Pin-fin cooling structure for turbine component and Gas turbine comprising the same

Abstract

The airfoil of the present invention comprises, in an airfoil of a turbine blade or turbine vane, a cooling passage cavity formed in the inner rear edge of the airfoil; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the cooling passage cavity, wherein the fin-fin cooling structures comprise a cooling fin connected to one side and the other side of the cooling passage cavity and a pair of guide fins formed to surround the cooling fins, spaced apart by a predetermined distance on both sides of the cooling fins.

Description

Technology Field

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

[0002] A turbine is a mechanical device that generates rotational force through impulse or reaction force by utilizing the flow of a compressible fluid, such as steam or gas; examples include steam turbines that use steam and gas turbines that use high-temperature combustion gases.

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

[0004] The combustion device generates high-temperature, high-pressure combustion gas by supplying fuel to the compressed air compressed by the compressor and igniting it with a burner.

[0005] The turbine has multiple turbine vanes and turbine blades arranged alternately within the turbine housing. Additionally, a rotor is positioned to penetrate the center of the compressor, combustor, turbine, and exhaust chamber.

[0006] The above rotor is rotatably supported at both ends by bearings. Additionally, a plurality of discs are fixed to the rotor, and each blade is connected to them, while a drive shaft, such as that of a generator, is connected to the end on the exhaust chamber side.

[0007] Since these gas turbines do not have a reciprocating mechanism like the piston of a four-stroke engine, there are no mutual friction parts like piston-cylinder, so the consumption of lubricating oil is extremely low, and the amplitude characteristic of reciprocating machines is greatly reduced, and high-speed motion is possible.

[0008] To briefly explain the operation of a gas turbine, air compressed by a compressor is mixed with fuel and combusted to produce high-temperature combustion gases, which are then injected toward the turbine. As the injected combustion gases pass through the turbine vanes and blades, they generate rotational force, causing the rotor to rotate. Prior art literature

[0009] Korean Patent Publication No. 10-2376052 (Registered on March 15, 2022) The problem to be solved

[0010] The present invention aims to provide a fin-fin cooling structure for a turbine component that exhibits excellent heat transfer performance by forming a plurality of fin-fin cooling structures in a cooling channel cavity formed inside the turbine component, and a gas turbine including the same. means of solving the problem

[0011] An airfoil of the present invention for achieving the above objective comprises, in an airfoil of a turbine blade or turbine vane, a cooling passage cavity formed in the inner rear edge of the airfoil; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the cooling passage cavity, wherein the fin-fin cooling structures comprise a cooling fin connected to one side and the other side of the cooling passage cavity and a pair of guide fins formed to surround the cooling fins, spaced apart by a predetermined distance on both sides of the cooling fins.

[0012] In the first embodiment of the present invention, the cooling fin is formed in the shape of a cylinder, and the guide fin may be formed in the shape of an arc-shaped rib arranged within a predetermined angle range from the center of the cylinder.

[0013] The guide pin is formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin, and the lower guide pin may be positioned to contact one side of the cooling channel cavity and the upper guide pin may be positioned to contact the other side of the cooling channel cavity.

[0014] The above pair of guide pins may have an angle (a) of 80 to 100 degrees from the center of the cylinder, from the upstream end to the downstream end.

[0015] The above pair of guide pins can be positioned so that the angle (2b) between the upstream ends of the cooling channel is greater than the angle (2c) between the downstream ends.

[0016] The above guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0017] In the second embodiment of the present invention, the cooling fin is formed in a cylindrical shape, and the guide fin may be formed in an arc-shaped rib shape that is perpendicular to the direction of air flow and is arranged in a downstream direction from a plane passing through the center of the cylinder.

[0018] The above guide pin may have an angle (a) of 50 to 65 degrees arranged downstream from the plane passing through the center of the cylinder.

[0019] The guide pin can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin.

[0020] The above guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0021] In the third embodiment of the present invention, the cooling fin is formed in a cylindrical shape, and the guide fin may include a curved rib portion formed in an arc shape that is perpendicular to the direction of air flow and arranged in a downstream direction within a predetermined angle range from a plane passing through the center of the cylinder, and a downstream extension portion that is bent in the opposite direction and extended at the downstream inflection point of the curved rib portion.

[0022] The above curved rib portion 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.

[0023] The guide pin can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin.

[0024] The above guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0025] In the fourth embodiment of the present invention, the cooling fin is formed in a cylindrical shape, and the guide fin may include a curved rib portion formed in an arc shape that is perpendicular to the direction of air flow and arranged in a 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, and a downstream extension portion that is bent in the opposite direction and extended from the downstream inflection point of the curved rib portion.

