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

Abstract

To provide a pin-collision jet cooling structure for a turbine component and a gas turbine including the same.SOLUTION: An air foil for a turbine blade or a turbine vane includes: a cooling flow passage cavity formed inside the air foil; an insert inserted into the cooling flow passage cavity and having a plurality of cooling holes; and a cooling structure formed between an outer surface of the insert and an inner surface of the cooling flow passage cavity. The cooling structure includes: support parts each coming into close contact with the outer surface of the insert and having a plurality of collision jet holes communicating with the plurality of cooling holes; and cooling pins each coupled to a space between a lower surface of the support part and the inner surface of the cooling flow passage cavity.SELECTED DRAWING: Figure 7

Description

Technical Field

[0001] The present invention relates to a pin-impinging jet 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 central portions 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 while each blade is connected, a drive shaft such as a generator is connected to the end on the exhaust chamber side.

[0007] Such a gas turbine has no reciprocating mechanism like a piston in 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 it has the merit of enabling high-speed movement.

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

Summary of the Invention

Problems to be Solved by the Invention

[0009] An object of the present invention is to provide a pin-impingement jet cooling structure for a turbine component and a gas turbine including the same, which can reduce the cross-flow of impingement cooling air and improve the cooling efficiency by forming a plurality of support portions and cooling pins in an impingement cooling flow path of an airfoil.

Means for Solving the Problems

[0010] To achieve the above object, the airfoil of a turbine blade or turbine vane of the present invention includes a cooling flow path cavity formed inside the airfoil, an insert inserted inside the cooling flow path cavity and including a plurality of cooling holes, and a cooling structure formed between an outer surface of the insert and an inner surface of the cooling flow path cavity. The cooling structure includes a support portion that is in close contact with the outer surface of the insert and includes a plurality of impingement jet holes communicating with the plurality of cooling holes, and a cooling pin connected between a lower surface of the support portion and the inner surface of the cooling flow path cavity.

[0011] The support portion may be formed in a circular disk shape with a predetermined thickness.

[0012] The plurality of impingement jet holes may include one first jet hole disposed upstream of the cooling pin and a pair of second jet holes disposed downstream of the cooling pin.

[0013] When the diameter of the plurality of collision jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

[0014] The support portion may be formed in a triangular disk shape with a predetermined thickness whose vertex is rounded.

[0015] The plurality of collision jet holes may include one first jet hole disposed upstream of the cooling pin and a pair of second jet holes disposed downstream of the cooling pin.

[0016] When the diameter of the plurality of collision jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

[0017] The support portion may be formed in an arc-shaped curved surface shape whose side surrounds the plurality of collision jet holes and the cooling pin.

[0018] The plurality of collision jet holes may include one first jet hole disposed upstream of the cooling pin and a pair of second jet holes disposed downstream of the cooling pin.

[0019] When the diameter of the plurality of collision jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

[0020] The gas turbine of the present invention includes a compressor that sucks and compresses external air, a combustor that mixes fuel with the air compressed by the compressor and burns the mixture, a turbine blade and a turbine vane mounted inside a turbine casing, and a turbine that rotates the turbine blade by combustion gas discharged from the combustor. In the gas turbine, the airfoils of the turbine blade and the turbine vane include a cooling flow path cavity formed inside the airfoil, an insert inserted into the cooling flow path cavity and including a plurality of cooling holes, and a cooling structure formed between the outer surface of the insert and the inner surface of the cooling flow path cavity. The cooling structure includes a support portion that is in close contact with the outer surface of the insert and includes a plurality of impingement jet holes communicating with the plurality of cooling holes, and a cooling pin connected between the lower surface of the support portion and the inner surface of the cooling flow path cavity.

[0021] The support portion may be formed in a circular disk shape with a predetermined thickness.

[0022] The plurality of impingement jet holes may include one first jet hole disposed upstream of the cooling pin and a pair of second jet holes disposed downstream of the cooling pin.

[0023] When the diameter of the plurality of impingement jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

[0024] The support portion may be formed in a triangular disk shape with a predetermined thickness and a rounded vertex.

[0025] The plurality of impingement jet holes may include one first jet hole disposed upstream of the cooling pin and a pair of second jet holes disposed downstream of the cooling pin.

