling rib CR1 serves to cool the tip portion by contact with the refrigerant. In the first embodiment, the cooling rib CR1 is not formed above the pressure surface S2, and the upper space of the pressure surface S2 is laterally opened.

The first side rib 1450 may be formed by connecting from the leading edge LE to the trailing edge TE, but the present invention is not limited thereto, and between the leading edge LE and the trailing edge TE. Can be formed. The first side rib 1450 protrudes upward from the suction surface S1, is formed in parallel with the suction surface S1, and is curved in an approximately arc shape.

A plurality of guide ribs 1460 are formed on the tip plate 1430, and the guide ribs 1460 guide the flow in a direction from the pressure surface S2 toward the first side rib 1450. The refrigerant guided by the guide ribs 1460 impacts the first side rib 1450 to cool the first side rib 1450 and then exits in the direction of the trailing edge TE.

The guide rib 1460 may include a first guide rib 1461, a second guide rib 1462, a third guide rib 1463, and a fourth guide rib 1464. Among the guide ribs 1460, the first guide rib 1461 arranged closest to the leading edge LE is a leading edge LE and a leading end 1461a and a leading end 1461a extending from the leading edge LE toward the suction surface S1. ), and a collision part 1461b facing the pressure surface S2 and a discharge part 1461c bent obliquely toward the suction surface S1 from the collision part 1461b.

The tip portion 1461a may be formed to be obliquely connected from the leading edge LE to the suction surface S1 with respect to the center line in the width direction of the tip plate 1430. The collision portion 1461b may be formed to face the pressure surface S2 by bending in a direction from the tip portion 1461a toward the trailing edge TE. In addition, the discharge part 1461c is bent obliquely in the direction from the collision part 1461b toward the suction surface S1, and accordingly, the discharge part 1461c is inclined toward the suction surface S1 with respect to the center line CL. Is formed.

The front end 1461a not only guides the refrigerant to move between the guide ribs 1460, but also discharges heat transferred from the pressure surface S2 by contact with the refrigerant. The collision part 1461b performs cooling by colliding with the refrigerant moving along the front end 1461a, and changes the traveling direction of the refrigerant. The discharge part 1461c guides the refrigerant moved from the collision part 1461b toward the first side rib 1450.

Meanwhile, the second guide rib 1462 disposed adjacent to the first guide rib 1461 is inclined toward the suction surface S1 from the collision part 1462b and the collision part 1462b facing the pressure surface S2. It includes a curved discharge portion 1462c. The collision part 1462b moves the refrigerant from the leading edge LE to the trailing edge TE, and discharges heat from the pressure surface S2. The discharge unit 1462c performs cooling while guiding the refrigerant toward the first side rib 1450. The third guide rib 1463 is disposed between the second guide rib 1462 and the fourth guide rib 1464 and has the same structure as the second guide rib 1462.

The fourth guide rib 1464 is disposed closest to the trailing edge TE and is formed to be connected along the center line CL in the width direction of the tip plate 1430 so that the refrigerant is formed in the direction toward the trailing edge TE. Guide them out.

Meanwhile, the tip plate 1430 includes a first upper cooling hole 1412 formed between the guide ribs 1460 and a second upper cooling hole 1413 formed between the guide rib 1460 and the first side rib 1450. Is formed. The first upper cooling hole 1412 and the second upper cooling hole 1413 communicate with a cooling passage formed inside the airfoil 1410 to inject air as a refrigerant onto the tip plate 1430. The refrigerant injected through the first upper cooling hole 1412 moves along the guide ribs 1460, and the air injected through the second upper cooling hole 1413 moves along the first side rib 1450. .

In addition, a plurality of side cooling holes 1411 are formed on the pressure surface S2, and the side cooling hole 1411 located at the top of the side cooling holes 1411 collects air discharged from the side cooling hole 1411. It is connected to the guide groove 1415 leading to the tip plate 1430. The guide groove 1415 is curved on the pressure surface S2, and is formed by extending from the side cooling hole 1411 to the tip plate 1430. When the induction groove 1415 is formed as described above, the refrigerant discharged from the side cooling hole 1411 is guided to the tip plate 1430, thereby cooling the tip plate 1430 more efficiently.