[0026] The above curved rib portion 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.

[0027] The above upstream extension may be positioned at an angle of 20 to 40 degrees upstream from a plane passing through the center of the cylinder.

[0028] The guide pin can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin.

[0029] The above guide pin may be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin.

[0030] The turbine vane of the present invention comprises an airfoil, an inner endwall formed radially inward of the airfoil, and an outer endwall formed radially outward of the airfoil, wherein the turbine vane comprises: an endwall cavity formed inside each of the inner endwall and the outer endwall; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the endwall cavity, wherein the fin-fin cooling structures comprise a cooling fin connected to one side and the other side of the endwall cavity, and a pair of guide fins formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0031] The cooling fin is formed in the shape of a cylinder, and the guide fin can be formed in the shape of an arc-shaped rib positioned at a predetermined angle range from the center of the cylinder.

[0032] The gas turbine of the present invention comprises: a compressor that sucks in and compresses external air; a combustor that mixes fuel with the air compressed by the compressor and burns it; and a turbine in which a turbine blade and a turbine vane are mounted inside a turbine casing, and the turbine blade rotates by combustion gas discharged from the combustor. The airfoil of the turbine blade and the turbine vane comprises: a cooling passage cavity formed in the inner rear edge of the airfoil; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the cooling passage cavity. Each fin-fin cooling structure comprises a cooling fin connected to one side and the other side of the cooling passage cavity, and a pair of guide fins formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0033] The cooling fin is formed in the shape of a cylinder, and the guide fin can be formed in the shape of an arc-shaped rib positioned at a predetermined angle range from the center of the cylinder. Effects of the invention

[0034] According to the fin-fin cooling structure of the turbine component of the present invention and the gas turbine including the same, by configuring a guide fin structure around a circular cooling fin, the wake region and separation zone of the cooling fin wake are eliminated, the air flow is guided to reduce the secondary flow region, and the heat transfer performance of the cooling fin wake is improved by increasing the flow velocity through the guide fin structure. Brief explanation of the drawing

[0035] FIG. 1 is a partially cutaway perspective view of a gas turbine according to one embodiment of the present invention. FIG. 2 is a cross-sectional view showing the schematic structure of a gas turbine according to one embodiment of the present invention. FIG. 3 is a perspective view showing a turbine blade according to one embodiment of the present invention. FIG. 4 is a perspective view showing a turbine vane according to one embodiment of the present invention. FIG. 5 is a cross-sectional perspective view showing an airfoil according to one embodiment of the present invention. FIG. 6 is a partial cross-sectional perspective view showing a cooling channel cavity according to one embodiment of the present invention. FIG. 7 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a first embodiment of the present invention. FIG. 8 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a second embodiment of the present invention. FIG. 9 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a third embodiment of the present invention. FIG. 10 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a fourth embodiment of the present invention. FIG. 11 is a diagram showing the heat transfer characteristics of a fin-fin cooling structure according to the prior art and the first embodiment of the present invention. FIG. 12 is a diagram showing the heat transfer characteristics of a fin-fin cooling structure according to the second to fourth embodiments of the present invention. FIG. 13 is a graph showing the heat transfer performance of a fin-fin cooling structure according to the prior art and embodiments of the present invention. Specific details for implementing the invention

[0036] The present invention is capable of various modifications and may have various embodiments, and specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and it should be understood that it includes all modifications, equivalents, and substitutions that fall within the spirit and scope of the invention.

[0037] The terms used in this invention are used merely to describe specific embodiments and are not intended to limit the invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this invention, terms such as "comprising" or "having" are intended to indicate the existence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not precluding the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof.

[0038] Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. Note that in the accompanying drawings, identical components are indicated by the same reference numerals whenever possible. Furthermore, detailed descriptions of known functions and configurations that may obscure the essence of the present invention will be omitted. For the same reason, some components in the accompanying drawings may be exaggerated, omitted, or schematically depicted.

[0039] FIG. 1 is a partially cutaway perspective view of a gas turbine according to one embodiment of the present invention, and FIG. 2 is a cross-sectional view showing the schematic structure of a gas turbine according to one embodiment of the present invention.

[0040] As illustrated in FIG. 1, a gas turbine (1000) according to one embodiment of the present invention includes a compressor (1100), a combustor (1200), and a turbine (1300). The compressor (1100) has a plurality of blades (1110) installed radially. The compressor (1100) rotates the blades (1110), and air moves as it is compressed by the rotation of the blades (1110). The size and installation angle of the blades (1110) may vary depending on the installation location. In one embodiment, the compressor (1100) is connected directly or indirectly to the turbine (1300) so that it can receive a portion of the power generated from the turbine (1300) and use it for the rotation of the blades (1110).