[0026] When the diameter of the plurality of impinging jet holes is d, the height (z) of the cooling pins in the jet direction may be formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

[0027] The support portion may be formed in an arcuate curved surface shape whose side surrounds the plurality of impinging jet holes and the cooling pins.

[0028] The plurality of impinging jet holes may include one first jet hole disposed upstream of the cooling pins and a pair of second jet holes disposed downstream of the cooling pins.

[0029] When the diameter of the plurality of impinging jet holes is d, the height (z) of the cooling pins in the jet direction may be formed to be 2 to 4 times d, and the thickness (t) of the support portion may be formed to be 2 to 4 times d.

Advantages of the Invention

[0030] According to the pin-impinging jet cooling structure of the turbine component of the present invention and the gas turbine including the same, by forming a plurality of support portions and cooling pins in the impinging cooling flow path of the airfoil, the cross flow of the impinging cooling air can be reduced, and the cooling efficiency can be improved.

Brief Description of the Drawings

[0031]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Figure 10

Embodiments for Carrying Out the Invention

[0032] The present invention can have various embodiments with various transformations added, but specific embodiments are exemplified 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 transformations, equivalents, or alternatives included in the spirit and technical scope of the present invention.

[0033] The terms used in the present invention are merely used to describe specific embodiments and are not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In the present invention, terms such as "including" or "having" are intended to specify the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, and it should be understood that the presence or addition of one or more other features, numbers, steps, operations, components, parts, or combinations thereof is not precluded in advance.

[0034] Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. At this time, in the accompanying drawings, note that the same components are represented by the same reference numerals as much as possible. In addition, detailed descriptions of known functions and configurations that may obscure the gist of the present invention are omitted. For the same reason, some components in the accompanying drawings are exaggerated, omitted, or shown schematically.

[0035] FIG. 1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention, and FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.

[0036] As shown in FIG. 1, a gas turbine 1000 according to an embodiment of the present invention includes a compressor 1100, a combustor 1200, and a turbine 1300. The compressor 1100 includes a plurality of blades 1110 provided radially. The compressor 1100 rotates the blades 1110, and air moves while being compressed by the rotation of the blades 1110. The size and installation angle of the blades 1110 can be changed according to the installation position. In one embodiment, the compressor 1100 is directly or indirectly connected to the turbine 1300 and can receive a part of the power generated by the turbine 1300 and be used for the rotation of the blades 1110.

[0037] The air compressed by the compressor 1100 moves to the combustor 1200. The combustor 1200 includes a plurality of combustion chambers 1210 arranged annularly and a fuel nozzle module 1220.

[0038] As shown in FIG. 2, a gas turbine 1000 according to an embodiment of the present invention includes a housing 1010, and a diffuser 1400 through which combustion gas that has passed through the turbine is discharged is provided on the rear side of the housing 1010. And a combustor 1200 that receives and burns the compressed air is arranged in front of the diffuser 1400.

[0039] Describing with reference to the air flow direction, the compressor section 1100 is located on the upstream side of the housing 1010, and the turbine section 1300 is arranged on the downstream side. And between the compressor section 1100 and the turbine section 1300, a torque tube unit 1500 is arranged as a torque transmission member that transmits the rotational torque generated in the turbine section 1300 to the compressor section 1100.

[0040] The compressor section 1100 is provided with a plurality (for example, 14) of compressor rotor disks 1120, and each of the compressor rotor disks 1120 is fastened by tie rods 1600 so as not to be axially separated.

[0041] Specifically, each of the compressor rotor disks 1120 is aligned along the axial direction with the tie rods 1600 constituting the rotating shaft passing through substantially the center. Here, the opposing surfaces of adjacent compressor rotor disks 1120 are pressed by the tie rods 1600 and arranged so as not to be relatively rotatable.

[0042] A plurality of blades 1110 are radially coupled to the outer peripheral surface of the compressor rotor disk 1120. Each blade 1110 includes a dovetail portion 1112 and is fastened to the compressor rotor disk 1120.

[0043] Between each of the rotor disks 1120, a vane (not shown) fixed to the housing is located. The vane is fixed so as not to rotate differently from the rotor disk, and serves to align the flow of compressed air passing through the blades of the compressor rotor disk and guide the air to the blades of the rotor disk located on the downstream side.

