Turbine blade, turbine rotor blade and gas turbine containing these

Abstract

Turbine blade, which includes the following: a side wall (101) configured to form a blade and containing a leading edge (102) and a trailing edge (104); a partition (106) configured to partition an interior of the side wall (101) to form several cooling channels (110, 120) comprising at least one first cooling channel (110); and a metering plate (150) configured to block inlet parts of the multiple cooling channels (110, 120) and containing cooling openings (152, 153; 154, 155, 156, 157) that communicate with corresponding cooling channels (110, 120), the dosing plate (150) comprises: a first cooling opening (152, 153) which is formed in the inlet part of each of the several cooling channels (110, 120), and a second cooling opening (154, 155, 156, 157) which is formed close to the front edge (102) in the inlet part of the first cooling channel (110) which is closest to the front edge (102), so that cooling air drawn in through the second cooling opening (154, 155, 156, 157) cools a front edge area of ​​the side wall (101), wherein the second cooling opening (157) is formed such that it is inclined towards the leading edge (102); and / or wherein the metering plate (150) further comprises a guide (170) which is provided on a top side of a leading edge side of a section defining the second cooling opening (154) and is configured to direct cooling fluid to a leading edge area.

Description

BACKGROUND area

[0001] Devices and methods consistent with exemplary embodiments relate to a turbine blade, a turbine rotor blade, and a gas turbine containing these. Description of the related area

[0002] Turbines are machines that derive rotational force from a driving force or a reaction force using a flow of a pressurized fluid such as steam or gas, and include a steam turbine, which uses steam, a gas turbine, which uses high-temperature combustion gas, etc.

[0003] The gas turbine contains a compressor, a combustion unit, and a turbine. The compressor includes an air inlet into which air is introduced, and several compressor blades and several compressor rotor blades arranged alternately within a compressor casing.

[0004] The combustion device is configured to supply fuel to the air that has been compressed by the compressor and to ignite the fuel mixture using a burner to produce high-pressure and high-temperature combustion gas.

[0005] The turbine contains several turbine blades and several turbine rotor blades arranged alternately within a turbine casing. Furthermore, a rotor is positioned to pass through central sections of the compressor, the combustion unit, the turbine, and an exhaust chamber.

[0006] The rotor is rotatably mounted at both ends by bearings. Several disks are attached to the rotor, and the multiple rotor blades are each coupled to corresponding disks. A generator drive shaft is coupled to one end of the rotor, adjacent to the exhaust chamber.

[0007] A gas turbine has no reciprocating components such as a piston, which is typically found in a four-stroke engine. This means that the gas turbine has no frictional parts like a piston and cylinder, resulting in the advantages of low lubricant consumption and significantly reduced vibration amplitude compared to a piston engine, which exhibits high-amplitude characteristics. Therefore, gas turbines can be driven at high speeds.

[0008] A brief description of how a gas turbine operates is as follows. Air, compressed by the compressor, is mixed with a fuel. The fuel is burned to produce a high-temperature combustion gas, which is then fed to the turbine. The combustion gas passes through the turbine blades and rotor blades, generating a rotational force that turns the rotor.

[0009] Each turbine blade and rotor blade, which has a blade-like shape, contains a leading edge, a trailing edge, a suction side, and a pressure side. An internal structure of the turbine blade and rotor blade has a complex labyrinthine design that forms a cooling system. A cooling circuit within the turbine blade and rotor blade draws in a cooling fluid, such as air from a compressor, and this fluid flows through the tips of the blade and rotor blade. The cooling circuit contains multiple flow paths to maintain constant temperatures across all surfaces of the turbine blade and rotor blade. At least a portion of the fluid passing through the cooling circuit is conveyed over the leading edge, trailing edge, suction side, and pressure side of the turbine blade.

[0010] Several cooling channels, forming the cooling circuit, are integrated into the turbine blade and rotor blade. A metering plate is located at one of the inlets of these cooling channels. Cooling openings corresponding to the respective inlets of the cooling channels are formed in the metering plate.