[0041] The air compressed in 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).

[0042] As illustrated in FIG. 2, a gas turbine (1000) according to one embodiment of the present invention is provided with a housing (1010), and a diffuser (1400) is provided at the rear of the housing (1010) to discharge combustion gas that has passed through the turbine. Then, a combustor (1200) is disposed in front of the diffuser (1400) to receive compressed air and combust it.

[0043] When described based on the direction of air flow, a compressor section (1100) is located on the upstream side of the housing (1010), and a turbine section (1300) is positioned on the downstream side. Additionally, a torque tube unit (1500) is positioned between the compressor section (1100) and the turbine section (1300) as a torque transmission member that transmits rotational torque generated in the turbine section (1300) to the compressor section (1100).

[0044] The compressor section (1100) is provided with a plurality (e.g., 14) of compressor rotor disks (1120), and each of the compressor rotor disks (1120) is connected by a tie rod (1600) so as not to be separated in the axial direction.

[0045] Specifically, each of the compressor rotor disks (1120) is aligned along the axial direction with the tie rod (1600) forming the rotation axis passing approximately through the center. Here, the opposing surfaces of adjacent compressor rotor disks (1120) are compressed by the tie rod (1600) so that relative rotation is impossible.

[0046] A plurality of blades (1110) are radially coupled to the outer surface of the compressor rotor disk (1120). Each blade (1110) is equipped with a dovetail portion (1112) and is fastened to the compressor rotor disk (1120).

[0047] Between each of the above rotor disks (1120), a vane (not shown) is positioned and fixed to the housing. Unlike the rotor disks, the vane is fixed so as not to rotate and serves to align the flow of compressed air passing through the blades of the compressor rotor disks and guide the air to the blades of the rotor disks located downstream.

[0048] The fastening method of the above dovetail section (1112) is of the tangential type and the axial type. This can be selected according to the required structure of a commercially available 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 a fastening device other than the above shapes, such as a key or a bolt.

[0049] The tie rod (1600) is positioned to penetrate the center of the plurality of compressor rotor disks (1120) and turbine rotor disks (1320), and the tie rod (1600) may consist of one or more tie rods. One end of the tie rod (1600) is fastened within the compressor rotor disk located at the uppermost side, and the other end of the tie rod (1600) is fastened by a fixing nut (1450).

[0050] The shape of the tie rod (1600) can be formed in various structures depending on the gas turbine, so it is not necessarily limited to the shape shown in FIG. 2. That is, as illustrated, it may have a shape where one tie rod penetrates the center of the rotor disk, or a shape where multiple tie rods are arranged circumferentially, and a combination of these is also possible.

[0051] Although not shown in the drawings, a vane acting as a guide vane may be installed at the next position after the diffuser in the compressor of a gas turbine to match the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the fluid pressure, and this is called a deswirler.

[0052] In the above-mentioned combustor (1200), the introduced compressed air is mixed with fuel and combusted to produce high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is raised to a heat resistance limit that the combustor and turbine components can withstand through an isostatic combustion process.

[0053] Combustors constituting the combustion system of a gas turbine may be arranged in multiple numbers within a housing formed in a cell shape and are composed of a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a transition piece that serves as a connection part between the combustor and the turbine.

[0054] Specifically, the liner provides a combustion space in which fuel injected by a fuel nozzle is mixed with compressed air from a compressor and combusted. This liner may include a flame chamber that provides a combustion space in which the fuel mixed with air is combusted, and a flow sleeve that surrounds the flame chamber and forms an annular space. Additionally, a fuel nozzle is connected to the front end of the liner, and a spark plug is connected to the side wall.

[0055] Meanwhile, a transition piece is connected to the rear end of the liner to allow combustion gases, combusted by a spark plug, to be sent to the turbine side. The outer wall of this transition piece is cooled by compressed air supplied from the compressor to prevent damage caused by the high temperature of the combustion gases.

[0056] To this end, the transition piece is provided with cooling holes to allow air to be injected into the interior, and the compressed air cools the main body inside through the holes and then flows toward the liner.

[0057] Cooling air that has cooled the aforementioned transition piece flows through the annular space of the above-mentioned liner, and compressed air from the outside of the flow sleeve can be supplied as cooling air through cooling holes provided in the flow sleeve to the outer wall of the liner and collide with it.

