Pin-fin cooling structure for turbine component and gas turbine including the same

Abstract

To provide a pin-fin cooling structure for a turbine component that exhibits excellent heat transfer performance by forming the plurality of pin-fin cooling structures in a cooling flow passage cavity formed inside the turbine component, and a gas turbine including the pin-fin cooling structure.SOLUTION: In an air foil for a turbine blade or a turbine vane, the air foil includes: a cooling flow passage cavity formed at an inner rear edge part of the air foil; and a plurality of pin-fin cooling structures formed to come into contact with one side surface and the other side surface of the cooling flow passage cavity. The pin-fin cooling structure includes: a cooling pin coupled to one side surface and the other side surface of the cooling flow passage cavity; and a pair of guide pins formed on both sides of the cooling pin to surround the cooling pin while leaving a predetermined distance.SELECTED DRAWING: Figure 5

Description

Technical Field

[0001] The present invention relates to a pin-fin cooling structure for turbine components and a gas turbine including the same.

Background Art

[0002] A turbine is a mechanical device that obtains rotational force by impulse force or reaction force using the flow of a compressible fluid such as steam or gas, and includes a steam turbine using steam and a gas turbine using high-temperature combustion gas.

[0003] Among these, a gas turbine is mainly composed of a compressor, a combustor, and a turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged in a compressor housing.

[0004] The combustor supplies fuel to the compressed air compressed by the compressor and ignites it with a burner, thereby generating high-temperature and high-pressure combustion gas.

[0005] The turbine has a plurality of turbine vanes and turbine blades alternately arranged in a turbine housing. Also, a rotor is arranged so as to penetrate the centers of the compressor, the combustor, the turbine, and the exhaust chamber.

[0006] Both ends of the rotor are rotatably supported by bearings. A plurality of disks are fixed to the rotor, and at the same time, respective blades are connected, and a drive shaft such as a generator is connected to an end on the exhaust chamber side.

[0007] Such a gas turbine does not have a reciprocating mechanism such as a piston of a four-stroke engine, so there are no mutually rubbing parts such as a piston-cylinder, the consumption of lubricating oil is extremely small, the amplitude, which is a characteristic of a reciprocating machine, is greatly reduced, and there is an advantage that high-speed movement is possible.

[0008] Briefly explaining the operation of a gas turbine, high-temperature combustion gas is produced by mixing and burning the air compressed by a compressor with fuel, and the combustion gas thus produced is injected onto the turbine side. The injected combustion gas generates a rotational force while passing through the turbine vanes and turbine blades, thereby rotating the rotor.

Summary of the Invention

Problems to be Solved by the Invention

[0009] An object of the present invention is to provide a pin-fin cooling structure for a turbine component that exhibits excellent heat transfer performance by forming a plurality of pin-fin cooling structures in a cooling flow path cavity formed inside the turbine component, and a gas turbine including the same.

Means for Solving the Problems

[0010] To achieve the above object, the airfoil of the present invention includes, in the airfoil of a turbine blade or a turbine vane, a cooling flow path cavity formed at the inner trailing edge portion of the airfoil, and a plurality of pin-fin cooling structures formed so as to be in contact with one side surface and the other side surface of the cooling flow path cavity. The pin-fin cooling structure includes cooling pins connected to one side surface and the other side surface of the cooling flow path cavity, and a pair of guide pins formed at a predetermined distance from both sides of the cooling pins and surrounding the cooling pins.

[0011] In the first embodiment of the present invention, the cooling pins may be formed in a cylindrical shape, and the guide pins may be formed in an arc-shaped rib shape arranged within a predetermined angular range from the center of the cylinder.

[0012] The guide pins may be formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pins, and the lower guide pin may be in contact with one side surface of the cooling flow path cavity, and the upper guide pin may be arranged to be in contact with the other side surface of the cooling flow path cavity.

[0013] The pair of guide pins may be arranged at an angle (a) of 80 to 100 degrees from the center of the cylinder from the upstream end to the downstream end.

[0014] The pair of guide pins may be arranged such that the angle (2b) between the upstream end portions of the cooling flow path is larger than the angle (2c) between the downstream end portions.

[0015] The guide pins may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pins.

[0016] In the second embodiment of the present invention, the cooling pins are formed in a cylindrical shape, and the guide pins are perpendicular to the air flow direction and are formed in an arc-shaped rib shape arranged within a predetermined angle range in the downstream direction from a plane passing through the center of the cylinder.

[0017] The angle (a) at which the guide pins are arranged in the downstream direction from a plane passing through the center of the cylinder may be 50 to 65 degrees.

[0018] The guide pins may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pins is 1.0 to 2.0 times the diameter (D) of the cooling pins.

[0019] The guide pins may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pins.

[0020] In the third embodiment of the present invention, the cooling pins are formed in a cylindrical shape, and the guide pins include a curved surface rib portion formed in an arc-shaped rib shape arranged within a predetermined angle range in the downstream direction from a plane passing through the center of the cylinder and perpendicular to the air flow direction, and a downstream extension portion bent and extended in the opposite direction from an inflection point downstream of the curved surface rib portion.