[0044] The fastening methods of the dovetail portion 1112 include a tangential type and an axial type. These can be selected according to the required structure of a commercial gas turbine and can have a commonly known dovetail or Fir-tree shape. In some cases, the blade can be fastened to the rotor disk using fastening devices other than the above forms, such as fixtures like keys or bolts.

[0045] The tie rod 1600 is arranged to penetrate the central portions of the plurality of compressor rotor disks 1120 and turbine rotor disks 1320, and the tie rod 1600 may be composed of one or more tie rods. One end of the tie rod 1600 is fastened within the compressor rotor disk located on the most upstream side, and the other end of the tie rod 1600 is fastened by a fixing nut 1450.

[0046] The form of the tie rod 1600 can have various structures depending on the gas turbine, and thus is not necessarily limited to the form presented in FIG. 2. That is, as shown in the figure, it may have a form in which one tie rod penetrates the central portion of the rotor disk, or a form in which a plurality of tie rods are arranged on the circumference, or a combination of these is also possible.

[0047] Although not shown, in the compressor of the gas turbine, in order to adjust the flow angle of the fluid entering the inlet of the combustor to the designed flow angle after increasing the pressure of the fluid, vanes that serve as guide vanes may be provided at the position next to the diffuser, and this is called a deswirler.

[0048] In the combustor 1200, the inflowing compressed air is mixed with fuel and burned to produce high-energy high-temperature and high-pressure combustion gas, and the temperature of the combustion gas is increased to the heat resistance limit that the combustor and turbine components can withstand in the isobaric combustion process.

[0049] The combustor that constitutes the combustion system of a gas turbine may be arranged in a plurality within a housing formed in a cell shape, and includes a burner including a fuel injection nozzle and the like, a combustor liner that forms a combustion chamber, and a transition piece that serves as a connection part between the combustor and the turbine.

[0050] Specifically, the liner provides a combustion space in which the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and burned. Such a liner can include a flame tube that provides a combustion space in which the fuel mixed with air is burned, and a flow sleeve that forms an annular space while surrounding the flame tube. Further, a fuel nozzle is coupled to the front end of the liner, and an ignition plug is coupled to the side wall.

[0051] On the other hand, a transition piece is coupled to the rear end of the liner so that the combustion gas burned by the ignition plug can be sent to the turbine side. Such a transition piece has its outer wall cooled by the compressed air supplied from the compressor so as to prevent damage due to the high temperature of the combustion gas.

[0052] For this purpose, the transition piece is provided with holes for cooling so that air can be injected therein, and the compressed air cools the body inside through the holes and then flows to the liner side.

[0053] The cooling air that has cooled the aforementioned transition piece flows in the annular space of the liner, and compressed air is provided as cooling air through the cooling holes provided in the flow sleeve outside the flow sleeve and can collide with the outer wall of the liner.

[0054] On one hand, the high-temperature and high-pressure combustion gas exiting from the combustor is supplied to the above-described turbine 1300. The supplied high-temperature and high-pressure combustion gas collides with the rotating blades of the turbine while expanding, providing a reaction force to generate rotational torque. The rotational torque thus obtained is transmitted to the compressor via the above-described torque tube, and the power exceeding the power required to drive the compressor is used to drive a generator or the like.

[0055] The turbine 1300 is basically similar in structure to a compressor. That is, the turbine 1300 is also provided with a plurality of turbine rotor disks 1320 similar to the compressor rotor disk of the compressor. Therefore, the turbine rotor disk 1320 also includes a plurality of turbine blades 1340 arranged radially. The turbine blades 1340 can also be coupled to the turbine rotor disk 1320 in a manner such as a dovetail. At the same time, turbine vanes 1330 fixed to the housing are also provided between the blades 1340 of the turbine rotor disk 1320 to guide the flow direction of the combustion gas passing through the blades.

[0056] 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 drawing number "100" is displayed on the turbine blade.

[0057] The turbine blade 100 includes an airfoil 110 that rotates by the pressure of the combustion gas at the upper part, a platform part 120 integrally formed at the lower part of the airfoil, and a root part 130 integrally formed at the lower part of the platform part and coupled to the turbine rotor disk 1320. An inlet through which the cooling fluid is supplied to the internal flow path formed inside the airfoil 110 may be formed inside the platform part 120.