[0058] Meanwhile, the high-temperature, high-pressure combustion gas from the above-described combustor is supplied to the turbine (1300) described above. As the supplied high-temperature, high-pressure combustion gas expands, it collides with the rotating blades of the turbine, generating a reaction force and causing rotational torque. The rotational torque thus obtained is transmitted to the compressor through the torque tube described above, and any power exceeding the power required to drive the compressor is used to drive a generator, etc.

[0059] The turbine (1300) is basically similar in structure to a compressor. That is, the turbine (1300) is also equipped with a plurality of turbine rotor disks (1320) similar to the compressor rotor disks of a compressor. Accordingly, the turbine rotor disks (1320) also include a plurality of turbine blades (1340) arranged radially. The turbine blades (1340) can also be connected to the turbine rotor disks (1320) in a manner such as a dovetail. In addition, turbine vanes (1330) fixed to a housing are provided between the blades (1340) of the turbine rotor disks (1320) to guide the flow direction of combustion gas passing through the blades.

[0060] FIG. 3 is a perspective view showing a turbine blade according to an embodiment of the present invention. In FIG. 3, unlike FIG. 2, the reference numeral "100" is indicated on the turbine blade.

[0061] The turbine blade (100) includes an airfoil (110) that rotates by the pressure of combustion gas at the top, a platform portion (120) formed integrally at the bottom of the airfoil, and a root portion (130) formed integrally at the bottom of the platform portion and coupled to a turbine rotor disk (1320). An inlet may be formed on the inner side of the platform portion (120) to supply cooling fluid to an internal flow path formed inside the airfoil (110).

[0062] The airfoil (110) includes an intake surface (112) formed convexly outwardly on one side into which combustion gas is introduced, and a pressure surface (111) formed concavely on the opposite side of the intake surface. The front edge where the pressure surface (111) and the intake surface (112) meet forms a leading edge (113), and the rear edge forms a trailing edge (114). An internal passage (not shown) through which cooling air introduced through an inlet flows may be formed inside the airfoil (110).

[0063] The platform portion (120) serves to maintain the gap between the blades by having its side contact with the platform portion (120) of an adjacent turbine blade.

[0064] The root portion (130) may have an axial-type shape that is inserted along the axial direction of the turbine rotor disk into a coupling slot formed on the outer surface of the turbine rotor disk (1320). The root portion (130) may have a curve in the shape of a dovetail or fir tree, which may be formed to correspond to the shape of the curve formed in the coupling slot.

[0065] FIG. 4 is a perspective view showing a turbine vane according to one embodiment of the present invention.

[0066] The turbine vane (200) may include an airfoil (210) fixed between the turbine blades (100) to guide the flow direction of 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.

[0067] The airfoil (210) of the turbine vane (200), like the airfoil (110) of the turbine blade (100), includes a concave pressure surface (211), a convex suction surface (212) on the opposite side, a leading edge (213), and a trailing edge (214).

[0068] The inner endwall (220) can be integrally formed on the radially inner side of the airfoil (210) and fixed within the turbine housing. An endwall cavity (225) through which air can flow is formed inside the inner endwall (220), and a plurality of fin-fin cooling structures (300) can be formed in the endwall cavity (225). The plurality of fin-fin cooling structures (300) can be arranged around the joint with the airfoil (210) inside the endwall cavity (225).

[0069] The outer end wall (230) can be formed integrally on the radially outer side of the airfoil (210) and fixed to the turbine housing. An end wall cavity (235) is also formed inside the outer end wall (230), and although not shown in FIG. 4, a plurality of fin-fin cooling structures (300) can be formed in the end wall cavity (235).

[0070] FIG. 5 is a cross-sectional perspective view showing an airfoil according to one embodiment of the present invention. FIG. 5 shows an airfoil (110) of a turbine blade (100), but the same configuration can be formed on an airfoil (210) of a turbine vane (200).

[0071] The airfoil (110) may include a cooling passage cavity (150) formed in the inner rear portion and a plurality of fin-fin cooling structures (300) formed to be in contact with one side and the other side of the cooling passage cavity.

[0072] A cooling cavity (150) is formed in the inner rear edge of the airfoil (110) so that cooling air can flow toward the trailing edge (114).

[0073] A plurality of fin-fin cooling structures (300) can be integrally connected in a column shape from one side to the other side of the cooling channel cavity (150). The fin-fin cooling structures (300) can be composed of fins in the shape of pins. A plurality of fin-fin cooling structures (300) can be arranged such that even and odd sections are staggered from each other.

[0074] FIG. 6 is a partial cross-sectional perspective view showing a cooling channel cavity according to one embodiment of the present invention, and FIG. 7 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a first embodiment of the present invention.