[0021] The curved surface rib portion may be arranged at an angle (a) of 50 to 65 degrees from a plane passing through the center of the cylinder to an inflection point downstream.

[0022] The guide pin may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pin is 1.0 to 2.0 times the diameter (D) of the cooling pin.

[0023] The guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0024] In the fourth embodiment of the present invention, the cooling pin is formed in a cylindrical shape, the guide pin is perpendicular to the air flow direction, and includes a curved surface rib portion formed in an arc-shaped rib shape arranged within a predetermined angular range in the downstream direction from a plane passing through the center of the cylinder, an upstream extension portion extending at a predetermined angle from the upstream end portion of the curved surface rib portion, and a downstream extension portion bent and extended in the opposite direction from the inflection point downstream of the curved surface rib portion.

[0025] The curved surface rib portion may be arranged such that the angle (a) from the plane passing through the center of the cylinder to the inflection point downstream is 50 to 65 degrees.

[0026] The upstream extension portion may be arranged at 20 to 40 degrees in the upstream direction from the plane passing through the center of the cylinder.

[0027] The guide pin may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pin is 1.0 to 2.0 times the diameter (D) of the cooling pin.

[0028] The guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0029] The turbine vane of the present invention is a turbine vane including an airfoil, an inner end wall formed radially inside the airfoil, and an outer end wall formed radially outside the airfoil. The turbine vane includes end wall cavities respectively formed inside the inner end wall and the outer end wall, and a plurality of pin-fin cooling structures formed to be in contact with one side surface and the other side surface of the end wall cavity. The pin-fin cooling structure includes cooling pins connected to one side surface and the other side surface of the end wall cavity, and a pair of guide pins formed at a predetermined distance on both sides of the cooling pins and surrounding the cooling pins.

[0030] The cooling pins may be formed in a cylindrical shape, and the guide pins may be formed in an arc-shaped rib shape arranged within a predetermined angular range from the center of the cylinder.

[0031] The gas turbine of the present invention includes a compressor that sucks in and compresses external air, a combustor that mixes fuel with the air compressed by the compressor and burns the mixture, and a turbine in which turbine blades and turbine vanes are mounted inside a turbine casing, and the turbine blades are rotated by combustion gas discharged from the combustor. In the gas turbine, the airfoils of the turbine blades and turbine vanes include a cooling flow path cavity formed at the inner trailing edge portion of the airfoil, and a plurality of pin-fin cooling structures formed to be in contact with one side surface and the other side surface of the cooling flow path cavity. The pin-fin cooling structure includes cooling pins connected to one side surface and the other side surface of the cooling flow path cavity, and a pair of guide pins formed at a predetermined distance on both sides of the cooling pins and surrounding the cooling pins.

[0032] The cooling pins may be formed in a cylindrical shape, and the guide pins may be formed in an arc-shaped rib shape arranged within a predetermined angular range from the center of the cylinder.

Advantages of the Invention

[0033] According to the pin-fin cooling structure of the turbine component of the present invention described above and the gas turbine including the same, by forming a guide pin structure around the circular cooling pins, the wake region and the separation zone in the downstream of the cooling pins are removed, the flow of air is guided to reduce the secondary flow region, and the flow velocity is increased by the guide pin structure to improve the heat transfer performance in the downstream of the cooling pins.

Brief Description of the Drawings

[0034]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7A

Figure 7B

Figure 8A

Figure 8B

Figure 9A

Figure 9B

Figure 10A

Figure 10B

Figure 11A

Figure 11B

Figure 11C

Figure 12A

Figure 12B

Figure 12C

Figure 12D

Figure 13

Embodiments for Carrying Out the Invention

[0035] The present invention can have various examples with various transformations added, but specific examples are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and it should be understood that all transformations, equivalents, or alternatives included in the spirit and technical scope of the present invention are included.

[0036] The terms used in the present invention are merely 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 "comprising" or "having" are intended to specify the presence of the features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, and it should be understood that the presence or addition of one or more other features, numbers, steps, operations, components, parts, or combinations thereof is not precluded in advance.

[0037] Hereinafter, with reference to the accompanying drawings, preferred embodiments of the present invention will be described in detail. At this time, note that in the accompanying drawings, the same components are represented by the same reference numerals as much as possible. Also, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention are omitted. For the same reason, in the accompanying drawings, some components are exaggerated, omitted, or shown schematically.

[0038] FIG. 1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention, and FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.

[0039] As shown in FIG. 1, a gas turbine 1000 according to an embodiment of the present invention includes a compressor 1100, a combustor 1200, and a turbine 1300. The compressor 1100 includes a plurality of blades 1110 provided radially. The compressor 1100 rotates the blades 1110, and air moves while being compressed by the rotation of the blades 1110. The size and installation angle of the blades 1110 can be changed according to the installation position. In one embodiment, the compressor 1100 is directly or indirectly connected to the turbine 1300 and can receive a part of the power generated by the turbine 1300 and use it for the rotation of the blades 1110.

[0040] The air compressed by the compressor 1100 moves to the combustor 1200. The combustor 1200 includes a plurality of combustion chambers 1210 arranged in an annular shape and a fuel nozzle module 1220.