[0058] The airfoil 110 includes an intake surface 112 that bulges outward on one side into which combustion gas flows, and a pressure surface 111 that is recessed on the side opposite to the intake surface. The front-side angle where the pressure surface 111 and the intake surface 112 meet constitutes a leading edge 113, and the rear-side angle forms a trailing edge 114. Inside the airfoil 110, an internal flow path (not shown) through which cooling air flowing in through an inlet flows may be formed.

[0059] The platform portion 120 serves to maintain the interval between blades such that the platform portions 120 of adjacent turbine blades and their side surfaces are in contact with each other.

[0060] The root portion 130 can have an axial-type form that is inserted along the axial direction of the turbine rotor disk into a coupling slot formed on the outer peripheral surface of the turbine rotor disk 1320. The root portion 130 has a substantially double-tail shape or a bent portion in the shape of a fir tree, and this may be formed to correspond to the form of the bent portion formed in the coupling slot.

[0061] FIG. 4 is a perspective view showing a turbine vane according to an embodiment of the present invention. In FIG. 4, different from FIG. 2, the drawing number "200" is displayed for the turbine vane.

[0062] The turbine vane 200 can include an airfoil 210 that is fixed between the turbine blades and guides the flow direction of the combustion gas that has passed 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.

[0063] The airfoil 210 of the turbine vane 200, similar to the airfoil 110 of the turbine blade 100, includes a recessed pressure surface 211, a bulging intake surface 212 on the opposite side, a leading edge 213, and a trailing edge 214.

[0064] Inside the airfoil 210, one or more cooling flow path cavities 240 may be formed by being separated by partition walls. The cooling flow path cavity 240 may be formed to be long in the radial direction inside the airfoil 210.

[0065] FIG. 5 is a cross-sectional view showing an airfoil according to an embodiment of the present invention, and FIG. 6 is a cross-sectional view showing a cooling structure arranged between an insert and an outer wall of a cooling flow path cavity.

[0066] In the present invention, the airfoil 110 or 210 of the turbine blade 100 or the turbine vane 200 includes a cooling flow path cavity 140 or 240 formed inside the airfoil, inserts 150 and 250 inserted into the cooling flow path cavity and including a plurality of cooling holes 155, and a plurality of cooling structures 300 formed between the outer surface of the insert and the inner surface of the cooling flow path cavity.

[0067] The cooling flow path cavity 140 or 240 may be partitioned by partition walls inside the airfoil 110 or 210 to form two or more.

[0068] The inserts 150 and 250 may be formed in a shape corresponding to the inner peripheral surface of the cooling flow path cavity 140 or 240 and inserted and mounted inside the cooling flow path cavity 140 or 240. A plurality of cooling holes 155 are formed through the side walls of the inserts 150 and 250, and the cooling air inside the inserts can flow to the outside of the inserts through the plurality of cooling holes 155. Alternatively, the airfoil 110 or 210 may be manufactured such that structures corresponding to the inserts 150 and 250 are integrally formed inside the cooling flow path cavity 140 or 240.

[0069] The cooling structure 300 can be integrally formed so as to be arranged in plurality between the outer surfaces of the inserts 150 and 250 and the inner surfaces of the cooling channel cavities 140 or 240. The plurality of cooling structures 300 are formed so as to be integrally connected between the outer surfaces of the inserts 150 and 250 and the inner surfaces of the cooling channel cavities 140 or 240, guide the cooling air flowing through the plurality of cooling holes 155, and may be arranged to enhance the impingement cooling effect.

[0070] As shown in FIG. 6, the cooling structure 300 may include a support portion 320 that is in close contact with the outer surface of the insert 150 and includes a plurality of impingement jet holes 330 and 340 that communicate with the plurality of cooling holes 155, and a cooling pin 310 that is connected between the lower surface of the support portion and the inner surface of the cooling channel cavity 140.

[0071] The support portion 320 may be formed in a form that surrounds the plurality of impingement jet holes 330 and 340 formed at positions corresponding to the plurality of cooling holes 155 in close contact with the outer surface of the insert 150. The support portion 320 may be formed to have a thickness (t) that is approximately half of the height (h) of the space between the outer surface of the insert 150 and the inner surface of the cooling channel cavity 140.

[0072] The plurality of impingement jet holes 330 and 340 can be formed to penetrate the support portion 320 in the thickness direction before and after the cooling pin 310 with reference to the flow direction of the cooling air.