[0011] Here, a cooling fluid forms strong jets as it passes through the cooling openings of the dosing plate. Because a current stagnation area occurs in the leading edge of the lower part of the plate, the cooling efficiency of this area is reduced.

[0012] Relevant state of the art can be found in the following documents: WO 2017 / 207 924 A1, US 2013 / 0 028 727 A1, US 4 820 123 A, US 2017 / 0 009 590 A1, KR 10 1 770 068 B1, DE 10 2004 037 444 A1, US 8 591 189 B2. SUMMARY

[0013] The task is therefore to specify a turbine blade, a turbine rotor blade and a gas turbine in which the lower end of the leading edge is better cooled.

[0014] Aspects of one or more exemplary embodiments create a turbine blade, a turbine rotor blade and a gas turbine containing these, in which cooling fluid can be sufficiently drawn into a front part of a lower end of a leading edge, thereby improving the cooling performance.

[0015] The problem is solved by the features of the independent claims. Advantageous embodiments are solved in the dependent claims.

[0016] According to one aspect of an exemplary embodiment, a turbine blade is created comprising: a side wall configured to form a blade and comprising a leading edge and a trailing edge; a partition configured to divide an interior of the side wall to form multiple cooling channels; and a metering plate configured to block inlet portions of the multiple cooling channels and comprising cooling orifices communicating with corresponding cooling channels, wherein the metering plate comprises a first cooling orifice formed in the inlet portion of each of the multiple cooling channels and a second cooling orifice formed at a position near the leading edge in the inlet portion of the cooling channel below the multiple cooling channels adjacent to the leading edge.

[0017] Cooling air, drawn in through the second cooling opening, cools a leading edge area of ​​the side wall.

[0018] The first cooling opening can have a rectangular shape and the second cooling opening can have a circular shape.

[0019] The first cooling opening can have a circular or elliptical shape, and the second cooling opening can have a circular or elliptical shape.

[0020] The first cooling opening can have a rectangular shape, and the second cooling opening can also have a rectangular shape.

[0021] The dosing plate may further include a current guide which is provided on the top of a leading edge side of a section defining the second cooling opening and is configured to cool a leading edge area via a conduit using cooling air.

[0022] The second cooling opening is designed so that it is inclined towards the front edge.

[0023] The dosing plate additionally or alternatively includes a guide that is provided on the top side of a leading edge of a section defining the second cooling opening and is configured to direct cooling fluid to a leading edge area.

[0024] According to one aspect of a further exemplary embodiment, a turbine rotor blade is created comprising: a side wall configured to form a blade and comprising a leading edge and a trailing edge; a partition configured to divide an interior of the side wall to form multiple cooling channels; and a metering plate configured to block inlet portions of the multiple cooling channels and comprising cooling orifices communicating with corresponding cooling channels, wherein the metering plate comprises a first cooling orifice formed in the inlet portion of each of the multiple cooling channels and a second cooling orifice formed at a position near the leading edge in the inlet portion of the cooling channel below the multiple cooling channels adjacent to the leading edge.

[0025] Cooling air, drawn in through the second cooling opening, cools a leading edge area of ​​the side wall.

[0026] The first cooling opening can have a rectangular shape and the second cooling opening can have a circular shape.

[0027] The first cooling opening can have a circular, elliptical, or rectangular shape, and the second cooling opening can have a circular, elliptical, or rectangular shape.

[0028] The dosing plate may further include a current guide which is provided on the top of a leading edge side of a section defining the second cooling opening and is configured to cool a leading edge area via a conduit using cooling air.

[0029] The second cooling opening can be designed in such a way that it is inclined towards the front edge.

[0030] The metering plate further includes a guide which is provided on the top side of a leading edge of a section defining the second cooling opening and is configured to direct cooling fluid to a leading edge area.