[0075] A fin-fin cooling structure (300) according to the first embodiment may include a cooling fin (310) connected to one side and the other side of a cooling channel cavity (150), and a pair of guide pins (320) formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0076] In FIG. 6, the upper and lower surfaces of the cooling channel cavity (150) are simplified to be planes parallel to each other, but in reality, as shown in FIG. 5, one side and the other side of the cooling channel cavity (150) may be formed as curved surfaces arranged at an angle to each other. In addition, the fin-fin cooling structure (300) shown in FIG. 6 is illustrated as corresponding to the first embodiment.

[0077] The cooling fin (310) is formed in the shape of a cylinder, and the upper and lower surfaces of the cylinder can be integrally formed to be connected to one side and the other side of the cooling channel cavity (150).

[0078] A pair of guide pins (320) may be formed to surround the cooling fin (310) at a predetermined distance from both sides of the cooling fin. The pair of guide pins (320) may be arranged symmetrically with respect to a plane passing through the center of the cooling fin (310) to guide the flowing cooling air.

[0079] In the first embodiment, the guide pin (320) may be formed in the shape of an arc-shaped rib positioned at a predetermined angle from the center of the cylinder. Unlike the cooling pin (310), the guide pin (320) may not be formed in the shape of a column, but may be formed in a total of four such pins so as to be connected to one side and the other side of the cooling channel cavity (150) respectively, next to the upper and lower parts of the cooling pin (310).

[0080] As shown in FIG. 7, the guide pin (320) is formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin (310), and the lower guide pin (320) may be positioned to be in contact with one side of the cooling channel cavity and the upper guide pin (320) may be positioned to be in contact with the other side of the cooling channel cavity (150).

[0081] The height (H) of the cooling fin (310) can be formed to be similar to the diameter (D) of the cooling fin (310). The height (h) of each guide fin (320) can be formed to be approximately 16.7% to 33.3% of the diameter (D) of the cooling fin (310) or the height (H) of the cooling fin (310).

[0082] A pair of guide pins (320) can be formed at an angle (a) of 80 to 100 degrees from the center of the cylinder, from the upstream end to the downstream end. For example, the arc-shaped rib angle (a) of the guide pins (320) can be formed at 90 degrees.

[0083] A pair of guide pins (320) can be positioned so that the angle (2b) between the upstream ends of the cooling channel is greater than the angle (2c) between the downstream ends.

[0084] The guide pin (320) can be positioned such that the angle (b) to the upstream end of the guide pin (320) is 50 to 70 degrees when referenced to a straight line passing through the center of the cooling pin (310) in the direction of flow. At this time, the angle (c) to the downstream end of the guide pin (320) from a straight line passing through the center of the cooling pin (310) in the direction of flow can be 20 to 40 degrees.

[0085] The guide pin (320) can be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin (310). In other words, the width (w) of the guide pin (320) can be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin (310).

[0086] 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 semicircular shape at the upstream and downstream ends of the curved rib portion.

[0087] As shown in FIG. 7, the angle (a) positioned 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).

[0088] Since a pair of end round portions (322) are formed at both ends of the curved rib portion (321), flowing air can be smoothly guided, and since there are no sharp vertices, damage due to stress concentration can be prevented.

[0089] FIG. 8 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a second embodiment of the present invention.

[0090] A fin-fin cooling structure (300) according to the second embodiment may include a cooling fin (310) connected to one side and the other side of a cooling channel cavity (150), and a pair of guide pins (320) formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0091] The cooling fin (310) is formed in a cylindrical shape, and the guide fin (320) can be formed in an arc-shaped rib shape that is perpendicular to the direction of air flow and is positioned in a downstream direction from a plane passing through the center of the cylinder.

[0092] In the second embodiment, the guide pin (320) can be formed in the shape of a pillar connected to one side and the other side of the cooling channel cavity (150), similar to the cooling pin (310).

[0093] 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 as planes passing through the center of the cylinder at the upstream and downstream ends of the curved rib portion.

[0094] As illustrated in FIG. 8, the guide pin (320) can be formed at an angle (a) of 50 to 65 degrees, positioned downstream from a plane passing through the center of the cylinder. In other words, the angle between the upstream ends of a pair of guide pins (320) can be 180 degrees, and the angle between the downstream ends of a pair of guide pins (320) can be 50 to 80 degrees.

[0095] The guide pin (320) can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin (320) in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin. In other words, the distance (L) from the center of the cooling pin (310) to the center of the guide pin (320) in the width direction can be positioned so that it is 2 to 4 times the radius of the cooling pin (310).

[0096] The guide pin (320) can be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin (310). In other words, the width (w) of the guide pin (320) can be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin (310).