[0073] The cooling pin 310 can be connected to the substantially central portion of the lower surface of the support portion 320. Also, the lower end of the cooling pin 310 can be integrally connected to the inner peripheral surface of the outer wall 145 of the cooling channel cavity 140.

[0074] The side wall of the insert 150 in which the plurality of cooling holes 155 are formed constitutes a jet plate in the impingement cooling channel, and the inner peripheral surface of the outer wall 145 of the cooling channel cavity 140 can constitute a target surface against which the cooling air impinges.

[0075] Fig. 7(a) is a perspective view showing a cooling structure according to the first embodiment of the present invention, and Fig. 7(b) is a top view showing the cooling structure according to the first embodiment.

[0076] In the cooling structure 300 according to the first embodiment of the present invention, the support portion 320 may be formed in a circular disk shape with a predetermined thickness. A plurality of impinging jet holes 330 and 340 may be formed to penetrate in the longitudinal direction of the cooling pin 310 before and after the cooling pin 310 in the support portion 320.

[0077] The plurality of impinging jet holes 330 and 340 may include one first jet hole 330 disposed upstream of the cooling pin 310 and a pair of second jet holes 340 disposed downstream of the cooling pin.

[0078] The first jet hole 330 and the second jet holes 340 may be formed in a circular hole shape having an inner diameter smaller than the diameter of the cooling pin 310. The first jet hole 330 may be disposed at a predetermined distance upstream from the center of the cooling pin 310 with respect to the flow direction of the cooling air. The pair of second jet holes 340 may be disposed at a predetermined distance downstream from the center of the cooling pin 310. The pair of second jet holes 340 may be formed so as to be separated from each other by a predetermined distance at left and right positions on a straight line passing through the center of the first jet hole 330 and the center of the cooling pin 310. That is, the center of the first jet hole 330 and the centers of the pair of second jet holes 340 may be disposed at the vertex positions of an isosceles triangle.

[0079] As shown in Fig. 7(b), the angle (θ) between the center of the first jet hole 330 and the center of the second jet holes 340 with respect to the center of the cooling pin 310 may be arranged to be 140 to 160 degrees, particularly about 150 degrees. At this time, the pair of second jet holes 340 may be disposed far apart so that the distance between their centers is larger than the outer diameter of the cooling pin 310.

[0080] As shown in FIG. 6, when the diameters of the plurality of collision jet holes 330 and 340 are d, the height (z) in the jet direction of the cooling pin 310 may be formed to be 2 to 4 times d, and the thickness (t) of the support portion 320 may be formed to be 2 to 4 times d.

[0081] The inner diameters (d) of the first jet hole 330 and the second jet hole 340 can be formed to be the same as the cooling holes 155 of the insert 150 that constitutes the jet plate. The inner diameters (d) of the first jet hole 330 and the second jet hole 340 may be formed to be 0.8 to 1.2 mm.

[0082] The height (z) in the jet direction of the cooling pin 310 may be formed to be 2 to 4 times the diameter (d) of the collision jet holes 330 and 340. The thickness (t) of the support portion 320 may be formed to be 2 to 4 times the diameter (d) of the collision jet holes 330 and 340.

[0083] Thereby, the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140 that constitutes the target surface may be formed to be 4 to 8 times the diameter (d) of the collision jet holes 330 and 340. That is, the height (z) of the cooling pin 310 and the thickness (t) of the support portion 320 may be formed to be approximately half of the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140.

[0084] FIG. 8 is a perspective view showing a cooling structure according to a second embodiment of the present invention.

[0085] In the cooling structure 300 according to the second embodiment of the present invention, the support portion 320 may be formed in a triangular disk shape with a predetermined thickness having a rounded vertex. A plurality of collision jet holes 330 and 340 may be formed to penetrate in the longitudinal direction of the cooling pin 310 before and after the cooling pin 310 in the support portion 320.

[0086] The plurality of impinging jet holes 330, 340 can include one first jet hole 330 disposed upstream of the cooling pin 310 and a pair of second jet holes 340 disposed downstream of the cooling pin. The first jet hole 330 and the pair of second jet holes 340 may be formed to be disposed inside the rounded three vertices of the support portion 320. That is, the support portion 320 may surround the three impinging jet holes 330, 340 and may be formed in an isosceles triangle disk shape with rounded vertices.