[0041] As shown in FIG. 2, the gas turbine 1000 according to an embodiment of the present invention includes a housing 1010, and a diffuser 1400 through which the combustion gas that has passed through the turbine is discharged is provided on the rear side of the housing 1010. And a combustor 1200 that receives and burns the compressed air is disposed on the front side of the diffuser 1400.

[0042] Explaining with reference to the air flow direction, the compressor section 1100 is located on the upstream side of the housing 1010, and the turbine section 1300 is disposed on the downstream side. And between the compressor section 1100 and the turbine section 1300, a torque tube unit 1500 as a torque transmission member that transmits the rotational torque generated in the turbine section 1300 to the compressor section 1100 is disposed.

[0043] The compressor section 1100 is provided with a plurality (for example, 14) of compressor rotor disks 1120, and each of the compressor rotor disks 1120 is fastened by tie rods 1600 so as not to be axially separated.

[0044] Specifically, each of the compressor rotor disks 1120 is aligned along the axial direction with the tie rod 1600 constituting the rotating shaft passing through substantially the center. Here, each of the adjacent compressor rotor disks 1120 has opposing surfaces pressed by the tie rod 1600 so that relative rotation is impossible.

[0045] A plurality of blades 1110 are radially coupled to the outer peripheral surface of the compressor rotor disk 1120. Each blade 1110 includes a double-tail portion 1112 and is fastened to the compressor rotor disk 1120.

[0046] Between each of the rotor disks 1120, there is a vane (not shown) fixedly disposed in the housing. The vane is fixed so as not to rotate differently from the rotor disk, and serves to align the flow of compressed air passing through the blades of the compressor rotor disk and guide the air to the blades of the rotor disk located on the downstream side.

[0047] The fastening method of the dovetail portion 1112 includes a tangential type and an axial type. This can be selected according to the required structure of a commercial gas turbine and can have a commonly known dovetail or Fir-tree shape. In some cases, the blade can be fastened to the rotor disk using other fastening devices other than the above forms, such as fixtures like keys or bolts.

[0048] The tie rod 1600 is disposed so as to penetrate the central portions of the plurality of compressor rotor disks 1120 and turbine rotor disks 1320, and the tie rod 1600 may be composed of one or more tie rods. One end portion of the tie rod 1600 is fastened within the compressor rotor disk located on the most upstream side, and the other end portion of the tie rod 1600 is fastened by a fixing nut 1450.

[0049] The form of the tie rod 1600 can have various structures depending on the gas turbine, and thus is not necessarily limited to the form presented in FIG. 2. That is, as shown in the figure, it may have a form in which one tie rod penetrates the central portion of the rotor disk, may have a form in which a plurality of tie rods are arranged on the circumference, or a combination of these is also possible.

[0050] Although not shown, in the compressor of the gas turbine, vanes that serve as guide vanes may be provided at the next position of the diffuser in order to adjust the flow angle of the fluid entering the inlet of the combustor to the designed flow angle after increasing the pressure of the fluid. This is called a deswirler.

[0051] In the combustor 1200, the inflowing compressed air is mixed with fuel and burned to produce high-energy high-temperature and high-pressure combustion gas, and the temperature of the combustion gas is increased to the heat-resistant limit that the combustor and turbine components can withstand in the isobaric combustion process.

[0052] The combustor that constitutes the combustion system of the gas turbine may be arranged in a plurality in a housing formed in a cell shape, and includes a burner including a fuel injection nozzle and the like, a combustor liner that forms a combustion chamber, and a transition piece that serves as a connecting portion between the combustor and the turbine.

[0053] Specifically, the liner provides a combustion space where the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and burned. Such a liner may include a flame tube that provides a combustion space where the fuel mixed with air is burned, and a flow sleeve that forms an annular space while surrounding the flame tube. Further, a fuel nozzle is coupled to the front end of the liner, and an ignition plug is coupled to the side wall.

[0054] On the other hand, at the rear end of the liner, a transition piece is connected so that the combustion gas burned by the ignition plug can be sent to the turbine side. Such a transition piece has its outer wall portion cooled by the compressed air supplied from the compressor so as to prevent damage due to the high temperature of the combustion gas.

[0055] For this purpose, the transition piece is provided with holes for cooling so that air can be injected therein, and the compressed air cools the body inside through the holes and then flows to the liner side.

[0056] In the annular space of the liner, the cooling air that cools the aforementioned transition piece flows, and on the outer wall of the liner, compressed air is provided as cooling air through cooling holes provided in the flow sleeve outside the flow sleeve and can collide with it.

[0057] On the other hand, the high-temperature and high-pressure combustion gas discharged from the combustor is supplied to the aforementioned turbine 1300. The supplied high-temperature and high-pressure combustion gas collides with the rotating blades of the turbine while expanding, giving a reaction force to generate a rotational torque, and the rotational torque thus obtained is transmitted to the compressor through the aforementioned torque tube. The power exceeding the power required to drive the compressor is used to drive a generator or the like.