[0031] According to one aspect of a further exemplary embodiment, a gas turbine is created comprising: a compressor configured to draw in ambient air and compress the air; a combustion device configured to mix the air compressed by the compressor with a fuel and burn a mixture of the fuel and air; and a turbine configured to include a turbine rotor blade and a turbine blade mounted in the turbine such that the turbine rotor blade is rotated by combustion gas discharged from the combustion device, the turbine blade comprising: a side wall configured to form a blade and including a leading edge and a trailing edge; a partition configured to divide an interior of the side wall to form multiple cooling channels;and a metering plate configured to block inlet portions of the multiple cooling channels, and cooling orifices communicating with corresponding cooling channels, wherein the metering plate includes a first cooling orifice formed in the inlet portion of each of the multiple cooling channels, and a second cooling orifice formed at a position near the leading edge in the inlet portion of the cooling channel below the multiple cooling channels adjacent to the leading edge.

[0032] Cooling air drawn in through the second cooling opening can cool a leading edge area of ​​the side wall.

[0033] The dosing plate may further include a current guide which is provided on the top of a leading edge side of a section defining the second cooling opening and is configured to cool a leading edge area via a conduit using cooling air.

[0034] The dosing plate may further include a guide that is provided on the top side of a leading edge of a section defining the second cooling opening and is configured to direct cooling fluid to a leading edge area.

[0035] According to one or more exemplary embodiments, sufficient cooling fluid can be drawn into a front part of a lower end of a leading edge, thereby improving the cooling performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The aspects described above and others will become clearer from the following description of the exemplary embodiments with reference to the accompanying drawings; they show: Fig. 1 a perspective partial exploded view of a gas turbine according to an exemplary embodiment; Fig. 2 a sectional view showing a schematic structure of the gas turbine according to an exemplary embodiment; Fig. 3 a perspective exploded view showing a turbine rotor disk of Fig. 2 represents; Fig. 4A and Fig. 4B Sectional views showing a turbine blade or turbine rotor blade of the related area; Fig. 5A and Fig. 5B Sectional views showing a turbine blade or turbine rotor blade according to an exemplary embodiment; Fig. 6A, Fig. 6B and Fig. 6C Sectional views illustrating exemplary embodiments of a dosing plate; and Fig. 7 to Fig. 9 diagrams illustrating exemplary embodiments of a turbine blade or turbine rotor blade. DETAILED DESCRIPTION

[0037] The terminology used herein serves only to describe certain embodiments and is not intended to limit the scope of disclosure. The singular forms of "a," "an," and "the" are intended to include the plural forms unless the context clearly indicates otherwise. In this disclosure, terms such as "comprise," "contain," and "exhibit" should be interpreted as establishing the presence of such features, integers, steps, processes, elements, components, and / or combinations thereof, not as excluding the presence or the possibility of adding one or more further features, integers, steps, processes, elements, components, and / or combinations thereof.

[0038] Exemplary embodiments are described in detail below with reference to the accompanying drawings. Reference should now be made to the drawings, with the same reference numerals used throughout to denote the same or similar components. Details of known configurations and functions may be omitted to avoid unnecessarily obscuring the main content of this disclosure. For the same reason, some elements are enlarged, omitted, or described schematically in the accompanying drawings.

[0039] Fig. Figure 1 is a perspective partial exploded view of a gas turbine according to an exemplary embodiment. Fig. Figure 2 is a sectional view showing a schematic structure of the gas turbine according to an exemplary embodiment. Fig. Figure 3 is a perspective exploded view showing a turbine rotor disk. Fig. 2 represents.

[0040] With reference to Fig. 1. The gas turbine 1000 can include a compressor 1100, a combustion unit 1200, and a turbine 1300. The compressor 1100, which contains several radially installed rotor blades 1110, rotates the rotor blades 1110, compressing air and moving it through the rotation of the rotor blades 1110. The size and installation angle of each of the rotor blades 1110 can be changed depending on their installation position. The compressor 1100 is coupled to the turbine 1300 directly or indirectly and can receive some of the power generated by the turbine 1300 and use the received power to rotate the rotor blades 1110.

[0041] Air compressed by the compressor 1100 can be moved through the combustion device 1200. The combustion device 1200 can contain several combustion chambers 1210 and several fuel nozzle modules 1220 arranged in a ring shape.