[0087] The first jet hole 330 and the second jet hole 340 may be formed in a circular hole shape having an inner diameter smaller than the diameter of the cooling pin 310. The first jet hole 330 may be disposed at a predetermined distance upstream from the center of the cooling pin 310 with respect to the flow direction of the cooling air. The pair of second jet holes 340 may be disposed at a predetermined distance downstream from the center of the cooling pin 310. The pair of second jet holes 340 may be formed to be separated by a predetermined distance from the left and right positions of the straight line passing through the center of the first jet hole 330 and the center of the cooling pin 310. That is, the center of the first jet hole 330 and the centers of the pair of second jet holes 340 may be disposed at the vertex positions of an isosceles triangle.

[0088] Referring to FIG. 7(b), the angle (θ) between the center of the first jet hole 330 and the center of the second jet hole 340 with respect to the center of the cooling pin 310 may be arranged to be 140 to 160 degrees, particularly about 150 degrees. At this time, the pair of second jet holes 340 may be disposed far apart so that the distance between their centers is larger than the outer diameter of the cooling pin 310.

[0089] As shown in FIG. 6, when the diameters of the plurality of impinging jet holes 330, 340 are d, the height (z) of the cooling pin 310 in the jet direction may be formed to be 2 to 4 times d, and the thickness (t) of the support portion 320 may be formed to be 2 to 4 times d.

[0090] The inner diameters (d) of the first jet hole 330 and the second jet hole 340 can be formed to be the same as the cooling holes 155 of the insert 150 that constitutes the jet plate. The inner diameters (d) of the first jet hole 330 and the second jet hole 340 may be formed to be 0.8 to 1.2 mm.

[0091] The height (z) of the cooling pin 310 in the jet direction may be formed to be 2 to 4 times the diameter (d) of the collision jet holes 330 and 340. The thickness (t) of the support portion 320 may be formed to be 2 to 4 times the diameter (d) of the collision jet holes 330 and 340.

[0092] As a result, the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140 that constitutes the target surface may be formed to be 4 to 8 times the diameter (d) of the collision jet holes 330 and 340. That is, the height (z) of the cooling pin 310 and the thickness (t) of the support portion 320 may be formed to be approximately half of the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140.

[0093] FIG. 9 is a perspective view showing a cooling structure according to the third embodiment of the present invention.

[0094] In the cooling structure 300 according to the third embodiment of the present invention, the support portion 320 may be formed in an arc-shaped curved surface shape whose side surfaces surround the plurality of collision jet holes 330, 340 and the cooling pin 310. A plurality of collision jet holes 330, 340 may be formed to penetrate in the longitudinal direction of the cooling pin 310 before and after the cooling pin 310 in the support portion 320.

[0095] The plurality of impinging jet holes 330, 340 can include one first jet hole 330 disposed upstream of the cooling pin 310 and a pair of second jet holes 340 disposed downstream of the cooling pin. The first jet hole 330 and the pair of second jet holes 340 may be formed to be disposed inside the rounded three vertices of the support portion 320. That is, the figure connecting the centers of the three impinging jet holes 330, 340 can form an isosceles triangle.

[0096] The contour line of the support portion 320 may be formed in a form in which three arc-shaped curved surfaces surrounding the centers of the three impinging jet holes 330, 340 and having a constant radius of curvature and a pair of arc-shaped curved surfaces surrounding the center of the cooling pin 310 and having a constant radius of curvature are connected to each other.

[0097] The first jet hole 330 and the second jet hole 340 may be formed in a circular hole shape having an inner diameter smaller than the diameter of the cooling pin 310. The first jet hole 330 may be disposed at a predetermined distance upstream from the center of the cooling pin 310 with respect to the flow direction of the cooling air. The pair of second jet holes 340 may be disposed at a predetermined distance downstream from the center of the cooling pin 310. The pair of second jet holes 340 may be formed to be spaced apart from each other by a predetermined distance to the left and right of the straight line passing through the center of the first jet hole 330 and the center of the cooling pin 310. That is, the center of the first jet hole 330 and the centers of the pair of second jet holes 340 may be disposed at the vertex positions of the isosceles triangle.