[0058] The turbine 1300 is basically similar in structure to the compressor. That is, the turbine 1300 is also provided with a plurality of turbine rotor disks 1320 similar to the compressor rotor disk of the compressor. Therefore, the turbine rotor disk 1320 also includes a plurality of turbine blades 1340 arranged radially. The turbine blades 1340 can also be coupled to the turbine rotor disk 1320 by a method such as a double tail. At the same time, between the blades 1340 of the turbine rotor disk 1320, turbine vanes 1330 fixed to the housing are provided to guide the flow direction of the combustion gas passing through the blades.

[0059] FIG. 3 is a perspective view showing a turbine blade according to an embodiment of the present invention. In FIG. 3, different from FIG. 2, the drawing number "100" is displayed on the turbine blade.

[0060] The turbine blade 100 includes an airfoil 110 that rotates by the pressure of combustion gas at the upper part, a platform part 120 integrally formed at the lower part of the airfoil, and a root part 130 integrally formed at the lower part of the platform part and coupled to the turbine rotor disk 1320. An inlet through which cooling fluid is supplied to an internal flow path formed inside the airfoil 110 may be formed inside the platform part 120.

[0061] The airfoil 110 includes a suction surface 112 formed to bulge outward on one side surface into which combustion gas flows, and a pressure surface 111 formed to be concave on the opposite side of the suction surface. The front side angle where the pressure surface 111 and the suction surface 112 meet constitutes a leading edge 113, and the rear side angle forms a trailing edge 114. An internal flow path (not shown) through which cooling air flowing in through the inlet flows may be formed inside the airfoil 110.

[0062] The platform part 120 serves to maintain the interval between blades by having the platform parts 120 of adjacent turbine blades and their side surfaces in contact with each other.

[0063] The root part 130 can have an axial - type form that is inserted along the axial direction of the turbine rotor disk into a coupling slot formed on the outer peripheral surface of the turbine rotor disk 1320. The root part 130 has a substantially double - tail shape or a bent part in the shape of a fir tree, and this may be formed to correspond to the form of the bent part formed in the coupling slot.

[0064] Figure 4 is a perspective view showing a turbine vane according to an embodiment of the present invention.

[0065] The turbine vane 200 can include an airfoil 210 fixed between the turbine blades 100 to guide the flow direction of the combustion gas passing through the turbine blades, an inner end wall 220 formed on the radially inner side of the airfoil, and an outer end wall 230 formed on the radially outer side of the airfoil.

[0066] Similar to the airfoil 110 of the turbine blade 100, the airfoil 210 of the turbine vane 200 includes a concave pressure surface 211, an opposite convex suction surface 212, a leading edge 213, and a trailing edge 214.

[0067] The inner end wall 220 is integrally formed on the radially inner side of the airfoil 210 and can be fixed within the turbine housing. An endwall cavity (225) through which air can flow is formed inside the inner end wall 220, and a plurality of pin-fin cooling structures 300 may be formed in the endwall cavity 225. The plurality of pin-fin cooling structures 300 may be arranged around the joint with the airfoil 210 inside the endwall cavity 225.

[0068] The outer end wall 230 is integrally formed on the radially outer side of the airfoil 210 and can be fixed to the turbine housing. An endwall cavity 235 is also formed inside the outer end wall 230. Although not shown in FIG. 4, a plurality of pin-fin cooling structures 300 may be formed in the endwall cavity 235.

[0069] FIG. 5 is a cross-sectional perspective view showing an airfoil according to an embodiment of the present invention. Although the airfoil 110 of the turbine blade 100 is shown in FIG. 5, the same configuration can be formed on the airfoil 210 of the turbine vane 200.

[0070] The airfoil 110 can include a cooling flow path cavity 150 formed in the inner trailing edge portion, and a plurality of pin-fin cooling structures 300 formed to contact one side surface and the other side surface of the cooling flow path cavity.

[0071] The cooling flow path cavity 150 is formed in the inner trailing edge portion of the airfoil 110 so that cooling air can flow in the direction of the trailing edge 114.

[0072] The plurality of pin-fin cooling structures 300 can be integrally connected in a column shape from one side surface to the other side surface of the cooling flow path cavity 150. The pin-fin cooling structure 300 may be composed of fins in the form of pins. The plurality of pin-fin cooling structures 300 may be arranged alternately in even and odd rows.

[0073] FIG. 6 is a partial cross-sectional perspective view showing the cooling flow path cavity according to an embodiment of the present invention, FIG. 7A is a perspective view showing the pin-fin cooling structure according to the first embodiment of the present invention, and FIG. 7B is a top view showing the pin-fin cooling structure according to the first embodiment.

[0074] The pin-fin cooling structure 300 according to the first embodiment can include cooling pins 310 connected to one side surface and the other side surface of the cooling flow path cavity 150, and a pair of guide pins 320 formed at a predetermined distance from both sides of the cooling pins and surrounding the cooling pins.

[0075] In FIG. 6, the upper surface and the lower surface of the cooling flow path cavity 150 are shown in a simplified manner in the case of parallel planes, but in reality, as shown in FIG. 5, one side surface and the other side surface of the cooling flow path cavity 150 can be formed on curved surfaces inclined with respect to each other. Also, the pin-fin cooling structure 300 shown in FIG. 6 corresponds to the first embodiment.