[0097] Since a pair of guide pins (320) are positioned only at the upstream end, the fin-fin cooling structure (300) of the second embodiment can be called a half guide pin.

[0098] FIG. 9 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a third embodiment of the present invention.

[0099] A fin-fin cooling structure (300) according to the third embodiment may also include a cooling fin (310) connected to one side and the other side of a cooling channel cavity (150), and a pair of guide pins (320) formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0100] The cooling fin (310) is formed in a cylindrical shape, and the guide fin (320) may include a curved rib portion (321) formed in an arc shape that is perpendicular to the direction of air flow and arranged in a downstream direction from a plane passing through the center of the cylinder, and a downstream extension portion (325) that is bent in the opposite direction and extended at the downstream inflection point of the curved rib portion.

[0101] The cooling fin (310) can be formed in the shape of a cylinder having a predetermined diameter (D) and height (H).

[0102] The upstream end of the curved rib portion (321) is positioned perpendicular to the direction of air flow and meets a plane passing through the center of the cylinder, and the downstream end of the curved rib portion (321) can be positioned at a predetermined angle (a) from the plane with respect to the center of the cylinder.

[0103] The downstream extension (325) can be formed to have a predetermined radius of curvature by bending outward at the downstream end of the curved rib (321). The length of the downstream extension (325) can be formed to be 1 / 3 to 1 / 2 times that of the curved rib (321). The radius of curvature of the downstream extension (325) can be formed to be smaller than the radius of curvature of the curved rib (321).

[0104] The curved rib section (321) can be positioned 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. In other words, the angle between the upstream ends of a pair of curved rib sections (321) can be positioned at 180 degrees, and the angle between the downstream ends of a pair of guide pins (320) can be positioned at 50 to 80 degrees. The angle between the downstream ends of a pair of downstream extension sections (325) can be positioned to be smaller than the angle between the downstream ends of a pair of guide pins (320).

[0105] The guide pin (320) can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin (320) in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin. In other words, the distance (L) from the center of the cooling pin (310) to the center of the guide pin (320) in the width direction can be positioned so that it is 2 to 4 times the radius of the cooling pin (310).

[0106] The guide pin (320) can be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin (310). In other words, the width (w) of the guide pin (320) can be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin (310).

[0107] Since a pair of guide pins (320) are positioned only at the upstream end and are horseshoe-shaped, the pin-fin cooling structure (300) of the third embodiment can be called a half horseshoe guide pin.

[0108] FIG. 10 is a perspective view (a) and a top view (b) showing a fin-fin cooling structure according to a fourth embodiment of the present invention.

[0109] A fin-fin cooling structure (300) according to the fourth embodiment may also include a cooling fin (310) connected to one side and the other side of a cooling channel cavity (150), and a pair of guide pins (320) formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin.

[0110] The cooling fin (310) is formed in a cylindrical shape, and the guide fin (320) may include a curved rib portion (321) formed in an arc shape that is perpendicular to the direction of air flow and arranged in a downstream direction from a plane passing through the center of the cylinder, an upstream extension portion (326) that extends at a predetermined angle from the upstream end of the curved rib portion, and a downstream extension portion (325) that is bent in the opposite direction and extended from the downstream inflection point of the curved rib portion.

[0111] The cooling fin (310) can be formed in the shape of a cylinder having a predetermined diameter (D) and height (H).

[0112] The upstream end of the curved rib portion (321) is positioned perpendicular to the direction of air flow and meets a plane passing through the center of the cylinder, and the downstream end of the curved rib portion (321) can be positioned at a predetermined angle (a) from the plane with respect to the center of the cylinder.

[0113] The upstream extension (326) can be formed by extending a predetermined length with the same radius of curvature from the upstream end of the curved rib (321).

[0114] The downstream extension (325) can be formed to have a predetermined radius of curvature by bending outward at the downstream end of the curved rib (321). The length of the downstream extension (325) can be formed to be 1 / 3 to 1 / 2 times that of the curved rib (321). The radius of curvature of the downstream extension (325) can be formed to be smaller than the radius of curvature of the curved rib (321).

[0115] The curved rib section (321) can be positioned 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. In other words, the angle between the upstream ends of a pair of curved rib sections (321) can be positioned at 180 degrees, and the angle between the downstream ends of a pair of guide pins (320) can be positioned at 50 to 80 degrees. The angle between the downstream ends of a pair of downstream extension sections (325) can be positioned to be smaller than the angle between the downstream ends of a pair of guide pins (320).

