Flow machine component for a gas turbine and a gas turbine possessing the same

Abstract

Turbomachinery component (1) for a gas turbine (10), wherein the turbomachinery component (1) comprises the following: - a platform (200) and - a blade (100) extending from the platform (200) and comprising a base part (100b) adjoining the platform (200) and a head part (100a) spaced from the base part (100b) in a longitudinal direction (A) of the blade (100); wherein the blade (100) further comprises: - a pressure side (102) and a suction side (104) that meet at a leading edge (106) and a trailing edge (108) and define an interior (100s) of the blade (100); - at least one web (60) which is arranged in the interior (100s) of the blade (100) and extends between the pressure side (102) and the suction side (104); - at least two cooling channels (70) for the flow of cooling air (5), which are formed in the interior (100s) of the blade (100) and extend in the longitudinal direction (A) of the blade (100) and are defined at least by the web (60) and the pressure side (102) and suction side (104); and - a flow deflector (80) projecting outwards from the web (60) into the cooling channel (70) and shaped in such a way that it deflects at least a part of the cooling air (5) flowing in the longitudinal direction (A) of the blade (100) in the cooling channel (70) to at least one target area (T) on the pressure side (102) and / or on the suction side (104), characterized in that the target area (T) comprises at least one heat transfer improvement element (90), and the flow deflector (80) is shaped such that it deflects the cooling air (5) to the at least one heat transfer improvement element (90) in such a way that the cooling air (5) deflected by the flow deflector (80) directly affects the at least one heat transfer improvement element (90), wherein the flow deflector (80) is configured such that a blocking factor due to the flow deflector (80) is equal to or greater than 0.15, where the blocking factor is defined as follows: Blocking factor = DH , wo − DH , w DH , wo , where D H,wo the hydraulic diameter of the cooling channel (70) without the flow deflector (80) represents and D H,wthe hydraulic diameter of the cooling channel (70) is represented by the flow deflector (80), where the hydraulic diameter (D H,wo ) of the cooling channel (70) without the flow deflector (80) is defined by the following: DH , wo = 4 A wo P wo , where A wo an area of ​​a cross-section of the cooling channel (70) without the flow deflector (80) is represented and P wo represents the circumference of the cross-section of the cooling channel (70) excluding the flow deflector (80); and / or the hydraulic diameter (D H,w ) of the cooling channel (70) with the flow deflector (80) is defined by the following: DH , w = 4 A w P w , where A w an area of ​​a cross-section of the cooling channel (70) with the flow deflector (80) represents and P wrepresents the circumference of the cross-section of the cooling channel (70) with the flow deflector (80).

Description

[0001] The present invention relates to a turbomachine component for a gas turbine and a gas turbine having the same, and more particularly to the cooling of gas turbine blades.

[0002] Turbomachines contain various turbomachine components that benefit from cooling, which results in increased component life.

[0003] WO 2017 / 171 764 A1 shows an airfoil with at least one inner cooling channel extending in the radial direction and being bounded on opposite sides by an airfoil pressure sidewall and an airfoil suction sidewall.

[0004] US 10 533 427 B2 shows a turbine blade with a flow displacement element arranged in an inner portion of a blade body between a pair of adjacent partition walls and having a radially extending elongated main body.

[0005] US 2019 / 0 093 487 A1 shows a turbine blade with a flow-restricting body positioned at an internal cavity.

[0006] US 6 257 831 B1 shows a cooled airfoil of a gas turbine engine comprising a flow deflector adapted to direct a cooling fluid away from an unfilled opening left by a support element of a casting core used in casting the airfoil.

[0007] Certain turbomachinery components have an airfoil, such as a rotor blade or a vane. The airfoils enclose internal spaces and are cooled internally, or from within, by forcing cooling air through the interior of the airfoil or through one or more cooling channels formed within the airfoil.

[0008] The turbomachinery component - also referred to as the rotor blade or bucket - generally comprises the airfoil (also referred to as an airfoil) projecting from a platform.

[0009] The platform is the surface to which the blade is adjacent and from which it projects.