As described above, when a plurality of guide ribs 1460 spaced apart from the first side ribs 1450 are formed on the tip plate 1430, the cooling ribs CR1 formed on the tip plate 1430 do not interfere with the flow. Still, it is possible to efficiently cool the tip portion of the turbine blade 1400.

Hereinafter, a turbine blade according to a second embodiment of the present invention will be described. 6 is a perspective view showing a part of a turbine blade according to a second embodiment of the present invention, and FIG. 7 is a plan view of the turbine blade according to the second embodiment of the present invention as viewed from above.

6 and 7, the turbine blade 2400 according to the second embodiment has the same structure as the turbine blade according to the first embodiment, except for the cooling rib CR2. Duplicate description of the configuration will be omitted.

A plurality of cooling passages may be formed in the air foil 2410, and air as a refrigerant may be supplied to the cooling passages. Meanwhile, the airfoil 2410 includes a tip plate 2430 facing the platform portion and a cooling rib CR2 protruding from the tip plate 2430 by being formed at an outer end in the radial direction.

The tip plate 2430 is disposed outside the radial echo of the airfoil 2410, and is spaced apart from the shroud of the turbine at intervals. The tip plate 2430 is fixed to the sidewall of the airfoil 2410 to form a cooling space inside the sidewall. The tip plate 2430 has a shape corresponding to the cross section of the airfoil 2410.

The cooling rib CR2 protrudes radially outward from the tip plate 2430 and is formed between the first side rib 2450 connected to the suction surface S1 and the pressure surface S2 and the suction surface S1. It includes a guide rib 2460 divided into. The cooling rib CR2 serves to cool the tip portion by contact with the refrigerant.

The first side rib 2450 may be formed by connecting from the leading edge LE to the trailing edge TE, but the present invention is not limited thereto, and between the leading edge LE and the trailing edge TE Can be formed. The first side rib 2450 protrudes upward from the suction surface S1 and is approximately curved in an arc shape.

A plurality of guide ribs 2460 are formed on the tip plate 2430, and the guide rib 2460 guides the flow in a direction from the pressure surface S2 toward the first side rib 2450, and is attached to the guide rib 2460. The refrigerant guided by this impacts the first side rib 2450 to cool the first side rib 2450 and then exits in the direction toward the trailing edge TE.

The guide rib 2460 may include a first guide rib 2461, a second guide rib 2462, and a third guide rib 2463. The first guide rib 2461 is disposed closest to the leading edge LE, and is bent at the front end 2461a and the front end 2461a extending from the pressure surface S2 toward the suction surface S1 to It includes a collision portion 2461b facing (S2) and a discharge portion 2461c bent obliquely toward the suction surface S1 from the collision portion 2461b.

The distal end 2461a is connected to the upper end of the pressure surface S2, and may be formed by being obliquely connected in a direction toward the suction surface S1 at an edge where the upper end of the pressure surface S2 and the tip plate 2430 are connected. The tip portion 2461a may be formed to be inclined with respect to the center line CL in the width direction of the tip plate 2430 in a direction toward the trailing edge TE.

The collision part 2461b may be bent in a direction from the tip part 2461a toward the trailing edge TE and may be formed to be inclined with respect to the tip part 2461a. The discharge part 2461c is bent obliquely with respect to the collision part 2461b in the direction from the collision part 2461b toward the suction surface S1. One end of the first guide rib 2461 in the longitudinal direction is connected to the pressure surface S2, and the other end in the longitudinal direction is spaced apart from the suction surface S1.

In this way, when the front end 2461a is formed to extend to the upper end of the pressure surface S2, heat from the pressure surface S2 can be discharged more efficiently. The second guide rib 2462 is disposed between the first guide rib 2461 and the third guide rib 2463 and has the same structure as the first guide rib 2461.

The third guide rib 2463 is disposed closest to the trailing edge TE, and is bent at the tip portion 2463a and the tip portion 2463a extending from the pressure surface S2 toward the suction surface S1 to form a pressure surface. It includes a collision part 2463b facing (S2).

The tip portion 2463a is connected to the upper end of the pressure surface S2, and may be formed by being obliquely connected in a direction toward the suction surface S1 at an edge where the upper end of the pressure surface S2 and the tip plate 2430 are connected. The collision part 2463b may be bent in a direction from the tip part 2463a toward the trailing edge TE and may be formed to be inclined with respect to the tip part 2463a. The collision part 2463b may be disposed parallel to the center line of the tip plate 2430.