[0116] The upstream extension (326) can be positioned such that the angle (b) extending upstream from the plane passing through the center of the cylinder is 20 to 40 degrees. Accordingly, the angle between the upstream ends of a pair of upstream extensions (326) can be positioned such that it is 100 to 140 degrees.

[0117] The guide pin (320) can be positioned so that the distance (L) from the center of the cylinder to the center of the guide pin (320) in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling pin. In other words, the distance (L) from the center of the cooling pin (310) to the center of the guide pin (320) in the width direction can be positioned so that it is 2 to 4 times the radius of the cooling pin (310).

[0118] The guide pin (320) can be formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pin (310). In other words, the width (w) of the guide pin (320) can be formed to be 16.7% to 33.3% of the diameter (D) of the cooling pin (310).

[0119] Since a pair of guide pins (320) are horseshoe-shaped, the pin-shaped cooling structure (300) of the fourth embodiment can be called a horseshoe guide pin.

[0120] FIG. 11 is a diagram showing the heat transfer characteristics of a fin-fin cooling structure according to the prior art and the first embodiment of the present invention, FIG. 12 is a diagram showing the heat transfer characteristics of a fin-fin cooling structure according to the second to fourth embodiments of the present invention, and FIG. 13 is a graph showing the heat transfer performance of a fin-fin cooling structure according to the prior art and embodiments of the present invention.

[0121] In FIG. 11(a), the fin-fin of the prior art consists only of cylindrical cooling fins arranged alternately in each row. FIG. 11(b) and FIG. 11(c) show a fin-fin cooling structure according to the first embodiment of the present invention, comprising cooling fins and two pairs of guide fins, FIG. 11(b) shows a case where the width (w) of the guide fin in the form of an arc-shaped rib is 1 / 6 of the height of the cooling fin, and FIG. 11(c) shows a case where the width (w) of the guide fin is 1 / 3 of the height of the cooling fin.

[0122] FIG. 12(a) shows a Half Guide Fin model of the second embodiment, FIG. 12(b) shows a Horseshoe Guide Fin model of the fourth embodiment, FIG. 12(c) shows a Half Horseshoe Guide Fin model of the third embodiment where the angle (a) of the curved rib portion (321) is 57.5 degrees, and FIG. 12(d) shows a detailed flow structure where the angle (a) is 55 degrees.

[0123] In the case of the fin-fin of the conventional technology, the region of increased heat transfer due to collision upstream of the circular fin and the region of reduced heat transfer due to vortex in the wake are clearly visible.

[0124] According to the fin-fin cooling structure of the present invention, by utilizing a guide fin structure around a circular fin, heat transfer upstream of the circular fin is further improved, and the vortex and separation region in the wake portion with low heat transfer amount are eliminated, thereby contributing to an increase in average heat transfer.

[0125] As shown in FIG. 13, it can be confirmed that the fin-fin cooling structure of the present invention has a heat transfer performance improved by more than 40% compared to the prior art.

[0126] According to the fin-fin cooling structure of the turbine component of the present invention and the gas turbine including the same, by configuring a guide fin structure around a circular cooling fin, the wake region and separation zone of the cooling fin wake are eliminated, the air flow is guided to reduce the secondary flow region, and the heat transfer performance of the cooling fin wake is improved by increasing the flow velocity through the guide fin structure.

[0127] Although an embodiment of the present invention has been described above, those skilled in the art may modify and change the present invention in various ways by adding, changing, deleting, or adding components, etc., without departing from the spirit of the present invention as described in the claims, and such modifications and changes are also to be considered to be included within the scope of the rights of the present invention. Explanation of the symbols

[0128] 1000: Gas turbine 1010: Housing 1100: Compressor 1110: Compressor blade 1112: Dovetail section 1120: Compressor rotor disc 1200: Combustion unit 1210: Combustion chamber 1220: Fuel nozzle module 1300: Turbine 1320: Turbine rotor disk 1330: Turbine Vane 1340: Turbine Blade 1400: Diffuser 1450: Fixing 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 Section 130: Root Section 150: Cavity for cooling passage 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 fins 320: Guide pin 321: Curved rib section 322: Rounded end 323: Flat end 325: Downstream extension 326: Upstream extension

