Pin-fin cooling structures for turbine components and gas turbines including them

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

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[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. Further, 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 motion mechanism like a piston of a four-stroke engine, so there is no mutual friction part like a piston-cylinder, the consumption of lubricating oil is extremely small, the amplitude, which is a characteristic of a reciprocating machine, is significantly reduced, and there is an advantage that high-speed movement is possible.

[0008] To briefly explain the operation of a gas turbine, compressed air from a compressor is mixed with fuel and burned to produce high-temperature combustion gases, which are then injected into the turbine. As the injected combustion gases pass through the turbine vanes and blades, they generate rotational force, which causes the rotor to rotate. [Overview of the project] [Problems that the invention aims to solve]

[0009] The present invention aims to provide a pin-fin cooling structure for a turbine component and a gas turbine including the same, which exhibits excellent heat transfer performance by forming a plurality of pin-fin cooling structures in a cooling channel cavity formed inside the turbine component. [Means for solving the problem]

[0010] To achieve the above objective, the present invention provides an airfoil for a turbine blade or turbine vane, comprising a cooling channel cavity formed on the inner trailing edge of the airfoil, and a plurality of pin-fin cooling structures formed to be in contact with one side and the other side of the cooling channel cavity, wherein the pin-fin cooling structures include cooling pins connected to one side and the other side of the cooling channel cavity, and a pair of guide pins formed on both sides of the cooling pins at a predetermined distance apart and surrounding the cooling pins.

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

[0012] The guide pins are 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 positioned to contact one side of the cooling channel cavity, while the upper guide pin is positioned to contact the other side of the cooling channel cavity.

[0013] The pair of guide pins may be positioned 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 between the upstream ends (2b) of the cooling channel is greater than the angle between the downstream ends (2c).

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

[0016] In a second embodiment of the present invention, the cooling pin may be formed in a cylindrical shape, and the guide pin may be formed in an arc-shaped rib that is perpendicular to the direction of airflow and arranged in a predetermined angular range downstream from a plane passing through the center of the cylinder.

[0017] The guide pin may be positioned at an angle (a) of 50 to 65 degrees downstream from the plane passing through the center of the cylinder.

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

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

[0020] In a third embodiment of the present invention, the cooling pin is formed in a cylindrical shape, and the guide pin may include a curved rib portion formed in an arc-shaped form perpendicular to the direction of airflow and arranged in a predetermined angular range downstream from a plane passing through the center of the cylinder, and a downstream extension portion that curves and extends in the opposite direction from an inflection point downstream of the curved rib portion.

[0021] The curved rib portion may 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.

[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 angle 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 on the radially inner side of the airfoil, and an outer end wall formed on the radially outer side of the airfoil. In the turbine vane, end wall cavities are respectively formed inside the inner end wall and the outer end wall, and a plurality of pin-fin cooling structures are formed so as to contact 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 arcuate 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 and compresses external air, a combustor that mixes and burns fuel with the air compressed by the compressor, 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 the 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 so as to contact 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 arcuate rib shape arranged within a predetermined angular range from the center of the cylinder.

Effects of the Invention

[0033] According to the pin-fin cooling structure of the turbine component of the present invention and the gas turbine including it, by configuring a guide pin structure around a circular cooling pin, the wake region and separation zone behind the cooling pin can be eliminated, the airflow can be guided to reduce the secondary flow region, and the flow velocity can be increased by the guide pin structure to improve the heat transfer performance behind the cooling pin. [Brief explanation of the drawing]