[0010] An airfoil for a working fluid path of a turbomachine extends spanwise from a base portion to a tip portion. An aerodynamic body therefore includes a suction-side surface, a pressure-side surface, a leading edge, and a trailing edge. During operation of the gas turbine, the airfoil of the rotor blade or the blade of the turbine section of the gas turbine is positioned in the hot gas path. The airfoil also contains one or more webs extending from the pressure side to the suction side, thereby creating cooling channels in the interior of the airfoil. They also provide mechanical reinforcement for the airfoil. Depending on the number of webs, the web divides the interior of the airfoil into at least two cooling channels extending in the longitudinal direction of the airfoil.Cooling air generally flows into such cooling channels in the longitudinal direction of the airfoil after being introduced into the airfoil. Improving such internal airfoil cooling will have a beneficial effect on the efficiency of the gas turbine and / or the structural integrity of the airfoil.

[0011] Furthermore, the effects of the thermal loads to which the different regions or parts of the airfoil are subjected during gas turbine operation are not homogeneous. For example, some regions of the airfoil may experience higher stresses than others because they absorb more hot gas flow due to their position or orientation with respect to the hot gas flow, their shape that accommodates the hot gas flow, and / or because they exhibit variations in wall thickness, and / or because they exhibit less localized cooling, etc. Improving the internal cooling of such regions of the airfoil that are prone to experiencing higher thermal loads will also have a beneficial effect on the efficiency of the gas turbine and / or on the structural integrity of the airfoil.

[0012] In addition, to cool gas turbine components, a portion of the air from the compressor section of the gas turbine is taken and used as cooling air, and is directed to different sections of the gas turbine, which may be located at different distances. To achieve appropriate cooling air flow, the cooling air flow in various areas of the turbomachine and also in different areas of turbomachine components must be maintained at optimal pressures. Furthermore, maintaining optimal pressures is important for effective impingement cooling. However, increasing the amount of air taken from the compressor for cooling results in a decrease in the amount of air available for combustion, which can negatively affect the efficiency of the gas turbine.

[0013] Therefore, it is advantageous to improve internal cooling of the airfoil, preferably implementing targeted cooling of desired areas or specific target areas of the airfoil, while at least partially avoiding pressure loss to suboptimal levels.

[0014] The above-mentioned objects are achieved by the subject matter of the independent claim, preferably by a turbomachine component for a gas turbine. Advantageous embodiments of the present technology are provided in the dependent claims. Such turbomachine components that include an airfoil are illustrated below by a rotor blade, but the description is also applicable to other turbomachine components that include an airfoil, such as a blade, unless otherwise stated.

[0015] In a first aspect of the present technology, a turbomachinery component for a gas turbine is presented. The turbomachinery component includes a platform and an airfoil.

[0016] The airfoil extends from the platform. The airfoil includes a base portion adjacent to the platform and a head portion spaced from the base portion in a longitudinal direction of the airfoil.

[0017] The head section is also located on a platform or cover plate, such that blades and shrouded rotor blades are also included.

[0018] The airfoil contains a pressure side and a suction side that meet at a leading edge and a trailing edge. The pressure side, the suction side, the leading edge, and the trailing edge define the interior of the airfoil.

[0019] At least one web is arranged inside the blade. The web extends between the pressure side and the suction side.

[0020] The interior of the airfoil comprises at least two cooling channels for cooling air flow. The cooling channel extends in the longitudinal direction of the airfoil. The cooling channel is defined at least partially by the web and the pressure side and / or the suction side.

[0021] The airfoil includes a flow deflector that projects outward from the web into the cooling channel. The flow deflector is shaped to divert at least a portion of the cooling air flowing longitudinally along the airfoil in the cooling channel to at least one target area on the pressure side and / or the suction side.

[0022] The flow deflector is shaped and / or dimensioned such that a blocking factor due to the flow deflector is equal to or greater than 0.15, wherein the blocking factor may preferably be equal to or greater than 0.2 and equal to or less than 0.5.

[0023] The blocking factor is defined as follows: Blocking factor=DH,wo−DH,wDH,wo, where

[0024] D H,wo represents the hydraulic diameter of the cooling channel without the flow deflector and D H,w represents the hydraulic diameter of the cooling channel with the flow deflector.

[0025] The hydraulic diameter D H,wo of the cooling channel without the flow deflector is defined by the following: DH,wo=4AwoPwo, where

[0026] A wo represents an area of ​​a cross-section of the cooling channel without the flow deflector and P worepresents a circumference of the cross-section of the cooling channel without the flow deflector.