[0042] With reference to Fig. 2. The gas turbine 1000 can include a casing 1010 and a diffuser 1400, which is provided behind the casing 1010 to expel the combustion gas passing through the turbine 1300. The combustion device 1200 is arranged in front of the diffuser 1400 to combust the compressed air supplied to it.

[0043] Based on the airflow direction, the compressor 1100 is arranged upstream and the turbine 1300 is arranged downstream. Additionally, a torsion tube 1500, which serves as a torque transmission element for transferring torque generated by the turbine 1300 to the compressor 1100, is arranged between the compressor 1100 and the turbine 1300.

[0044] The compressor 1100 contains several compressor rotor discs 1120, each of which is fastened by a tie rod 1600 to prevent axial separation in an axial direction of the tie rod 1600.

[0045] For example, the compressor rotor discs 1120 are aligned axially with one another such that the tie rod 1600, which forms a rotating shaft, passes through central sections of the compressor rotor discs 1120. Here, adjacent compressor rotor discs 1120 are arranged such that their facing surfaces are in close contact with each other by being pressed together by the tie rod 1600. Due to this arrangement, the adjacent compressor rotor discs 1120 cannot rotate relative to each other.

[0046] Several rotor blades 1110 are radially coupled to an outer circumferential surface of each of the compressor rotor disks 1120. Each of the rotor blades 1110 includes a dovetail section 1112 by which the rotor blade 1110 is coupled to the compressor rotor disk 1120.

[0047] Several compressor blades are fixedly arranged between all the compressor rotor disks 1120 in the housing 1010. While the compressor rotor disks 1120 rotate together with a turn of the drawbar 1600, the compressor blades, which are attached to the housing 1010, do not rotate. The compressor blades direct the flow of compressed air, which is moved from the front compressor rotor blades 1110 to the rear compressor rotor blades 1110.

[0048] A coupling scheme for the dovetail part 1112 is classified into a tangential type and an axial type. This can be selected depending on the structure of the gas turbine to be used and can have a dovetail or fir-tree shape. In some cases, the compressor rotor blade 1110 can be coupled to the compressor rotor disk 1120 using other types of coupling devices, such as a wedge or a bolt.

[0049] The tie rod 1600 is arranged running through central sections of several compressor rotor disks 1120 and several turbine rotor disks 1320. The tie rod 1600 can be a single or multiple tie rod structure. One end of the tie rod 1600 is coupled to the compressor rotor disk 1120 that is located furthest upstream, and its other end is coupled to a fastening nut 1450.

[0050] It goes without saying that the shape of the drawbar 1600 does not correspond to the example shown in Fig. Figure 2 is limited and can be modified or varied according to one or more exemplary embodiments. For example, a single tie rod can be arranged running through the central sections of the rotor disks, several tie rods can be arranged in a circumferential direction, or a combination thereof is also possible.

[0051] Furthermore, a vane acting as a guide vane can be installed at the rear stage of the compressor 1100 diffuser to adjust the flow angle of a fluid entering the combustion chamber inlet and to increase the fluid pressure. This vane is referred to as a de-swirl vane.

[0052] The combustion device 1200 mixes introduced compressed air with fuel, burns the fuel mixture to produce high-temperature and high-pressure combustion gas, which possesses high energy, and increases the temperature of the combustion gas via an isobaric combustion process to a temperature at which the combustion device and the turbine can exist.

[0053] Several combustion units, comprising the combustion unit 1200, can be arranged in a cell-shaped housing. Each combustion unit contains a burner, which includes a fuel injection nozzle, etc., a combustion unit liner, which forms a combustion chamber, and a transition piece, which serves as a connector between the combustion unit and the turbine.

[0054] The combustion chamber liner creates a combustion chamber in which fuel, expelled from the fuel injector, mixes with compressed air supplied by the compressor and is burned. The combustion chamber liner may include a flame tube to provide the combustion chamber in which the fuel-air mixture is burned, and a flow sleeve to form an annular space enclosing the flame tube. The fuel injector is coupled to a front end of the combustion chamber liner, and a spark plug is coupled to a side wall of the combustion chamber liner.