[0034] [Figure 1] This is a partially cut perspective view of a gas turbine according to one embodiment of the present invention. [Figure 2] This is a cross-sectional view showing the schematic structure of a gas turbine according to one embodiment of the present invention. [Figure 3] This is a perspective view showing a turbine blade according to one embodiment of the present invention. [Figure 4] This is a perspective view showing a turbine vane according to one embodiment of the present invention. [Figure 5] This is a cross-sectional perspective view showing an airfoil according to one embodiment of the present invention. [Figure 6] This is a partial cross-sectional perspective view showing a cooling channel cavity according to one embodiment of the present invention. [Figure 7A] This is a perspective view showing a pin-fin cooling structure according to a first embodiment of the present invention. [Figure 7B] This is a top view showing a pin-fin cooling structure according to the first embodiment. [Figure 8A] This is a perspective view showing a pin-fin cooling structure according to a second embodiment of the present invention. [Figure 8B] This is a top view showing a pin-fin cooling structure according to the second embodiment. [Figure 9A] This is a perspective view showing a pin-fin cooling structure according to a third embodiment of the present invention. [Figure 9B] This is a top view showing a pin-fin cooling structure according to the third embodiment. [Figure 10A]This is a perspective view showing a pin-fin cooling structure according to a fourth embodiment of the present invention. [Figure 10B] This is a top view showing a pin-fin cooling structure according to the fourth embodiment. [Figure 11A] This figure shows the heat transfer characteristics of a conventional pin-fin cooling structure. [Figure 11B] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to the first embodiment of the present invention. [Figure 11C] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to the first embodiment of the present invention. [Figure 12A] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to a second embodiment of the present invention. [Figure 12B] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to the fourth embodiment of the present invention. [Figure 12C] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to a third embodiment of the present invention. [Figure 12D] This figure shows the heat transfer characteristics of a pin-fin cooling structure according to a third embodiment of the present invention. [Figure 13] This graph shows the heat transfer performance of a pin-fin cooling structure according to the prior art and an embodiment of the present invention. [Modes for carrying out the invention]

[0035] While the present invention can have various embodiments through diverse transformations, specific embodiments will be illustrated and described in detail in the detailed description. However, it should be understood that this does not intend to limit the present invention to specific embodiments, but rather includes all transformations, equivalents, or substitutions that fall within the spirit and technical scope of the present invention.

[0036] The terms used in this invention are used solely 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 “includes” or “having” are intended to specify the existence of features, figures, stages, operations, components, parts, or combinations thereof described in the specification, and should be understood not to preemptively exclude the possibility of the existence or addition of one or more other features, figures, stages, operations, components, parts, or combinations thereof.

[0037] Preferred embodiments of the present invention will be described in detail below with reference to the attached drawings. Note that, in the attached drawings, identical components are represented by the same reference numerals whenever possible. Furthermore, detailed descriptions of known functions and configurations that may obscure the gist of the present invention will be omitted. For similar reasons, some components in the attached drawings are exaggerated, omitted, or shown schematically.

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

[0039] As shown in Figure 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 comprises a plurality of radially arranged blades 1110. The compressor 1100 rotates the blades 1110, and air is compressed and moved by the rotation of the blades 1110. The size and installation angle of the blades 1110 can be changed depending on the installation position. In one embodiment, the compressor 1100 can be directly or indirectly connected to the turbine 1300 and can receive a portion of the power generated by the turbine 1300 and use it to rotate the blades 1110.

[0040] 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 manner and a fuel nozzle module 1220.

[0041] As shown in Figure 2, a gas turbine 1000 according to one embodiment of the present invention is equipped with a housing 1010, and a diffuser 1400 is provided on the rear side of the housing 1010 to discharge the combustion gas that has passed through the turbine. A combustor 1200 is positioned in front of the diffuser 1400 to receive compressed air and burn it.

[0042] To explain using the direction of airflow as a reference, the compressor section 1100 is located upstream of the housing 1010, and the turbine section 1300 is positioned downstream. Between the compressor section 1100 and the turbine section 1300, a torque tube unit 1500 is positioned as a torque transmission member that transmits the rotational torque generated in the turbine section 1300 to the compressor section 1100.

[0043] The compressor section 1100 is equipped with a plurality (for example, 14) of compressor rotor discs 1120, and each of the compressor rotor discs 1120 is fastened by tie rods 1600 so as not to separate in the axial direction.

[0044] Specifically, each of the compressor rotor discs 1120 is aligned axially with respect to each other, with a tie rod 1600, which constitutes the rotation axis, passing through approximately the center of each disc. Here, adjacent compressor rotor discs 1120 are positioned so that their opposing surfaces are pressed together by the tie rod 1600, making relative rotation impossible.