[0027] The hydraulic diameter (D H,w ) of the cooling channel with the flow deflector is defined by the following: DH,w=4AwPw, where

[0028] A w represents an area of ​​a cross-section of the cooling channel with the flow deflector and P w represents a circumference of the cross-section of the cooling channel with the flow deflector. The cooling channel may include an inlet where the base portion of the airfoil meets a top surface of the platform.

[0029] The flow deflector may be confined or limited in the airfoil or may be completely incorporated by spacing it from the inlet of the cooling channel.

[0030] The flow deflector may have an elongated shape and may be oriented to extend between the base portion of the airfoil and the tip portion of the airfoil.

[0031] The turbomachine component of the present technique may include multiple flow deflectors. The flow deflectors may be arranged in an array along the longitudinal direction of the airfoil.

[0032] The flow deflectors can be bar-shaped and / or pin-rib-shaped.

[0033] The target area contains at least one heat transfer enhancement element.

[0034] The heat transfer enhancing element may be a web and / or a pin and / or a recess.

[0035] The flow deflector is shaped to deflect the cooling air toward the at least one heat transfer enhancing element such that the cooling air deflected by the flow deflector directly impacts the at least one heat transfer enhancing element.

[0036] The purpose of the flow deflector is to direct cooling air from one side (e.g. the pressure side) to another side (e.g. the suction side) in order to improve heat transfer on another side (e.g. the suction side).

[0037] The flow deflector can be formed integrally with the web. Alternatively, the flow deflector can be formed as a single unit and then attached to the web.

[0038] The deflector can be connected to the bridge, for example, by brazing or welding.

[0039] The flow deflector may include a base portion adjacent to a surface of the web from which the flow deflector projects outward into the cooling channel, and a head portion spaced from the base portion. The head portion of the flow deflector may be freely suspended, i.e., it does not need to be in direct contact with a wall of the cooling channel or any other structure disposed in the cooling channel, e.g., disposed on the wall of the cooling channel.

[0040] The turbomachinery component may be a rotor blade or a vane. The turbomachinery component may be a rotor blade or a vane of a gas turbine. The turbomachinery component may be a rotor blade of a turbine section of a gas turbine and may be mounted on a rotor disk of the gas turbine.

[0041] In another aspect of the present technique, a gas turbine is presented. The gas turbomachine may include at least one turbomachine component according to the first aspect of the present technique, as described above.

[0042] The above-mentioned characteristics and other features and advantages of the present technique and the manner of achieving them will become more apparent and the present technique itself will be better understood by reference to the following description of embodiments of the present technique in conjunction with the accompanying drawings, in which: Fig. 1 shows a part of a gas turbine in a sectional view and incorporating a turbomachine component of the present technology; Fig. 2 schematically shows a turbomachine arrangement incorporating a turbomachine component of the present technique; Fig. 3A is a vertical cross-sectional view illustrating a conventional rotor blade; Fig. 3B is a horizontal cross-sectional view showing a conventional blade in the conventional rotor blade of Fig. 3A illustrates; Fig. 4A is a vertical cross-sectional view illustrating an exemplary embodiment of a rotor blade of the present technique, illustrating a turbomachine component according to the present technique; Fig. 4B is a horizontal cross-sectional view illustrating an exemplary embodiment of an airfoil of the present technique in the rotor blade of Fig. 4A illustrates; Fig. 5 schematically shows another exemplary embodiment of the airfoil of the present technique, illustrating the operation of the present technique; Fig. 6A is a partial cross-sectional view of an airfoil section without a flow deflector of the present technique; Fig. 6B is a partial cross-sectional view of an airfoil section having a flow deflector of the present technique; and Fig. 7A- Fig. 7M schematically illustrates various exemplary embodiments of the flow deflector of the present technique in accordance with aspects of the present technique.

[0043] The above-mentioned and other features of the present technique are described in detail below. Various embodiments are described with reference to the drawings, wherein like reference numerals are used to refer to similar elements throughout. In the following description, for the purpose of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. It may be noted that the illustrated embodiments are intended to explain the invention and not to limit it. It may be apparent that such embodiments may be practiced without these specific details.