[0098] Referring to FIG. 7(b) for explanation, the angle (θ) between the center of the first jet hole 330 and the center of the second jet hole 340 with respect to the center of the cooling pin 310 may be arranged to be 140 to 160 degrees, particularly about 150 degrees. At this time, the pair of second jet holes 340 may be disposed far apart so that the distance between their centers is larger than the outer diameter of the cooling pin 310.

[0099] As shown in FIG. 6, when the diameters of the plurality of impinging jet holes 330 and 340 are d, the height (z) in the jet direction of the cooling pin 310 may be formed to be 2 to 4 times d, and the thickness (t) of the support portion 320 may be formed to be 2 to 4 times d.

[0100] The inner diameters (d) of the first jet hole 330 and the second jet hole 340 can be formed to be the same as the cooling holes 155 of the insert 150 that constitutes the jet plate. The inner diameters (d) of the first jet hole 330 and the second jet hole 340 may be formed to be 0.8 to 1.2 mm.

[0101] The height (z) in the jet direction of the cooling pin 310 may be formed to be 2 to 4 times the diameter (d) of the impinging jet holes 330 and 340. The thickness (t) of the support portion 320 may be formed to be 2 to 4 times the diameter (d) of the impinging jet holes 330 and 340.

[0102] As a result, the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140 that constitutes the target surface may be formed to be 4 to 8 times the diameter (d) of the impinging jet holes 330 and 340. That is, the height (z) of the cooling pin 310 and the thickness (t) of the support portion 320 may be formed to be approximately half of the height (h) between the outer surface of the insert 150 and the inner surface of the outer wall 145 of the cooling channel cavity 140.

[0103] FIG. 10 is a photograph showing a comparison of the cooling effects of the cooling structure of the prior art and the present invention.

[0104] In the case of the prior art, only a plurality of cooling holes are formed in the jet plate, and it is a collision cooling channel structure in which a cooling structure such as a cooling pin is not formed.

[0105] In the case of the first embodiment, the support portion of the cooling structure is formed in a circular disk shape.

[0106] In the case of the second embodiment, the support portion of the cooling structure is formed in a round disk shape with the apex of an isosceles triangle surrounding the impinging jet holes.

[0107] In the case of the third embodiment, the support portion of the cooling structure is formed in a shape where arcs surrounding the impinging jet holes and the cooling pins are connected to form its contour line.

[0108] In the case of the prior art, it can be seen that the temperature difference between the upstream and the downstream in the impingement cooling flow path is very large. This is presumably because a large amount of cross-flow of the impingement cooling air occurs, resulting in a decrease in the cooling efficiency.

[0109] On the other hand, according to the cooling structure according to the embodiment of the present invention, it was confirmed that the cross-flow of the impingement cooling air is reduced by about 40% or more compared to the prior art, and the overall cooling efficiency is improved by about 30% or more compared to the prior art.

[0110] As described above, although one embodiment of the present invention has been described, those having ordinary knowledge in the technical field can variously modify and change the present invention by adding, changing, deleting, or adding components without departing from the idea of the present invention described in the claims, and this is also included within the scope of the rights of the present invention.

Explanation of Reference Numerals

[0111] 1000: Gas turbine, 1010: Housing 1100: Compressor, 1110: Blade 1112: Doubletail portion, 1120: Compressor rotor disk 1200: Combustor, 1210: Combustion chamber 1220: Fuel nozzle module 1300: Turbine, 1320: Turbine rotor disk 1330: Turbine vane, 1340: Turbine blade 1400: Diffuser, 1450: Fixed nut 1500: Torque tube unit, 1600: Tie rod 100: Turbine blade, 110: Airfoil 111: Pressure surface, 112: Suction surface 113: Leading edge, 114: Trailing edge 120: Platform part, 130: Root part 140: Cooling flow path cavity, 145: Outer wall 150: Insert, 155: Cooling hole 200: Turbine vane, 210: Airfoil 211: Pressure surface, 212: Suction surface 213: Leading edge, 214: Trailing edge 220: Inner end wall, 230: Outer end wall 240: Cooling flow path cavity, 245: Outer wall 250: Insert 300: Cooling structure 310: Cooling pin, 320: Support part 330: First jet hole, 340: Second jet hole

Claims

1. In an airfoil of a turbine blade or a turbine vane, a cooling flow path cavity formed inside the airfoil; an insert inserted inside the cooling flow path cavity and including a plurality of cooling holes; a cooling structure formed between an outer surface of the insert and an inner surface of the cooling flow path cavity, wherein the cooling structure includes a support portion that is in close contact with the outer surface of the insert and includes a plurality of impingement jet holes communicating with the plurality of cooling holes; an airfoil including cooling pins connected between a lower surface of the support portion and the inner surface of the cooling flow path cavity.