The third guide rib 2463 not only guides the refrigerant introduced between the second guide rib 2462 and the third guide rib 2463 to the trailing edge TE, but also flows into the front of the third guide rib 2463 The resulting air is guided to the trailing edge (TE).

The tip plate 2430 includes a first upper cooling hole 2412 formed between the guide ribs 2460 and a second upper cooling hole 2413 formed between the guide rib 2460 and the first side rib 2450 . The first upper cooling hole 2412 and the second upper cooling hole 2413 communicate with a cooling passage formed in the airfoil 2410 to inject air as a refrigerant onto the tip plate 2430. The refrigerant injected through the first upper cooling hole 2412 moves along the guide ribs 2460, and the air injected through the second upper cooling hole 2413 moves along the first side rib 2450. .

In addition, the side cooling hole 2411 positioned at the top of the side cooling holes 2411 formed on the pressure surface S2 is an induction groove that guides the air discharged from the side cooling hole 2411 to the tip plate 2430. 2415). The guide groove 2415 is curved on the pressure surface S2, and is formed by extending from the side cooling hole 2411 to the tip plate 2430.

As described above, according to the second embodiment, the cooling rib CR2 is connected to the upper end of the pressure surface S2 to efficiently cool the pressure surface S2, and the third guide rib 2463 is Since the front end portion 2463a and the collision portion 2463b are included, the trailing edge TE can be cooled more efficiently.

Hereinafter, a turbine blade according to a third embodiment of the present invention will be described. 8 is a perspective view showing a part of a turbine blade according to a third embodiment of the present invention, and FIG. 9 is a plan view of the turbine blade according to the third embodiment of the present invention as viewed from above.

8 and 9, the turbine blade 3400 according to the third exemplary embodiment has the same structure as the turbine blade according to the first exemplary embodiment except for the cooling rib CR3. Duplicate description of the configuration will be omitted.

A plurality of cooling passages may be formed inside the air foil 3410, and air as a refrigerant may be supplied to the cooling passages. Meanwhile, the airfoil 3410 includes a tip plate 3430 facing the platform portion at an outer end in the radial direction and a cooling rib CR3 protruding from the tip plate 3430.

The tip plate 3430 is disposed outside the radial reflection of the airfoil 3410 and is spaced apart from the shroud of the turbine. The tip plate 3430 is fixed to the sidewall of the airfoil 3410 to form a cooling space inside the sidewall. The tip plate 3430 has a shape corresponding to the cross section of the airfoil 3410.

The cooling rib (CR3) protrudes radially outward from the tip plate (3430), the first side rib (3450) connected to the suction surface (S1) and the second side rib (3470) connected to the pressure surface (S2) and pressure It is formed between the surface (S2) and the suction surface (S1) and includes a guide rib (3460) divided into a plurality. The cooling rib CR3 serves to cool the tip portion by contact with the refrigerant.

The first side rib 3450 protrudes upward from the suction surface S1 and is formed between the leading edge LE and the trailing edge TE. The first side rib 3450 is connected to the suction surface S1 and is curved in an approximately arc shape.

Meanwhile, the second side rib 3470 protrudes upward from the pressure surface S2 and is formed between the leading edge LE and the trailing edge TE. The second side rib 3470 protrudes upward from the pressure surface S2 and is formed to be curved in an approximately arc shape. A plurality of side openings 3471 are formed in the second side ribs 3470, and the side openings 3471 are connected to a guide groove 3415 to be described later.

The second side rib 3470 faces the first side rib 3450, and its front and rear ends are spaced apart from the first side rib 3450. Accordingly, between the second side rib 3470 and the first side rib 3450, an inlet opening 381 and an outlet opening 3482 may be formed. The inlet opening 381 is positioned on the leading edge LE, and the outlet opening 3482 is positioned on the trailing edge TE. The air introduced through the inlet opening 3461 may cool the guide rib 3460 and then exit through the discharge opening 3482.

A guide rib 3460 is formed on the tip plate 3430, and the guide rib 3460 is positioned between the first side rib 3450 and the second side rib 3470. The guide rib 3460 may include a first guide rib 3461, a second guide rib 3462, and a third guide rib 3463. The first guide rib 3461 is disposed closest to the leading edge LE, and is bent at the tip portion 3461a and the tip portion 3461a extending from the pressure surface S2 toward the suction surface S1 to provide a pressure surface. It includes a collision portion 3461b facing (S2) and a discharge portion 3461c bent obliquely toward the suction surface S1 from the collision portion 3461b.