[0076] The cooling pins 310 are formed in a cylindrical shape, and the upper surface and the lower surface of the cylinder can be integrally formed so as to be connected to one side surface and the other side surface of the cooling flow path cavity 150.

[0077] A pair of guide pins 320 may be formed at a predetermined distance on both sides of the cooling pin 310 so as to surround the cooling pin. The pair of guide pins 320 may be arranged symmetrically with respect to a plane passing through the center of the cooling pin 310 to guide the flowing cooling air.

[0078] In the first embodiment, the guide pin 320 may be formed in an arc-shaped rib shape arranged within a predetermined angular range from the center of the cylinder. Different from the cooling pin 310, the guide pin 320 is not formed in a column shape, and four guide pins 320 may be formed to be connected to one side surface and the other side surface of the cooling channel cavity 150 on the sides of the upper end portion and the lower end portion of the cooling pin 310, respectively.

[0079] As shown in FIGS. 7A and 7B, the guide pin 320 may be formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin 310. The lower guide pin 320 may be in contact with one side surface of the cooling channel cavity, and the upper guide pin 320 may be arranged to be in contact with the other side surface of the cooling channel cavity 150.

[0080] The height (H) of the cooling pin 310 may be formed to be similar to the diameter (D) of the cooling pin 310. The height (h) of each guide pin 320 may be formed to be about 16.7% to 33.3% of the diameter (D) of the cooling pin 310 or the height (H) of the cooling pin 310.

[0081] The pair of guide pins 320 may be formed such that the angle (a) arranged from the center of the cylinder from the upstream end portion to the downstream end portion is 80 to 100 degrees. For example, the angle (a) of the arc-shaped rib of the guide pin 320 may be formed to be 90 degrees.

[0082] The pair of guide pins 320 may be arranged such that the angle (2b) between the upstream end portions of the cooling channel is larger than the angle (2c) between the downstream end portions.

[0083] When taking a straight line in the flow direction as a reference through the center of the cooling pin 310, the guide pin 320 can be arranged such that the angle (b) to the upstream end of the guide pin 320 is 50 to 70 degrees. At this time, the angle (c) from the straight line in the flow direction through the center of the cooling pin 310 to the downstream end of the guide pin 320 may be 20 to 40 degrees.

[0084] The guide pin 320 may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin 310. That is, the width (w) of the guide pin 320 may be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin 310.

[0085] The guide pin 320 may include a curved rib portion 321 formed with a predetermined angle, height, and width, and a pair of end round portions 322 formed in a semi-circular shape at the upstream end and the downstream end of the curved rib portion.

[0086] As shown in FIG. 7B, the angle (a) arranged from the center of the cylinder from the upstream end to the downstream end of the guide pin 320 may mean the angle from the upstream end to the downstream end of the curved rib portion 321.

[0087] Since a pair of end round portions 322 are formed at both ends of the curved rib portion 321, the flowing air can be smoothly guided, and there is no sharp vertex, preventing damage due to stress concentration.

[0088] FIG. 8A is a perspective view showing a pin-fin cooling structure according to a second embodiment of the present invention, and FIG. 8B is a top view showing the pin-fin cooling structure according to the second embodiment.

[0089] The pin-fin cooling structure 300 according to the second embodiment may include cooling pins 310 connected to one side surface and the other side surface of the cooling flow path cavity 150, and a pair of guide pins 320 formed at a predetermined distance on both sides of the cooling pins and surrounding the cooling pins.

[0090] The cooling pins 310 are formed in a cylindrical shape, and the guide pins 320 may be formed in an arc-shaped rib shape that is perpendicular to the air flow direction and arranged within a predetermined angular range in the downstream direction from a plane passing through the center of the cylinder.

[0091] In the second embodiment, similar to the cooling pins 310, the guide pins 320 may be formed in a columnar shape connected to one side surface and the other side surface of the cooling channel cavity 150.

[0092] The guide pin 320 may include a curved rib portion 321 formed with a predetermined angle, height, and width, and a pair of end plane portions 323 formed in a plane passing through the center of the cylinder at the upstream end and the downstream end of the curved rib portion.

[0093] As shown in FIG. 8B, the guide pin 320 may be formed such that the angle (a) arranged in the downstream direction from a plane passing through the center of the cylinder is 50 to 65 degrees. That is, the angle between the upstream ends of the pair of guide pins 320 may be arranged at 180 degrees, and the angle between the downstream ends of the pair of guide pins 320 may be arranged at 50 to 80 degrees.

[0094] The guide pin 320 may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pin 320 is 1.0 to 2.0 times the diameter (D) of the cooling pin. That is, the distance (L) from the center of the cooling pin 310 to the center in the width direction of the guide pin 320 may be arranged to be 2 to 4 times the radius of the cooling pin 310.

[0095] The guide pin 320 may be formed to have a width (w) that is 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin 310. That is, the width (w) of the guide pin 320 may be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin 310.

[0096] Since the pair of guide pins 320 are arranged only at the upstream ends, the pin-fin cooling structure 300 of the second embodiment can be referred to as a Half Guide Pin.