[0045] Multiple blades 1110 are radially connected to the outer circumferential surface of the compressor rotor disk 1120. Each blade 1110 is fastened to the compressor rotor disk 1120 and is equipped with a dovetail portion 1112.

[0046] Between each of the rotor discs 1120, there are vanes (not shown) fixed to the housing. Unlike the rotor discs, the vanes are fixed so as not to rotate and serve to align the flow of compressed air that has passed through the blades of the compressor rotor discs, guiding the air to the blades of the rotor disc located downstream.

[0047] The fastening method for the dovetail portion 1112 can be tangential or axial. This can be selected according to the required structure of the commercial gas turbine and can have the commonly known dovetail or fir-tree shape. In some cases, the blades can be fastened to the rotor disk using other fastening devices other than those described above, such as fasteners such as keys or bolts.

[0048] The tie rod 1600 is positioned to penetrate the centers of the plurality of compressor rotor discs 1120 and turbine rotor discs 1320, and the tie rod 1600 may consist of one or more tie rods. One end of the tie rod 1600 is fastened into the compressor rotor disc located on the upstream side, and the other end of the tie rod 1600 is fastened by a fixing nut 1450.

[0049] The form of the tie rod 1600 can consist of various structures depending on the gas turbine, and is not necessarily limited to the form shown in Figure 2. That is, as shown in the figure, it may have a form in which one tie rod penetrates the center of the rotor disc, or it may have a form in which multiple tie rods are arranged around the circumference, or a combination of these is also possible.

[0050] Although not shown in the diagram, a gas turbine compressor may have vanes that act as guide vanes located after the diffuser to adjust the fluid flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the fluid pressure; these are called deswirlers.

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

[0052] The combustors constituting the combustion system of a gas turbine may be arranged in multiples within a housing formed in a cell shape, and may consist of a burner including fuel injection nozzles, a combustor liner that forms a combustion chamber, and a transition piece that connects the combustor to the turbine.

[0053] Specifically, the liner provides a combustion space in which fuel injected by a fuel nozzle is mixed with compressed air from a compressor and burned. Such a liner may include a flame tube that provides a combustion space in which the fuel mixed with air is burned, and a flow sleeve that surrounds the flame tube and forms an annular space. A fuel nozzle is coupled to the front end of the liner, and a spark plug is coupled to the side wall.

[0054] Meanwhile, a transition piece is connected to the rear end of the liner to allow combustion gases, which are burned by the spark plug, to be sent to the turbine. The outer wall of such a transition piece is cooled by compressed air supplied from the compressor to prevent damage from the high temperature of the combustion gases.

[0055] For this purpose, the transition piece is provided with cooling holes that allow air to be injected into it. The compressed air cools the main body inside through the holes before flowing towards the liner.

[0056] Cooling air, which has cooled the transition piece described above, flows through the annular space of the liner, and compressed air provided outside the flow sleeve as cooling air can collide with the outer wall of the liner through cooling holes provided in the flow sleeve.

[0057] Meanwhile, the high-temperature, high-pressure combustion gases discharged from the combustor are supplied to the turbine 1300 described above. The supplied high-temperature, high-pressure combustion gases expand and collide with the turbine blades, generating a reaction force and producing rotational torque. This rotational torque is transmitted to the compressor via the torque tube described above, and any 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 that of a compressor. That is, the turbine 1300 is also equipped with a plurality of turbine rotor discs 1320 similar to the compressor rotor disc of a compressor. Therefore, the turbine rotor discs 1320 also include a plurality of turbine blades 1340 arranged radially. The turbine blades 1340 can also be coupled to the turbine rotor discs 1320 by a method such as a dovetail. In addition, turbine vanes 1330 fixed to the housing are provided between the blades 1340 of the turbine rotor discs 1320 to guide the flow direction of the combustion gases that have passed through the blades.

[0059] Figure 3 is a perspective view showing a turbine blade according to one embodiment of the present invention. Unlike Figure 2, Figure 3 shows the drawing number "100" on the turbine blade.