The tip portion 3461a may be formed to be inclined with respect to the center line in the width direction of the tip plate 3430 in a direction toward the trailing edge TE. The collision part 3461b may be formed to be bent in a direction from the tip part 3461a toward the trailing edge TE to be inclined with respect to the tip part 3461a, and the collision part 3461b is the center line in the width direction of the tip plate 3430 It can be located on the top. The discharge part 3461c may be bent in a direction from the collision part 3461b toward the suction surface S1, but may be formed to be inclined toward the trailing edge TE than the tip part 3461a. The second guide rib 3462 is disposed between the first guide rib 3461 and the third guide rib 3463 and has the same structure as the first guide rib 3461.

The third guide rib (3463) is disposed closest to the trailing edge (TE) and is bent at the tip portion (3463a) and the tip portion (3463a) extending from the pressure surface (S2) toward the suction surface (S1) to A collision part 3463b connected in a direction facing (S1) may be included, and the collision part 3463b may be located on the center line CL of the tip plate 3430.

The tip plate 3430 includes a first upper cooling hole 3412 formed between the guide ribs 3460 and a second upper cooling hole 3413 formed between the guide rib 3460 and the first side rib 3450. . The first upper cooling hole 3412 and the second upper cooling hole 3413 communicate with a cooling passage formed inside the airfoil 3410 to inject air as a refrigerant onto the tip plate 3430

In addition, the side cooling hole 3411 positioned at the top of the side cooling holes 3411 is connected to an induction groove 3415 for guiding the air discharged from the side cooling hole 3411 to the tip plate 3430. The guide groove 3415 is curved on the pressure surface S2, and is formed by extending from the side cooling hole 3411 to the tip plate 3430. The guide groove 3415 is connected to the side opening 3471, so that the refrigerant discharged from the side cooling hole 3411 may move to the tip plate 3430.

As described above, according to the third exemplary embodiment, the first side rib 3450, the second side rib 3470, and the guide rib 3460 are formed, so that the cooling efficiency of the tip plate 3430 may be improved. In addition, the induction groove 3415 and the side opening 3471 are connected to guide the refrigerant in the side cooling hole 3411 to the tip plate 3430, thereby further improving the cooling efficiency of the tip plate 3430.

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

1000: gas turbine
1100: compressor
1130: compressor blade
1140: Bane
1150: housing
1170: torque tube
1200: combustor
1300: turbine
1310: rotor disk
1400: turbine blade
1410, 2410, 3410: airfoil
1411, 2411, 3411: side cooling hole
1412, 2412, 3412: first upper cooling hole
1413, 2413, 3413: second upper cooling hole
1415, 2415, 3415: induction groove
1420: platform part
1425: root part
1430, 2430, 3430: tip plate
1450, 2450, 3450: first side rib
1460, 2460, 3460: guide rib
1461, 2461, 3461: first guide rib
1462, 2462, 3462: second guide rib
1463, 2463, 3463: 3rd guide rib
1464: fourth guide rib
3470: second side rib
3481: inlet opening
3482: discharge opening
CR1 CR2, CR3: cooling rib
LE: leading edge
TE: Trailing Edge
S1: suction side
S2: pressure side

Claims (20)