[0044] Fig. 1 shows an example of a gas turbine 10 in a sectional view. The gas turbine 10 may include, in the flow sequence, an inlet 12, a compressor or compressor section 14, a combustor section 16, and a turbine section 18, generally arranged in the flow sequence and generally about and toward a longitudinal axis or rotational axis 20. The gas turbine 10 may further include a shaft 22 rotatable about the rotational axis 20 and extending longitudinally through the gas turbine 10. The shaft 22 may drivingly connect the turbine section 18 to the compressor section 14.

[0045] During operation of the gas turbine 10, air 24 taken in through the air inlet 12 is compressed by the compressor section 14 and transmitted to the combustion section or the combustor section 16. The combustor section 16 may include a combustor chamber 26, one or more combustion chambers 28, and at least one burner 30, each attached to the combustion chamber 28. The combustion chambers 28 and the burners 30 may be located in the combustor chamber 26. The compressed air passing through the compressor 14 may enter a diffuser 32 and may be expelled from the diffuser 32 into the combustor chamber 26, from where a portion of the air may enter the burner 30 and be mixed with a gaseous or liquid fuel. The air / fuel mixture is then combusted and the combustion gas 34 or the working gas from the combustion is passed through the combustion chamber 28 via a transition channel 17 to the turbine section 18.

[0046] This exemplary gas turbine 10 may include a tubular combustor section assembly 16 formed by an annular array of combustor tubes 19, each containing the burner 30 and the combustor 28, with the transition duct 17 having a generally circular inlet interfacing with the combustor 28 and an outlet in the form of an annular segment. An annular array of transition duct outlets may form an annular space for directing the combustion gases to the turbine 18.

[0047] The turbine section 18 may include a plurality of rotor blade support disks 36 attached to the shaft 22. In the present example, two disks 36 are shown, each supporting an annular array of turbine blades 38. However, the number of rotor blade support disks may vary, i.e., only one disk or more than two disks. Additionally, guide vanes 40 attached to a stator 42 of the gas turbine 10 may be arranged between the rows of annular arrays of turbine blades 38. Inlet guide vanes 44 may be provided between the exit of the combustor 28 and the leading turbine blades 38 and redirect the working gas flow onto the turbine blades 38.

[0048] The combustion gas from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38, which in turn rotate the shaft 22. The guide vanes 40, 44 serve to optimize the angle of the combustion gas or the working gas at the turbine blades 38.

[0049] The turbine section 18 drives the compressor section 14. The compressor section 14 includes an axial array of blade rows 46 and rotor blade rows 48. The rotor blade rows 48 may comprise a rotor disk supporting an annular array of rotor blades. The compressor section 14 may also include a casing 50 surrounding the rotor rows and supporting the blade rows 48. The vane rows may include an annular array of radially extending vanes mounted on the casing 50. The vanes are provided to present a gas flow at an optimal angle for the rotor blades at a given gas turbine operating point. Some of the vane stages may have variable vanes, wherein the angle of the vanes about their own longitudinal axis can be adjusted with respect to the angle according to airflow characteristics that may occur at different turbine operating conditions.The housing 50 may define a radially outer surface 52 of the passage 56 of the compressor 14. A radially inner surface 54 of the passage 56 may be defined at least partially by a rotor drum 53 of the rotor, which may be partially defined by the annular array of rotor blades 48.

[0050] The present technique is described with reference to the exemplary gas turbine described above, which has a single shaft or spool connecting a single multi-stage compressor and a single single- or multi-stage turbine. However, it should be understood that the present technique is equally applicable to gas turbines with two or three shafts and may be used for industrial, aerospace, or marine applications.

[0051] The terms upstream and downstream refer to the flow direction of the air flow and / or the working gas flow through the gas turbine, unless otherwise stated. The terms forward and reverse refer to the general gas flow through the gas turbine. The terms axial, radial, and circumferential are used with reference to the rotational axis 20 of the gas turbine.

[0052] In the present technique, a turbomachine component 1 is presented which includes a blade 100 - such as in Fig. 4A, Fig. 4B and Fig. 5. The turbomachine component 1 of the present technique may be the rotor blade 38 of the gas turbine 10 described above. The turbomachine component 1 of the present technique may be the bucket 40, 44 of the gas turbine 10 described above. Hereinafter, for the sake of simplicity and brevity, and not intended to be limiting unless otherwise stated, the turbomachine component 1 has been illustrated and referred to as a rotor blade of the gas turbine, however, it may be noted that the turbomachine component 1 according to the present technique may also be another turbomachine component 1 including an airfoil in accordance with the present technique, e.g., the turbomachine component 1 may be a bucket 40, 44.