[0060] The turbine blade 100 includes an airfoil 110 at its upper end that rotates due to the pressure of the combustion gases, a platform portion 120 integrally formed at the lower part of the airfoil, and a root portion 130 integrally formed at the lower part of the platform portion and coupled to the turbine rotor disk 1320. An inlet may be formed inside the platform portion 120 for supplying cooling fluid to an internal flow path formed inside the airfoil 110.

[0061] The airfoil 110 includes an intake surface 112 that bulges outward on one side into which combustion gases flow, and a pressure surface 111 that is recessed on the opposite side of the intake surface. The front corner where the pressure surface 111 and the intake surface 112 meet constitutes a leading edge 113, and the rear corner forms a trailing edge 114. An internal flow path (not shown) may be formed inside the airfoil 110 through which cooling air flowing in through the inlet flows.

[0062] The platform portion 120 plays a role in maintaining the spacing between adjacent turbine blades by having the platform portion 120 and its side surface come into contact with each other.

[0063] The root portion 130 may have an axial-type configuration, being inserted along the axial direction of the turbine rotor disc into a coupling slot formed on the outer circumferential surface of the turbine rotor disc 1320. The root portion 130 may have a substantially dovetail or fir tree-shaped bend, which may be formed to correspond to the shape of the bend formed in the coupling slot.

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

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

[0066] The airfoil 210 of the turbine vane 200, like the airfoil 110 of the turbine blade 100, includes a recessed pressure surface 211, an outwardly bulging intake surface 212, a leading edge 213, and a trailing edge 214.

[0067] The inner end wall 220 is integrally formed radially inward of the airfoil 210 and can be fixed within the turbine housing. An airflowable endwall cavity 225 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 inside the endwall cavity 225 around the junction with the airfoil 210.

[0068] The outer end wall 230 is integrally formed radially outward of the airfoil 210 and can be fixed to the turbine housing. An end wall cavity 235 is also formed inside the outer end wall 230, and although not shown in Figure 4, multiple pin-fin cooling structures 300 may be formed in the end wall cavity 235.

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

[0070] The airfoil 110 may include a cooling channel cavity 150 formed at its inner trailing edge and a plurality of pin-fin cooling structures 300 formed to be in contact with one side and the other side of the cooling channel cavity.

[0071] The cooling channel cavity 150 is formed at the inner trailing edge of the airfoil 110, allowing cooling air to flow towards the trailing edge 114.

[0072] Multiple pin-fin cooling structures 300 can be integrally connected in a columnar shape from one side to the other of the cooling channel cavity 150. The pin-fin cooling structures 300 may be composed of pin-shaped fins. Multiple pin-fin cooling structures 300 may be arranged in alternating even and odd rows.

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

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

[0075] Figure 6 shows a simplified representation of the case where the upper and lower surfaces of the cooling channel cavity 150 are parallel planes. However, in reality, as shown in Figure 5, the cooling channel cavity 150 can be formed as a curved surface with one side and the other side inclined relative to each other. Furthermore, the pin-fin cooling structure 300 shown in Figure 6 corresponds to the first embodiment.

[0076] The cooling pin 310 is formed in a cylindrical shape, and the upper and lower surfaces of the cylinder can be integrally formed to connect to one side and the other side of the cooling channel cavity 150.

[0077] A pair of guide pins 320 may be formed on either side of the cooling pin 310 at a predetermined distance apart, surrounding the cooling pin. The pair of guide pins 320 can 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 pins 320 may be formed in the shape of arcuate ribs positioned within a predetermined angular range from the center of the cylinder. Unlike the cooling pins 310, the guide pins 320 are not formed in a columnar shape, and a total of four may be formed so as to be connected to one side and the other side of the cooling channel cavity 150, respectively, on the upper and lower ends of the cooling pins 310.

[0079] As shown in Figures 7A and 7B, the guide pins 320 may be formed to have a height (h) of 1 / 3 to 1 / 6 of the diameter (D) of the cooling pins 310, with the lower guide pin 320 in contact with one side of the cooling channel cavity and the upper guide pin 320 in contact with the other side 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 approximately 16.7% to 33.3% of the diameter (D) or height (H) of the cooling pin 310.