Claims

Claim 1 An airfoil of a turbine blade or turbine vane, comprising: a cooling passage cavity formed in the inner rear edge of the airfoil; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the cooling passage cavity, wherein the fin-fin cooling structures each comprise a cooling fin connected to one side and the other side of the cooling passage cavity and a pair of guide fins formed to surround the cooling fins, spaced apart by a predetermined distance on both sides of the cooling fins, wherein the cooling fins are formed in a cylindrical shape and the guide fins are formed in an arc-shaped rib shape and arranged within a predetermined angle range from the center of the cylinder. Claim 2 delete Claim 3 An airfoil according to claim 1, wherein the guide pin is formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling fin, and the lower guide pin is arranged to contact one side of the cooling channel cavity and the upper guide pin is arranged to contact the other side of the cooling channel cavity. Claim 4 An airfoil according to claim 1, characterized in that the predetermined angle (a) of the pair of guide pins is 80 to 100 degrees from the center of the cylinder from the upstream end to the downstream end. Claim 5 An airfoil according to claim 4, characterized in that the pair of guide pins are arranged such that the angle (2b) between the upstream ends of the cooling channel is greater than the angle (2c) between the downstream ends. Claim 6 ◈Claim 6 was abandoned upon payment of the registration fee.◈ An airfoil according to Claim 3, characterized in that the guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling fin. Claim 7 An airfoil according to claim 1, characterized in that the guide pin is formed in the shape of an arc-shaped rib arranged in a downstream direction from a plane perpendicular to the direction of air flow and passing through the center of the cylinder. Claim 8 An airfoil according to claim 7, characterized in that the predetermined angle (a) of the guide pin is 50 to 65 degrees downstream from the plane passing through the center of the cylinder. Claim 9 An airfoil according to claim 8, characterized in that the guide pin is 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 fin. Claim 10 ◈Claim 10 was abandoned upon payment of the registration fee.◈ An airfoil according to claim 8, characterized in that the guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling fin. Claim 11 An airfoil according to claim 1, wherein the guide pin comprises a curved rib portion formed in the shape of an arc and arranged in a downstream direction at a predetermined angle range from a plane perpendicular to the direction of air flow and passing through the center of the cylinder, and a downstream extension portion that is bent in the opposite direction and extended at a downstream inflection point of the curved rib portion. Claim 12 An airfoil according to claim 11, characterized in that the curved rib portion is 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. Claim 13 An airfoil according to claim 12, characterized in that the guide pin is arranged such that the distance (L) from the center of the cylinder to the center of the guide pin in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling fin. Claim 14 An airfoil according to claim 12, characterized in that the guide pin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling fin. Claim 15 An airfoil according to claim 1, wherein the guide pin comprises a curved rib portion formed in the shape of an arc and arranged in a downstream direction from a plane perpendicular to the direction of air flow and 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, and a downstream extension portion extending in the opposite direction and bent at the downstream inflection point of the curved rib portion. Claim 16 An airfoil according to claim 15, characterized in that the curved rib portion is 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. Claim 17 An airfoil according to claim 16, characterized in that the upstream extension is positioned at an angle of 20 to 40 degrees upstream from a plane passing through the center of the cylinder. Claim 18 An airfoil according to claim 16, characterized in that the guide pin is arranged such that the distance (L) from the center of the cylinder to the center of the guide pin in the width direction is 1.0 to 2.0 times the diameter (D) of the cooling fin. Claim 19 An airfoil according to claim 16, characterized in that the guide fin is formed to have a width (w) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling fin. Claim 20 A turbine vane comprising an airfoil, an inner endwall formed radially inward of the airfoil, and an outer endwall formed radially outward of the airfoil, wherein each endwall cavity is formed inside the inner endwall and the outer endwall, respectively; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the endwall cavity, wherein the fin-fin cooling structures each comprise a cooling fin connected to one side and the other side of the endwall cavity, and a pair of guide pins formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin, wherein the cooling fin is formed in a cylindrical shape, and the guide pins are formed in an arc-shaped rib shape and are arranged within a predetermined angle range from the center of the cylinder. Claim 21 delete Claim 22 A gas turbine comprising: a compressor that sucks in and compresses external air; a combustor that mixes fuel with the air compressed by the compressor and burns it; and a turbine in which a turbine blade and a turbine vane are mounted inside a turbine casing, and the turbine blade rotates by combustion gas discharged from the combustor, wherein the airfoil of the turbine blade and the turbine vane includes: a cooling passage cavity formed in the inner rear edge of the airfoil; and a plurality of fin-fin cooling structures formed to be in contact with one side and the other side of the cooling passage cavity, wherein the fin-fin cooling structures include a cooling fin connected to one side and the other side of the cooling passage cavity, and a pair of guide fins formed to surround the cooling fin and spaced apart by a predetermined distance on both sides of the cooling fin, wherein the cooling fin is formed in a cylindrical shape and the guide fin is formed in an arc-shaped rib shape and arranged within a predetermined angle range from the center of the cylinder. Claim 23 delete

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