[0055] The transition piece is connected to the rear of the combustion chamber lining to transfer combustion gas, burned by the spark plug, to the turbine. An outer wall of the transition piece is cooled by compressed air supplied by the compressor to prevent damage to the transition piece from high-temperature combustion gas.

[0056] For this purpose, the transition piece has cooling openings through which compressed air can be fed in. Compressed air cools the interior of the transition piece through the cooling openings and then flows to the combustion chamber lining.

[0057] The compressed air that has cooled the transition piece can flow into an annular space of the combustion device lining and can be supplied as cooling air from the outside of the flow sleeve through the cooling openings formed in the flow sleeve to an outer wall of the combustion device lining.

[0058] The high-temperature, high-pressure combustion gas expelled from the combustion unit 1200 is fed to the turbine 1300. This gas expands and exerts an impact or reaction force on the turbine rotor blades to generate torque. A portion of this torque is transmitted via the torsion tube to the compressor 1100, and the remaining portion, the excess torque, is used to drive the generator or similar equipment.

[0059] The turbine 1300 essentially has a structure similar to that of the compressor 1100. That is, the turbine 1300 can contain several turbine rotor disks 1320, which are similar to the compressor rotor disks 1120 of the compressor 1100. Each turbine rotor disk 1320 contains several turbine rotor blades 1340, which are arranged radially. Each turbine rotor blade 1340 can be coupled to the turbine rotor disk 1320 in a dovetail coupling manner. Additionally, turbine blades, which are attached to the casing 1010, are provided between the turbine rotor blades 1340 of the turbine rotor disk 1320 to guide the flow of combustion gas passing through the turbine rotor blades 1340.

[0060] With reference to Fig. 3 The turbine rotor disk 1320 has an approximately circular plate shape and contains several coupling slots 1322 formed in its outer circumferential surface. Each coupling slot 1322 has a fir-tree-shaped ribbed surface.

[0061] The turbine rotor blade 1340 is coupled to the coupling slot 1322 and contains in its approximately central section a platform part 1341, which has a flat shape. The platform part 1341 has a side surface that comes into contact with a side surface of the platform part 1341 of an adjacent turbine rotor blade in order to maintain a gap between the adjacent blades.

[0062] A root section 1342 is provided under a bottom surface of the platform section 1341. The root section 1342 has an axial structure such that the root section 1342 is inserted into the coupling slot 1322 of the rotor disk 1320 in an axial direction of the rotor disk 1320.

[0063] The root part 1342 has an approximately fir-tree-shaped ribbed section, corresponding to the fir-tree-shaped ribbed surface formed in the coupling slot 1322. It is understood that the coupling structure of the root part 1342 is not limited to a fir-tree shape and can be formed in such a way that it has a dovetail structure.

[0064] A rotor blade section 1343 is formed on the upper surface of the platform section 1331 such that it has an optimized blade shape according to the specifications of the gas turbine. The rotor blade section 1343 has a leading edge that is arranged upstream with respect to the flow direction of the combustion gas, and a trailing edge that is arranged downstream.

[0065] The turbine rotor blade 1340 comes into contact with a high-temperature and high-pressure combustion gas. Because the combustion gas has a high temperature, reaching 1700 °C, a cooling unit is required. For this purpose, the gas turbine contains a cooling passage through which some of the compressed air is drawn from certain sections of the compressor and supplied to the turbine rotor blades.

[0066] The cooling passage can run outside the housing (i.e., an external passage) or through the interior of the rotor disk (i.e., an internal passage), or both external and internal passages can be used. Several layer cooling holes 1344 are formed in a surface of the rotor blade part 1343. The layer cooling holes 1344 communicate with a cooling passage formed in the rotor blade part 1343 to supply cooling air to the surface of the rotor blade part 1343.

[0067] The rotor blade section 1343 is rotated within the housing by combustion gas. A gap is formed between one end of the rotor blade section 1343 and the inner surface of the housing, allowing the rotor blade section 1343 to rotate smoothly. However, because the combustion gas can escape through this gap, a sealing unit is required to prevent this escape.