[0097] FIG. 9A is a perspective view showing a pin-fin cooling structure according to a third embodiment of the present invention, and FIG. 9B is a top view showing the pin-fin cooling structure according to the third embodiment.

[0098] The pin-fin cooling structure 300 according to the third embodiment can also include cooling pins 310 connected to one side surface and the other side surface of the cooling flow path cavity 150, and a pair of guide pins 320 formed at a predetermined distance on both sides of the cooling pins and surrounding the cooling pins.

[0099] The cooling pin 310 is formed in a cylindrical shape, and the guide pin 320 can include a curved rib portion 321 formed in an arc-shaped rib shape that is perpendicular to the air flow direction and is arranged within a predetermined angle range in the downstream direction from a plane passing through the center of the cylinder, and a downstream extension portion 325 that bends and extends in the opposite direction from an inflection point downstream of the curved rib portion 321.

[0100] The cooling pin 310 may be formed in a cylindrical shape having a predetermined diameter (D) and height (H).

[0101] The upstream end portion of the curved rib portion 321 is perpendicular to the air flow direction and is arranged at a position where it meets a plane passing through the center of the cylinder, and the downstream end portion of the curved rib portion 321 may be arranged at a predetermined angle (a) position with respect to the center of the cylinder from the plane.

[0102] The downstream extension portion 325 may be formed to bend outward from the downstream end portion of the curved rib portion 321 and have a predetermined radius of curvature. The length of the downstream extension portion 325 may be formed to be 1 / 3 to 1 / 2 times that of the curved rib portion 321. The radius of curvature of the downstream extension portion 325 may be formed to be smaller than the radius of curvature of the curved rib portion 321.

[0103] The curved rib portion 321 may be arranged such that the angle (a) from the plane passing through the center of the cylinder to the downstream inflection point is 50 to 65 degrees. That is, the angle between the upstream end portions of the pair of curved rib portions 321 may be arranged to be 180 degrees, and the angle between the downstream end portions of the pair of guide pins 320 may be arranged to be 50 to 80 degrees. The angle between the downstream end portions of the pair of downstream extension portions 325 may be arranged to be smaller than the angle between the downstream end portions of the pair of guide pins 320.

[0104] The guide pin 320 may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pin 320 is 1.0 to 2.0 times the diameter (D) of the cooling pin. That is, the distance (L) from the center of the cooling pin 310 to the center in the width direction of the guide pin 320 may be arranged to be 2 to 4 times the radius of the cooling pin 310.

[0105] The guide pin 320 may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin 310. That is, the width (w) of the guide pin 320 may be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin 310.

[0106] Since the pair of guide pins 320 are arranged only at the upstream end portions and are horseshoe-shaped, the pin-fin cooling structure 300 of the third embodiment can be referred to as a Half Horseshoe Guide Pin.

[0107] FIG. 10A is a perspective view showing a pin-fin cooling structure according to a fourth embodiment of the present invention, and FIG. 10B is a top view showing the pin-fin cooling structure according to the fourth embodiment.

[0108] The pin-fin cooling structure 300 according to the fourth embodiment may also include cooling pins 310 connected to one side surface and the other side surface of the cooling flow path cavity 150, and a pair of guide pins 320 formed at a predetermined distance from both sides of the cooling pins and surrounding the cooling pins.

[0109] The cooling pin 310 is formed in a cylindrical shape, and the guide pin 320 includes a curved rib portion 321 formed in an arc-shaped rib shape that is perpendicular to the air flow direction and arranged within a predetermined angular range in the downstream direction from a plane passing through the center of the cylinder, an upstream extension portion 326 extending at a predetermined angle from the upstream end of the curved rib portion, and a downstream extension portion 325 bent and extended in the opposite direction from the downstream inflection point of the curved rib portion.

[0110] The cooling pin 310 may be formed in a cylindrical shape having a predetermined diameter (D) and height (H).

[0111] The upstream end of the curved rib portion 321 is perpendicular to the air flow direction and is arranged at a position where it meets a plane passing through the center of the cylinder, and the downstream end of the curved rib portion 321 may be arranged at a predetermined angular (a) position with respect to the center of the cylinder from the plane.

[0112] The upstream extension portion 326 may be formed by extending a predetermined length from the upstream end of the curved rib portion 321 with the same radius of curvature.

[0113] The downstream extension portion 325 may be formed by bending outward from the downstream end of the curved rib portion 321 to have a predetermined radius of curvature. The length of the downstream extension portion 325 may be formed to be 1 / 3 to 1 / 2 times that of the curved rib portion 321. The radius of curvature of the downstream extension portion 325 may be formed smaller than the radius of curvature of the curved rib portion 321.

[0114] The angle (a) from the plane passing through the center of the cylinder to the downstream inflection point of the curved rib portion 321 may be arranged at 50 to 65 degrees. That is, the angle between the upstream ends of a pair of curved rib portions 321 may be arranged at 180 degrees, and the angle between the downstream ends of a pair of guide pins 320 may be arranged at 50 to 80 degrees. The angle between the downstream ends of a pair of downstream extension portions 325 may be arranged smaller than the angle between the downstream ends of a pair of guide pins 320.