[0081] A pair of guide pins 320 may be positioned 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 angle (a) of the arcuate rib of the guide pin 320 may be formed at 90 degrees.

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

[0083] When a straight line passing through the center of the cooling pin 310 in the direction of flow is used as a reference, the guide pin 320 can be positioned such that the angle (b) from the center of the cooling pin 310 to its upstream end is 50 to 70 degrees. In this case, the angle (c) from the straight line passing through the center of the cooling pin 310 in the direction of flow 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) that is 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 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 at a predetermined angle, height, and width, and a pair of semicircular end round portions 322 formed at the upstream and downstream ends of the curved rib portion.

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

[0087] Since a pair of rounded end portions 322 are formed at both ends of the curved rib portion 321, the flowing air can be guided smoothly, and the absence of sharp points prevents damage due to stress concentration.

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

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

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

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

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

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

[0094] The guide pin 320 may be positioned such that the distance (L) from the center of the cylinder to the widthwise center of the guide pin 320 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 widthwise center of the guide pin 320 may be positioned such that it is 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. In other words, 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 located only at the upstream end, the pin-fin cooling structure 300 of the second embodiment can be described as a half guide pin.

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

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

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

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

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

[0102] The downstream extension 325 may be formed to curve outward from the downstream end of the curved rib portion 321 and have a predetermined radius of curvature. The length of the downstream extension 325 may be formed to be 1 / 3 to 1 / 2 times the length of the curved rib portion 321. The radius of curvature of the downstream extension 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 positioned so 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 ends of a pair of curved rib portions 321 may be 180 degrees, and the angle between the downstream ends of a pair of guide pins 320 may be 50 to 80 degrees. The angle between the downstream ends of a pair of downstream extensions 325 may be smaller than the angle between the downstream ends of a pair of guide pins 320.

[0104] The guide pin 320 may be positioned such that the distance (L) from the center of the cylinder to the widthwise center of the guide pin 320 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 widthwise center of the guide pin 320 may be positioned such that it is 2 to 4 times the radius of the cooling pin 310.

[0105] 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. In other words, 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 located only at the upstream end and are horseshoe-shaped, the pin-fin cooling structure 300 of the third embodiment can be described as a half-horseshoe guide pin.

[0107] Figure 10A is a perspective view showing a pin-fin cooling structure according to the fourth embodiment of the present invention, and Figure 10B is a top view showing a 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 and the other side of the cooling channel cavity 150, and a pair of guide pins 320 formed on both sides of the cooling pins at a predetermined distance apart and surrounding the cooling pins.

[0109] The cooling pin 310 is formed in a cylindrical shape, and the guide pin 320 may include a curved rib portion 321 formed in an arc-shaped form perpendicular to the direction of airflow and positioned within a predetermined angular range downstream 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 that curves and extends in the opposite direction from the inflection point downstream 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 positioned perpendicular to the direction of airflow and meets a plane passing through the center of the cylinder, while the downstream end of the curved rib portion 321 may be positioned at a predetermined angle (a) from the plane with respect to the center of the cylinder.

[0112] The upstream extension 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 325 may be formed to curve outward from the downstream end of the curved rib portion 321 and have a predetermined radius of curvature. The length of the downstream extension 325 may be formed to be 1 / 3 to 1 / 2 times the length of the curved rib portion 321. The radius of curvature of the downstream extension 325 may be formed to be smaller than the radius of curvature of the curved rib portion 321.

[0114] The curved rib portion 321 may be positioned so 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 ends of a pair of curved rib portions 321 may be 180 degrees, and the angle between the downstream ends of a pair of guide pins 320 may be 50 to 80 degrees. The angle between the downstream ends of a pair of downstream extensions 325 may be smaller than the angle between the downstream ends of a pair of guide pins 320.

[0115] The upstream extension 326 may be positioned at an angle (b) of 20 to 40 degrees extending upstream from the plane passing through the center of the cylinder. This allows the angle between the upstream ends of a pair of upstream extensions 326 to be 100 to 140 degrees.