[0053] Fig. Figure 2 schematically illustrates an example of a turbomachine assembly. The assembly may include turbine blades 38 as the turbomachine component 1, which is arranged on the rotor disk 36. The turbine blade 38 may include a platform 200, an airfoil 100, and optionally a root 300. The rotor blade 38 may be attached or mounted to the disk 36 via the root 300.

[0054] In the following, a turbomachine component 1 according to the present technique will be described with reference to the example of Fig. 4A and Fig. 4B in combination with the example of Fig. 2 and compared to Fig. 3A and Fig. 3B explains. Fig. 3A and Fig. 3B represent a conventional rotor blade 38' for comparative understanding of the turbomachine component 1 of the present technique.

[0055] The turbomachine component 1 includes a platform 200 and an airfoil 100 extending from the platform 200. The platform 200 may include a top surface 201 and a bottom surface 210. The airfoil 100 may extend from the top surface 201 of the platform 200. The top surface 201 may extend circumferentially around the disk's axis of rotation and axially toward the shaft. Similarly, the bottom surface 210 may extend circumferentially and axially. The airfoil 100 extends radially outward from the top surface 201 of the platform 200 or radially inward from outside the casing or platform.

[0056] The airfoil 100 includes a pressure side 102 (also referred to as a pressure surface or concave surface / side) and a suction side 104 (also referred to as a suction side or convex surface / side). The pressure side 102 and the suction side 104 meet at a leading edge 106 and a trailing edge 108 of the airfoil 100.

[0057] The airfoil 100 may have a base portion 100b adjacent to the platform 200 and a tip portion 100a spaced from the base portion 100b in a longitudinal direction A of the airfoil 100. A height of the airfoil 100 may be understood as a distance between the tip portion 100a and the base portion 100b of the airfoil, or in other words, a distance between a tip of the airfoil and the top surface 201 of the platform 200. Simply put, the height of the airfoil 100 may be understood as a total protruding length of the airfoil 100 from the top surface 201 of the platform 200.

[0058] The pressure side 102, the suction side 104, the leading edge 106 and the trailing edge 108 define an interior space 100s of the airfoil 100. The interior space 100s of the airfoil 100 may be bounded by the tip portion 100a and the base portion 100b of the airfoil 100.

[0059] The interior space may extend further or may be connected by the platform and the root. The cooling air supply may be provided at the bottom of the root.

[0060] At least one web 60 may be arranged in the interior 100s of the airfoil 100. The web 60 may extend between the pressure side 102 and the suction side 104. More specifically, each web 60 may extend between an inner surface of a wall of the airfoil 100 at the pressure side 102 of the airfoil 100 and an inner surface of the wall of the airfoil 100 at the suction side 104 of the airfoil 100. It may be mentioned that, although the example of Fig. 4B shows four such webs 60 by way of example; the airfoil 100 may have 1 or 2 or 3 or 5 or more webs 60. Each web 60 is connected to the pressure side 102 and the suction side 104. More specifically, each web 60 is connected to the inner surface of the pressure-side wall and the inner surface of the suction-side wall.

[0061] In preferred embodiments, a web may have a Y-shape, wherein, for example, one branch of the Y is then not directly connected to the pressure side or the suction side, or all three branches are connected to inner surfaces of the outer walls of the blade, thereby creating three cooling channels.

[0062] The wall of the airfoil 100, which includes the pressure side 102 and the suction side 104 and defines the leading edge 106 and the trailing edge 108, may also be referred to as the outer wall of the airfoil 100 or the primary wall of the airfoil 100. The primary wall of the airfoil 100 defines the external appearance of the airfoil, or in other words, defines the airfoil shape.