[0068] Fig. 4A and Fig. 4B are sectional views showing a turbine blade or turbine rotor blade of the related area. Fig. 5A and Fig. Figure 5B are sectional views showing a turbine blade or turbine rotor blade according to an exemplary embodiment.

[0069] Fig. 4A is a longitudinal section view showing a lower part of the turbine blade or turbine rotor blade. Fig. 4B is a sectional view taken along a line AA of Fig. 4A, which runs through a dosing plate 140, was taken.

[0070] With reference to Fig. 4A and Fig. 4B contains a turbine blade or turbine rotor blade 100, a side wall 101, a partition 106, and a metering plate 140. The side wall 101 forms a blade that includes a leading edge 102 and a trailing edge 104. The partition 106 divides an interior space of the side wall 101 to form several cooling channels 110 and 120. The metering plate 140 blocks inlet portions of the several cooling channels 110 and 120 and communicates with each of the cooling channels 110 and 120.

[0071] For example, a concave surface of the blade, formed by the side wall, refers to a pressure surface, and a convex surface refers to a suction surface.

[0072] Although Fig. 4 and Fig. Figure 5 shows an example in which the cooling channel formed in the interior of the side wall 101 is separated by the single partition 106 into two channels containing a first channel 110 and a second channel 120. The cooling channel can be formed in different shapes and the number of cooling channels can be changed to different values, e.g., three to ten.

[0073] The dosing plate 140 is coupled to the inlet parts of the several cooling channels 110 and 120 and cooling openings 142, which correspond to the respective cooling channels, are formed in the dosing plate 140.

[0074] The flow of cooling fluid in the first channel 110, which borders the leading edge 102, is indicated by arrows in Fig. Figure 4A shows that in the related area, cooling fluid is not properly supplied to a leading part of a lower end of the leading edge 102, i.e., section “C”. Therefore, a problem may exist in that section “C” is not adequately cooled.

[0075] On the other hand, the dosing plate contains 150 according to an exemplary embodiment, which is described in Fig. 5A and Fig. Figure 5B shows a first cooling opening 152 formed in the inlet part of each of the multiple cooling channels 110 and 120, and a second cooling opening 154 formed in the inlet part of the cooling channel 110 adjacent to the front edge 102, below the multiple cooling channels, at a position near the front edge.

[0076] Fig. 5A is a longitudinal section view showing a lower part of the turbine blade or turbine rotor blade. Fig. 5B is a sectional view taken along a line BB from Fig. 5A, which runs through a dosing plate 150, was taken.

[0077] Although Fig. 5A is an example that contains the first channel 110 and the second channel 120; the number of cooling channels can be changed.

[0078] With reference to Fig. 5A the inlet part of the second channel 120 contains the single cooling opening 152 and the inlet part of the first channel 110 contains the first cooling opening 152 formed in the inlet part and the second cooling opening 154 formed at a position adjacent to the front edge 102 of the cooling channel 110.

[0079] The first cooling opening 152 of the first channel 110 has the same size as the cooling opening 152 of the second channel 120 and can be located in a central section of the inlet portion of the corresponding channel. Furthermore, the first cooling opening 152 of the first channel 110 can be located slightly to the right, i.e., towards the trailing edge 104, compared to the cooling opening 152 of the second channel 120. The first cooling opening 152 can be slightly smaller than the second cooling opening 152.

[0080] Because the second cooling opening 154 in the dosing plate 150 is formed at a position near an inner surface of the front edge 102, cooling air drawn through the second cooling opening 154 can cool a lower part of the front edge 102 of the side wall 101.

[0081] With reference to Fig. 5B the first cooling opening 152 can have a rectangular shape and the second cooling opening 154 can have a circular shape.

[0082] Both the first channel 110 and the second channel 120 have an elongated, rectangular horizontal cross-section. Therefore, the first cooling opening 152, formed in the inlet section of each channel, can also have a rectangular shape.