[0116] The guide pin 320 may be positioned such that the distance (L) from the center of the cylinder to the widthwise center of the guide pin 320 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 widthwise center of the guide pin 320 may be positioned such that it is 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. In other words, 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 horseshoe-shaped, the pin-fin cooling structure 300 of the fourth embodiment can be called a horseshoe guide pin.

[0119] Figure 11A shows the heat transfer characteristics of a conventional pin-fin cooling structure, Figures 11B and 11C show the heat transfer characteristics of a pin-fin cooling structure according to the first embodiment of the present invention, Figures 12A to 12D show the heat transfer characteristics of pin-fin cooling structures according to the second to fourth embodiments of the present invention, and Figure 13 is a graph showing the heat transfer performance of a conventional pin-fin cooling structure and an embodiment of the present invention.

[0120] In Figure 11A, the conventional pin-fin structure consists only of cylindrical cooling pins arranged alternately in rows. Figures 11B and 11C show a pin-fin cooling structure according to the first embodiment of the present invention, which includes cooling pins and two pairs of guide pins. Figure 11B shows the case where the width (w) of the arc-shaped rib guide pins is 1 / 6 of the height of the cooling pins, and Figure 11C shows the case where the width (w) of the guide pins is 1 / 3 of the height of the cooling pins.

[0121] Figure 12A shows the half guide fin model of the second embodiment, Figure 12B shows the horseshoe guide fin model of the fourth embodiment, Figure 12C shows the detailed flow structure of the half horseshoe guide fin model of the third embodiment when the angle (a) of the curved rib portion 321 is 57.5 degrees, and Figure 12D shows the detailed flow structure when the angle (a) is 55 degrees.

[0122] In the case of conventional pin-fin technology, an increase in heat transfer due to collisions upstream of the circular pin and a decrease in heat transfer due to vortices downstream are frequently observed.

[0123] According to the pin-fin cooling structure of the present invention, by utilizing the guide pin structure around the circular pin, heat transfer upstream of the circular pin can be further improved, and vortices and separation regions in the downstream portion where the amount of heat transfer is small can be eliminated, thereby contributing to an increase in average heat transfer.

[0124] As shown in Figure 13, it can be confirmed that the pin-fin cooling structure of the present invention improves heat transfer performance by more than 40% compared to the conventional technology.

[0125] According to the pin-fin cooling structure for turbine components of the present invention and the gas turbine including it, by configuring a guide pin structure around a circular cooling pin, the wake region and separation zone behind the cooling pin can be eliminated, the airflow can be guided to reduce the secondary flow region, and the flow velocity can be increased by the guide pin structure to improve the heat transfer performance behind the cooling pin.

[0126] Although one embodiment of the present invention has been described above, a person with ordinary skill in the art can modify and change the present invention in various ways by adding, changing, deleting, or adding components, without departing from the spirit of the invention as described in the claims, and this is also included within the scope of the rights of the present invention. [Explanation of symbols]

[0127] 1000: Gas turbine, 1010: Housing 1100: Compressor, 1110: Blade 1112: Dovetail section, 1120: Compressor rotor disc 1200: Combustor, 1210: Combustion chamber 1220: Fuel nozzle module 1300: Turbine, 1320: Turbine rotor disc 1330: Turbine vanes, 1340: Turbine blades 1400: Diffuser, 1450: Fixing nut 1500: Torque tube unit, 1600: Tie rod 100: Turbine blades, 110: Airfoils 111: Pressure surface, 112: Intake surface 113: Leading edge, 114: Trailing edge 120: Platform section, 130: Route section 150: Cooling flow path cavity 200: Turbine vane, 210: Airfoil 211: Pressure surface, 212: Intake 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 section 322: Rounded end section, 323: Flat end section 325: Downstream extension, 326: Upstream extension

Claims

1. In the airfoil of a turbine blade or turbine vane, A cooling channel cavity formed at the inner trailing edge of the airfoil, It includes a plurality of pin-fin cooling structures formed so as to be in contact with one side and the other side of the cooling channel cavity, The plurality of pin-fin cooling structures are, Cooling pins connected to one side and the other side of the cooling channel cavity, An airfoil including a pair of guide pins formed in an arc-shaped rib form so as to surround the cooling pins within a predetermined angular range, spaced a predetermined distance apart on both sides of the cooling pins.