2. The airfoil according to claim 1, wherein the support portion is formed in a circular disk shape having a predetermined thickness.

3. The plurality of impingement jet holes include one first jet hole disposed upstream of the cooling pin; a pair of second jet holes disposed downstream of the cooling pin. The airfoil according to claim 2.

4. When the diameter of the plurality of impingement jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d; the thickness (t) of the support portion is formed to be 2 to 4 times d. The airfoil according to claim 2.

5. The airfoil according to claim 1, wherein the support portion is formed in a triangular disk shape having a predetermined thickness with a rounded vertex.

6. The plurality of impingement jet holes include one first jet hole disposed upstream of the cooling pin; a pair of second jet holes disposed downstream of the cooling pin. The airfoil according to claim 5.

7. When the diameter of the plurality of impingement jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d; the thickness (t) of the support portion is formed to be 2 to 4 times d. The airfoil according to claim 5.

8. The airfoil according to any one of claims 1 to 7, wherein the support portion is formed in an arcuate curved surface shape whose side surface surrounds the plurality of impingement jet holes and the cooling pins.

9. The plurality of impingement jet holes include one first jet hole disposed upstream of the cooling pin; a pair of second jet holes disposed downstream of the cooling pin. The airfoil according to claim 8.

10. When the diameter of the plurality of impingement jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d; The airfoil according to claim 8, wherein the thickness (t) of the support portion is formed to be 2 to 4 times that of d.

11. A compressor that sucks in and compresses external air, A combustor that mixes fuel with the air compressed by the compressor and burns the mixture, In a gas turbine including a turbine having a turbine blade and a turbine vane mounted inside a turbine casing, and the turbine blade being rotated by combustion gas discharged from the combustor, The airfoils of the turbine blade and the turbine vane are A cooling flow path cavity formed inside the airfoil, An insert inserted into the cooling flow path cavity and including a plurality of cooling holes, And a cooling structure formed between the outer surface of the insert and the inner surface of the cooling flow path cavity, The cooling structure is A support portion that adheres to the outer surface of the insert and includes a plurality of impingement jet holes communicating with the plurality of cooling holes, A gas turbine including a cooling pin connected between the lower surface of the support portion and the inner surface of the cooling flow path cavity.

12. The gas turbine according to claim 11, wherein the support portion is formed in a circular disk shape with a predetermined thickness.

13. The plurality of impingement jet holes are One first jet hole disposed upstream of the cooling pin, And a pair of second jet holes disposed downstream of the cooling pin. The gas turbine according to claim 12.

14. When the diameter of the plurality of impingement jet holes is d, The height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times that of d, The gas turbine according to claim 12, wherein the thickness (t) of the support portion is formed to be 2 to 4 times that of d.

15. The gas turbine according to claim 11, wherein the support portion is formed in a triangular disk shape with a predetermined thickness and a rounded vertex.

16. The plurality of impingement jet holes are One first jet hole disposed upstream of the cooling pin, And a pair of second jet holes disposed downstream of the cooling pin. The gas turbine according to claim 15.

17. When the diameter of the plurality of impingement jet holes is d, The height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times that of d, The gas turbine according to claim 15, wherein the thickness (t) of the support portion is formed to be 2 to 4 times that of d.

18. The gas turbine according to any one of claims 11 to 17, wherein the support portion is formed in an arcuate curved surface shape whose side surrounds the plurality of impinging jet holes and the cooling pins.

19. The plurality of impinging jet holes include one first jet hole disposed upstream of the cooling pin, and a pair of second jet holes disposed downstream of the cooling pin, the gas turbine according to claim 18.

20. When the diameter of the plurality of impinging jet holes is d, the height (z) of the cooling pin in the jet direction is formed to be 2 to 4 times d, and the thickness (t) of the support portion is formed to be 2 to 4 times d, the gas turbine according to claim 18.

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