[0083] Considering that the inner surface of the front edge 102 has a concave curved surface, the second cooling opening 154 can have a circular shape.

[0084] Fig. 6A, Fig. 6B and Fig. Figure 6C represents one or more exemplary embodiments of the dosing plate 150.

[0085] With reference to Fig. 6A a first cooling opening 152 can have a rectangular shape and a second cooling opening 155 can have an elliptical shape.

[0086] The main axis of the second cooling opening 155 can be arranged in a direction parallel to a short side of the first cooling opening 152.

[0087] Here, the term "ellipse" can include a shape in which a semicircle is joined in one piece to each of the opposite short sides of the rectangle.

[0088] With reference to Fig. 6B can have a first cooling opening 153 in an elliptical shape and a second cooling opening 155 can also have an elliptical shape.

[0089] For example, each corner in the side wall 101 and the partition wall 106 can be rounded with a specified radius of curvature.

[0090] Furthermore, a circumferential cross-section of the turbine blade or turbine rotor blade 100 can have a blade shape that gradually decreases in an area towards its end opposite the metering plate 150.

[0091] Because the second cooling opening 155 and the first cooling opening 153 can have an elliptical shape, the main axis of the second cooling opening 155 can be the same as the main axis of the first cooling opening 153.

[0092] With reference to Fig. 6C can have a first cooling opening 152 in a rectangular shape and a second cooling opening 156 can also have a rectangular shape.

[0093] A long side of the second cooling opening 156 can have the same length as a short side of the first cooling opening 152.

[0094] Fig. 7 to Fig. Figure 9 represents one or more exemplary embodiments of a turbine blade or turbine rotor blade.

[0095] With reference to Fig. 7 The metering plate 150 may further include a current guide 160, which is provided on the upper side of a leading edge side of a section defining the second cooling opening 154, to cool the leading edge area by means of conduction using cooling air.

[0096] The current guide 160 extends on the top of the dosing plate 150 from a front edge side of the second cooling opening 154 to a lower end of the inner surface of the front edge 102.

[0097] The current guide 160 can have a cross-section in the form of a right-angled triangle and can be formed in one piece with the metering plate 150 using metal. The upper surface of the current guide 160 can have a curved surface that is concave upwards.

[0098] Due to the current flow 160, a cooling fluid, i.e., cooling air, which is drawn in through the second cooling opening 154, can be transferred more smoothly to the front edge 102.

[0099] With reference to Fig. 8 the second cooling opening 157 can be formed such that it is inclined towards the front edge 102.

[0100] Because the dosing plate 150 has a predetermined thickness, the second cooling opening 157 in the dosing plate 150 can be formed at an angle inclined to the front edge 102. Cooling fluid drawn in through the second cooling opening 157 can be transferred to the lower end of the inner surface of the front edge 102.

[0101] Therefore, compared to the second cooling opening, 154 of Fig. 5, which penetrates in a vertical direction, the second cooling opening 157 of Fig. 8. Concentrate cooling fluid at the lower end of the inner surface of the leading edge 102, which can further improve the cooling effect of the lower end of the leading edge 102.

[0102] With reference to Fig. 9 The metering plate 150 may further include a guide 170 which is provided on a top side of a trailing edge side of a section defining the second cooling opening 154 to direct cooling fluid to the leading edge 102.

[0103] The guide 170 can be arranged on the top of the dosing plate 150 and extend from a right side of the second cooling opening 154 to the left and upwards.

[0104] The guide 170 directs cooling fluid, which is drawn in via the second cooling opening 154, to the lower end of the inner surface of the leading edge 102, thereby improving the cooling effect of the lower end of the leading edge 102.

[0105] The leadership 170 of Fig. 9 can also refer to the exemplary embodiment of Fig. 7 or Fig. 8 can be applied. In addition, the current flow can be 160 from Fig. 7 and the inclined second cooling opening 157 of Fig. 8 can be used together. The shape of each of the dispensing plates is 150. Fig. 7 to Fig. 9 can also refer to the exemplary embodiments of Fig. 5A to Fig. 6C can be applied.