An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
The guide rib is a turbine blade comprising a collision portion facing the pressure surface and a discharge portion bent obliquely toward the suction surface from the collision portion. An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
The guide rib is formed to guide the flow in a direction from the pressure surface toward the first side rib, and the upper space of the pressure surface is laterally opened. delete An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
Among the guide ribs, a guide rib disposed closest to the leading edge is a front end extending from the leading edge in a direction toward the suction surface and bent at the tip to face the pressure surface and the collision part facing the pressure surface and the suction at the collision part. Turbine blade comprising a discharge portion bent obliquely toward the surface. The method of claim 4,
Among the guide ribs, a guide rib disposed closest to the trailing edge is formed by being connected along a center line in the width direction of the tip plate. An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
A turbine blade having a first upper cooling hole formed between the guide ribs in the tip plate, and a second upper cooling hole formed between the guide rib and the first side rib in the tip plate. The method of claim 1,
A turbine blade having a plurality of side cooling holes on the pressure surface and an induction groove connecting the side cooling hole and the tip plate to guide the air discharged from the side cooling hole to the tip plate. The method of claim 7,
The cooling rib further includes a second side rib connected to the pressure surface, and the guide rib is a turbine blade disposed between the first side rib and the second side rib. The method of claim 8,
A turbine blade having a plurality of side openings connected to the guide grooves in the second side ribs. An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
In the pressure surface, a plurality of side cooling holes, and guide grooves for connecting the side cooling holes and the tip plate to guide air discharged from the side cooling holes to the tip plate, are formed,
The cooling rib further includes a second side rib connected to the pressure surface, and the guide rib is disposed between the first side rib and the second side rib,
A turbine blade having an inlet opening positioned on a leading edge and an outlet opening positioned on the trailing edge between the first side rib and the second side rib. An airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, and a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil,
A tip plate connected to the suction surface and the pressure surface and disposed outside facing the platform part,
Including a plurality of cooling ribs (cooling ribs) protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface and
It includes a plurality of guide ribs separated in a direction from the leading edge toward the trailing edge and connected from the pressure surface toward the suction surface,
The guide rib extends from the pressure surface toward the suction surface, and the turbine blade has two bent portions. The method of claim 11,
One end of the guide rib in the longitudinal direction is connected to the pressure surface, and the other end of the guide rib in the longitudinal direction is spaced apart from the suction surface. A turbine comprising a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk,
The turbine blade includes an airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil is connected to the suction surface and the pressure surface, and includes a tip plate facing the platform portion and a plurality of cooling ribs protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface,
A guide rib formed between the pressure surface and the suction surface and divided into a plurality of guide ribs so as to guide the flow from the pressure surface toward the first side rib,
The guide rib is a turbine comprising a collision portion facing the pressure surface and a discharge portion bent obliquely toward the suction surface from the collision portion. delete A turbine comprising a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk,
The turbine blade includes an airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil is connected to the suction surface and the pressure surface, and includes a tip plate facing the platform portion and a plurality of cooling ribs protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface,
A guide rib formed between the pressure surface and the suction surface and divided into a plurality of guide ribs so as to guide the flow from the pressure surface toward the first side rib,
The air foil includes a leading edge and a trailing edge,
Among the guide ribs, a guide rib disposed closest to the leading edge is a front end extending from the leading edge in a direction toward the suction surface and bent at the tip to face the pressure surface and the collision part facing the pressure surface and the suction at the collision part. Turbine comprising a discharge portion bent inclined toward the surface. A turbine comprising a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk,
The turbine blade includes an airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil is connected to the suction surface and the pressure surface, and includes a tip plate facing the platform portion and a plurality of cooling ribs protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface,
A guide rib formed between the pressure surface and the suction surface and divided into a plurality of guide ribs so as to guide the flow from the pressure surface toward the first side rib,
A turbine having a first upper cooling hole formed between the guide ribs in the tip plate, and a second upper cooling hole formed between the guide rib and the first side rib in the tip plate. The method of claim 13,
A turbine having a plurality of side cooling holes on the pressure surface and an induction groove connecting the side cooling hole and the tip plate to guide air discharged from the side cooling hole to the tip plate. The method of claim 17,
The cooling rib further includes a second side rib connected to the pressure surface, and the guide rib is disposed between the first side rib and the second side rib,
A plurality of side openings are formed in the second side ribs, and the side openings are connected to the guide grooves. A turbine comprising a rotatable rotor disk and a plurality of turbine blades installed on the rotor disk,
The turbine blade includes an airfoil formed in a wing shape and having a suction surface and a pressure surface, a platform portion coupled to a lower portion of the airfoil, a root portion protruding downward from the platform portion and coupled to the rotor disk,
The airfoil is connected to the suction surface and the pressure surface, and includes a tip plate facing the platform portion and a plurality of cooling ribs protruding from the tip plate,
The cooling rib,
A first side rib connected to the suction surface,
A guide rib formed between the pressure surface and the suction surface and divided into a plurality of guide ribs so as to guide the flow from the pressure surface toward the first side rib,
The guide rib extends from the pressure surface toward the suction surface, and has two bent portions. The method of claim 19,
One end of the guide rib in the longitudinal direction is connected to the pressure surface, and the other end of the guide rib in the longitudinal direction is spaced apart from the suction surface.

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