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

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. The airfoil according to claim 2, wherein the lower guide pin is arranged to contact one side of the cooling passage cavity, and the upper guide pin is arranged to contact the other side of the cooling passage cavity.

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

5. The airfoil according to claim 4, wherein the pair of guide pins are arranged such that the angle between the upstream ends (2b) of the cooling channel is greater than the angle between the downstream ends (2c).

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

7. The cooling pin is formed in the shape of a cylinder, The airfoil according to claim 1, wherein the guide pins are perpendicular to the direction of airflow and are formed in the shape of arc-shaped ribs arranged downstream from a plane passing through the center of the cylinder within the predetermined angular range.

8. The airfoil according to claim 7, wherein the guide pin is positioned downstream from a plane passing through the center of the cylinder at an angle (a) of 50 to 65 degrees.

9. The airfoil according to claim 8, wherein the guide pins are arranged such that the distance (L) from the center of the cylinder to the widthwise center of the guide pin is 1.0 to 2.0 times the diameter (D) of the cooling pin.

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

11. The cooling pin is formed in the shape of a cylinder, The aforementioned guide pin is A curved rib portion formed in the shape of an arc-shaped rib, perpendicular to the direction of airflow and arranged in the predetermined angular range downstream from a plane passing through the center of the cylinder, The airfoil according to claim 1, further comprising a downstream extension that is bent and extended in the opposite direction from the inflection point downstream of the curved rib portion.

12. The airfoil according to claim 11, wherein 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.

13. The airfoil according to claim 12, wherein the guide pins are arranged such that the distance (L) from the center of the cylinder to the widthwise center of the guide pin is 1.0 to 2.0 times the diameter (D) of the cooling pin.

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

15. The cooling pin is formed in the shape of a cylinder, The aforementioned guide pin is A curved rib portion formed in the shape of an arc-shaped rib, perpendicular to the direction of airflow and arranged in the predetermined angular range downstream from a plane passing through the center of the cylinder, An upstream extension extending at a predetermined angle from the upstream end of the curved rib portion, The airfoil according to claim 1, further comprising a downstream extension that is bent and extended in the opposite direction from the inflection point downstream of the curved rib portion.

16. The airfoil according to claim 15, wherein the curved rib portion is 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.

17. The airfoil according to claim 16, wherein the upstream extension is positioned at an angle of 20 to 40 degrees upstream from a plane passing through the center of the cylinder.

18. The airfoil according to claim 16 or 17, wherein the guide pins are arranged such that the distance (L) from the center of the cylinder to the widthwise center of the guide pins is 1.0 to 2.0 times the diameter (D) of the cooling pins.

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

20. A turbine vane comprising an airfoil, an inner end wall formed radially inward of the airfoil, and an outer end wall formed radially outward of the airfoil, The end wall cavities formed inside the inner end wall and the outer end wall, respectively, It includes a plurality of pin-fin cooling structures formed so as to be in contact with one side and the other side of the end wall cavity, The plurality of pin-fin cooling structures are, Cooling pins connected to one side and the other side of the end wall cavity, A turbine vane including a pair of guide pins formed in an arc-shaped rib form so as to surround the cooling pins within a predetermined angular range, spaced a predetermined distance apart on both sides of the cooling pins.

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

22. A compressor that takes in outside air and compresses it, A combustor that mixes fuel with the air compressed by the aforementioned compressor and burns it, In a gas turbine, which includes a turbine in which turbine blades and turbine vanes are mounted inside a turbine casing, and the turbine blades are rotated by combustion gases discharged from the combustor, The airfoils of the turbine blades and turbine vanes are A cooling channel cavity formed at the inner trailing edge of the airfoil, It includes a plurality of pin-fin cooling structures formed so as to be in contact with one side and the other side of the cooling channel cavity, The plurality of pin-fin cooling structures are, Cooling pins connected to one side and the other side of the cooling channel cavity, A gas turbine including a pair of guide pins formed in an arc-shaped rib form so as to surround the cooling pins within a predetermined angular range, spaced a predetermined distance apart on both sides of the cooling pins.

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

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