[0115] The upstream extension part 326 may be arranged such that the angle (b) extending in the upstream direction from the plane passing through the center of the cylinder is 20 to 40 degrees. As a result, the angle between the upstream ends of the pair of upstream extension parts 326 may be arranged to be 100 to 140 degrees.

[0116] The guide pin 320 may be arranged such that the distance (L) from the center of the cylinder to the center in the width direction of the guide pin 320 is 1.0 to 2.0 times the diameter (D) of the cooling pin. That is, the distance (L) from the center of the cooling pin 310 to the center in the width direction of the guide pin 320 may be arranged to be 2 to 4 times the radius of the cooling pin 310.

[0117] The guide pin 320 may be formed to have a width (w) that is 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin 310. That is, the width (w) of the guide pin 320 may be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin 310.

[0118] Since the pair of guide pins 320 are in a horseshoe shape, the pin-fin cooling structure 300 of the fourth embodiment can be referred to as a horseshoe guide pin.

[0119] FIG. 11A is a diagram showing the heat transfer characteristics of a pin-fin cooling structure according to the prior art, FIGS. 11B and 11C are diagrams showing the heat transfer characteristics of the pin-fin cooling structure according to the first embodiment of the present invention, FIGS. 12A to 12D are diagrams showing the heat transfer characteristics of the pin-fin cooling structures according to the second to fourth embodiments of the present invention, and FIG. 13 is a graph showing the heat transfer performance of the pin-fin cooling structures according to the prior art and the embodiments of the present invention.

[0120] In FIG. 11A, the prior art pin-fin has cylindrical cooling pins arranged alternately row by row. FIGS. 11B and 11C show that the pin-fin cooling structure according to the first embodiment of the present invention includes cooling pins and two pairs of guide pins. FIG. 11B shows the case where the width (w) of the arc-shaped rib guide pin is 1 / 6 of the height of the cooling pin, and FIG. 11C shows the case where the width (w) of the guide pin is 1 / 3 of the height of the cooling pin.

[0121] FIG. 12A shows the Half Guide Fin model of the second embodiment, FIG. 12B shows the Horseshoe Guide Fin model of the fourth embodiment, FIG. 12C shows the case where the angle (a) of the curved rib portion 321 is 57.5 degrees in the Half Horseshoe Guide Fin model of the third embodiment, and FIG. 12D shows the detailed flow structure when the angle (a) is 55 degrees.

[0122] In the case of the prior art pin-fin, an area of increased heat transfer due to collisions upstream of the circular pins and an area of decreased heat transfer due to vortices downstream often appear.

[0123] According to the pin-fin cooling structure of the present invention, by utilizing the guide pin structure around the circular pins, the heat transfer upstream of the circular pins can be further improved, and the vortices and separation regions in the downstream portion with low heat transfer can be removed, contributing to an increase in the average heat transfer.

[0124] As shown in FIG. 13, it can be confirmed that the pin-fin cooling structure of the present invention has a heat transfer performance improvement of 40% or more compared to the prior art.

[0125] According to the pin-fin cooling structure of the turbine component of the present invention and the gas turbine including the same, by forming a guide pin structure around the circular cooling pins, the wake region and the separation zone in the downstream of the cooling pins are removed, the flow of air is guided to reduce the secondary flow region, and the flow velocity is increased by the guide pin structure to improve the heat transfer performance in the downstream of the cooling pins.

[0126] As described above, an embodiment of the present invention has been described. However, those having ordinary knowledge in the technical field can make various modifications and changes to the present invention by adding, changing, deleting or adding components, etc., without departing from the idea of the present invention described in the claims, and this is also included within the scope of the rights of the present invention.

Explanation of Reference Numerals

[0127] 1000: Gas turbine, 1010: Housing 1100: Compressor, 1110: Blade 1112: Doubletail part, 1120: Compressor rotor disk 1200: Combustor, 1210: Combustion chamber 1220: Fuel nozzle module 1300: Turbine, 1320: Turbine rotor disk 1330: Turbine vane, 1340: Turbine blade 1400: Diffuser, 1450: Fixed nut 1500: Torque tube unit, 1600: Tie rod 100: Turbine blade, 110: Airfoil 111: Pressure surface, 112: Suction surface 113: Leading edge, 114: Trailing edge 120: Platform part, 130: Root part 150: Cooling flow path cavity 200: Turbine vane, 210: Airfoil 211: Pressure surface, 212: Suction surface 213: Leading edge, 214: Trailing edge 220: Inner end wall, 225: End wall cavity 230: Outer end wall, 235: End wall cavity 300: Cooling structure, 310: Cooling pin 320: Guide pin, 321: Curved rib portion 322: End rounded portion, 323: End flat portion 325: Downstream extension, 326: Upstream extension

Claims

1. In an airfoil of a turbine blade or a turbine vane, a cooling flow path cavity formed in an inner trailing edge portion of the airfoil; and a plurality of pin-fin cooling structures formed so as to be in contact with one side surface and the other side surface of the cooling flow path cavity, wherein the plurality of pin-fin cooling structures include cooling pins connected to one side surface and the other side surface of the cooling flow path cavity; and a pair of guide pins formed at a predetermined distance from both sides of the cooling pin and surrounding the cooling pin, the airfoil comprising the pair of guide pins.