[0106] In accordance with a turbine blade or turbine rotor blade of the exemplary embodiments, a cooling fluid can be satisfactorily drawn into a front part of a lower end of a leading edge, thereby improving the cooling performance.

Claims

[1] Turbine blade comprising the following: a side wall (101) configured to form a blade and containing a leading edge (102) and a trailing edge (104); a partition (106) configured to partition an interior of the side wall (101) to form several cooling channels (110, 120) comprising at least one first cooling channel (110); and a metering plate (150) configured to block inlet parts of the multiple cooling channels (110, 120) and containing cooling openings (152, 153; 154, 155, 156, 157) that communicate with corresponding cooling channels (110, 120), the dosing plate (150) comprises: a first cooling opening (152, 153) which is formed in the inlet part of each of the several cooling channels (110, 120), and a second cooling opening (154, 155, 156, 157) which is formed close to the front edge (102) in the inlet part of the first cooling channel (110) which is closest to the front edge (102), so that cooling air drawn in through the second cooling opening (154, 155, 156, 157) cools a front edge area of ​​the side wall (101), wherein the second cooling opening (157) is formed such that it is inclined towards the leading edge (102); and / or wherein the metering plate (150) further comprises a guide (170) which is provided on a top side of a leading edge side of a section defining the second cooling opening (154) and is configured to direct cooling fluid to a leading edge area. [2] Turbine blade according to claim 1, wherein the first cooling opening (152) has a rectangular shape and / or the second cooling opening (154) has a circular shape; or wherein the first cooling opening (153) has a circular, elliptical or rectangular shape and / or the second cooling opening (154, 155) has a circular, elliptical or rectangular shape; or wherein the first cooling opening (152) has a rectangular shape and / or the second cooling opening (156) has a rectangular shape. [3] Turbine blade according to claim 1 or 2, wherein the metering plate (150) further comprises a flow guide (160) which is provided on a top side of a leading edge side of a section defining the second cooling opening (154) and is configured to cool a leading edge area via a conduit using cooling air. [4] Turbine rotor blade comprising the following: a side wall (101) configured to form a blade and containing a leading edge (102) and a trailing edge (104); a partition (106) configured to separate an interior space of the side wall (101) to form several cooling channels (110, 120) comprising at least one first cooling channel (110); and a metering plate (150) configured to block inlet parts of the multiple cooling channels (110, 120) and containing cooling openings (152, 153; 154, 155, 156, 157) that communicate with corresponding cooling channels (110, 120), the dosing plate (150) comprises: a first cooling opening (152, 153) which is formed in the inlet part of each of the several cooling channels (110, 120), and a second cooling opening (154, 155, 156, 157) which is formed close to the front edge (102) in the inlet part of the first cooling channel (110) which is closest to the front edge (102), so that cooling air drawn in through the second cooling opening (154, 155, 156, 157) cools a front edge area of ​​the side wall (101), wherein the second cooling opening (157) is formed such that it is inclined towards the front edge (102); and / or wherein the metering plate (150) further comprises a guide (170) which is provided on the upper side of a leading edge side of a section defining the second cooling opening (154) and is configured to direct cooling fluid to a leading edge area. [5] Turbine rotor blade according to claim 4, wherein the first cooling opening (152) has a rectangular shape and / or the second cooling opening (154) has a circular shape; or wherein the first cooling opening (153) has a circular or elliptical or rectangular shape and / or the second cooling opening (154, 155) has a circular or elliptical or rectangular shape; or wherein the first cooling opening (152) has a rectangular shape and / or the second cooling opening (156) has a rectangular shape. [6] Turbine rotor blade according to one of the preceding claims 4 or 5, wherein the metering plate (150) further comprises a flow guide (160) which is provided on a top side of a leading edge side of a section defining the second cooling opening (154) and is configured to cool a leading edge area via a conduit using cooling air. [7] Gas turbine with a turbine blade or a turbine rotor blade, wherein the turbine blade is designed according to one of claims 1 to 3 and / or the turbine rotor blade is designed according to one of claims 4 to 6.

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