2. The cooling pin is formed in a cylindrical shape, and the guide pin is formed in an arc-shaped rib shape arranged within a predetermined angular range from the center of the cylinder, the airfoil according to claim 1.

3. The guide pin is formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin, wherein the lower guide pin is in contact with one side surface of the cooling flow path cavity, and the upper guide pin is arranged to be in contact with the other side surface of the cooling flow path cavity, the airfoil according to claim 2.

4. The pair of guide pins has an angle (a) arranged from the center of the cylinder from the upstream end to the downstream end of 80 to 100 degrees, the airfoil according to claim 3.

5. The pair of guide pins is arranged such that an angle (2b) between the upstream end portions of the cooling flow path is larger than an angle (2c) between the downstream end portions, the airfoil according to claim 4.

6. The guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin, the airfoil according to any one of claims 3 to 5.

7. The cooling pin is formed in a cylindrical shape, and the guide pin is formed in an arc-shaped rib shape arranged within a predetermined angular range in a downstream direction from a plane perpendicular to the air flow direction and passing through the center of the cylinder, the airfoil according to claim 1.

8. The guide pin has an angle (a) arranged in a downstream direction from a plane passing through the center of the cylinder of 50 to 65 degrees, the airfoil according to claim 7.

9. The guide pin is arranged such that a distance (L) from the center of the cylinder to the center in the width direction of the guide pin is 1.0 to 2.0 times the diameter (D) of the cooling pin, the airfoil according to claim 8.

10. The guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin. The airfoil according to claim 8 or 9.

11. The cooling pin is formed in a cylindrical shape, The guide pin is, A curved rib portion formed in an arcuate rib shape that is perpendicular to the air flow direction and is arranged within a predetermined angular range in the downstream direction from a plane passing through the center of the cylinder, The airfoil according to claim 1, comprising a downstream extension portion that bends and extends in the opposite direction from an inflection point downstream of the curved rib portion.

12. The airfoil according to claim 11, wherein the angle (a) from a plane passing through the center of the cylinder to an inflection point downstream of the curved rib portion is arranged at 50 to 65 degrees.

13. The airfoil according to claim 12, wherein the distance (L) from the center of the cylinder to the center in the width direction of the guide pin is arranged to be 1.0 to 2.0 times the diameter (D) of the cooling pin.

14. The guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin. The airfoil according to claim 12 or 13.

15. The cooling pin is formed in a cylindrical shape, The guide pin is, A curved rib portion formed in an arcuate rib shape that is perpendicular to the air flow direction and is arranged within a predetermined angular range in the downstream direction from a plane passing through the center of the cylinder, An upstream extension portion extending at a predetermined angle from the upstream end of the curved rib portion, The airfoil according to claim 1, comprising a downstream extension portion that bends and extends in the opposite direction from an inflection point downstream of the curved rib portion.

16. The airfoil according to claim 15, wherein the angle (a) from a plane passing through the center of the cylinder to an inflection point downstream of the curved rib portion is arranged at 50 to 65 degrees.

17. The airfoil according to claim 16, wherein the upstream extension portion is arranged at 20 to 40 degrees in the upstream direction from a plane passing through the center of the cylinder.

18. The airfoil according to claim 16 or 17, wherein the distance (L) from the center of the cylinder to the center in the width direction of the guide pin is arranged to be 1.0 to 2.0 times the diameter (D) of the cooling pin.

19. The guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin. The airfoil according to claim 16 or 17.

20. In a turbine vane including an airfoil, an inner end wall formed radially inward of the airfoil, and an outer end wall formed radially outward of the airfoil, end wall cavities respectively formed inside the inner end wall and the outer end wall, including a plurality of pin - fin cooling structures formed to contact one side surface and the other side surface of the end wall cavity, the plurality of pin - fin cooling structures include cooling pins connected to one side surface and the other side surface of the end wall cavity, and a pair of guide pins formed at a predetermined distance on both sides of the cooling pin and surrounding the cooling pin. A turbine vane.

21. The cooling pin is formed in a cylindrical shape, The guide pin is formed in an arc - shaped rib shape arranged within a predetermined angular range from the center of the cylinder. The turbine vane according to claim 20.

22. A compressor that inhales and compresses external air, a combustor that mixes fuel with the air compressed by the compressor and burns it, In a gas turbine including a turbine having turbine blades and turbine vanes mounted inside a turbine casing, and the turbine blades being rotated by combustion gas discharged from the combustor, the airfoils of the turbine blades and turbine vanes include a cooling flow path cavity formed at the inner trailing edge of the airfoil, and a plurality of pin - fin cooling structures formed to contact one side surface and the other side surface of the cooling flow path cavity, the plurality of pin - fin cooling structures include cooling pins connected to one side surface and the other side surface of the cooling flow path cavity, and a pair of guide pins formed at a predetermined distance on both sides of the cooling pin and surrounding the cooling pin. A gas turbine.

23. The cooling pin is formed in a cylindrical shape, The guide pin is formed in an arc - shaped rib shape arranged within a predetermined angular range from the center of the cylinder. The gas turbine according to claim 22.

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