[0063] Each land 60 can also be understood as being formed by a wall in the airfoil 100, however, the wall forming the land 60 is different from the primary wall and can be referred to as an inboard wall or secondary wall of the airfoil 100. When the airfoil 100 is positioned in the hot gas path of the gas turbine 100, the primary wall of the airfoil 100 is positioned directly in the hot gas path of the gas turbine. In other words, a surface (an outboard surface or an outer surface) of the primary wall of the airfoil 100, i.e., the pressure side 102 and the suction side 104 of the airfoil, comes into direct contact with the heating gas. However, when the airfoil 100 is positioned in the hot gas path of the gas turbine 100, the secondary wall, i.e., the land 60 of the airfoil 100, is not positioned directly in the hot gas path of the gas turbine.In other words, none of the surfaces or faces of the web 60 come into direct contact with the heating gas. The web 60 can be understood as being completely surrounded by the primary wall of the airfoil 100.

[0064] As in the examples of Fig. 4A and Fig. 4B, the interior space 100s of the airfoil 100 may include at least one cooling channel 70 for a cooling air flow 5. The cooling channels 70 may be understood as subdivisions of the interior space 100s of the airfoil 100 created by the webs 60. It may be mentioned that, although the example of Fig. 4B shows, by way of example, five such cooling channels 70, the airfoil 100 may have 1 or 2 or 3 or 4 or 6 or more cooling channels 70. The cooling air 5 may be supplied into the cooling channel 70 from outside the airfoil 100, e.g., through cooling air flow paths (not shown) formed in the root 300 of the rotor blade 1, or from cooling air flow paths (not shown) formed outside the airfoil 100 but fluidly connected to the airfoil 100 at the base part 100b and / or the tip part 100a of the airfoil 100. Alternatively, or in addition to what has been described above, the cooling air 5 may be supplied into the cooling channel 70 from a further cooling channel 70 of the airfoil 100, e.g.,through cooling air flow paths (not shown) formed in the root 300 of the rotor blade 1, or from cooling air flow paths (not shown) formed outside the airfoil 100 but fluidly connected to the airfoil 100 at the base part 100b and / or the tip part 100a of the airfoil 100.

[0065] The cooling channel 70 may extend in the longitudinal direction A of the blade 100, as in the examples of Fig. 2, Fig. 4A and Fig. 4B. As in the example of Fig. 4B, each cooling channel 70 may be defined by one or more webs 60 and the pressure side 102 and the suction side 104. The example of Fig. 4B shows a first cooling channel 70 defined by a land 60, a portion of the pressure side 102, a portion of the suction side 104, and the leading edge 106. The example of Fig. 4B also shows a second cooling channel 70 defined by a land 60, a portion of the pressure side 102, a portion of the suction side 104, and the trailing edge 108. In addition, the example of Fig. 4B a third cooling channel 70, which is defined by two adjacent webs 60 facing each other, a part of the pressure side 102 and a part of the suction side 104. The example of Fig. 4B illustrates three such third cooling channels 70 arranged between the first and second cooling channels 70.

[0066] As in the example of Fig. 4B and also in the example of Fig. 4A, which shows a cross section of the turbomachine component 1 along the line NN in Fig. 4B, the blade 100 may further include a flow deflector 80 which, compared to the conventional rotor blade shown in Fig. 3A and Fig. 3B and which does not include such a flow deflector on the web, protrudes outwardly from the web 60 into the cooling channel 70. Fig. Figure 3A schematically represents a cross-section of the conventional rotor blade along the line MM in Fig. 3B.

[0067] As in the example of Fig. 5, according to the present technique, the flow deflector 80 may be shaped to direct at least a portion of a cooling air 5 flowing in the longitudinal direction A of the airfoil 100 in the cooling channel 70 to at least one target area T on the pressure side 102 and / or on the suction side 104 (although Fig. 5 does not depict the target region formed on the pressure side) and consequently directs it (or, in other words, deflects it in a directed manner to give the cooling air a desired direction as a result of the deflection). More specifically, the target region T is formed or is a region of the inner surface of the pressure side 102 and / or the suction side 104 of the airfoil 100, which is formed or realized by the flow deflector 80 by deflecting or directing the cooling air 5 directly to this region of the inner surface of the pressure side 102 and / or the suction side 104.

[0068] The flow deflector 80 may be shaped to direct or deflect cooling air 5 to the target area T through a geometric shape or an external shape of the flow deflector 80. For example, the flow deflector 80 may have a surface that may be inclined with respect to the longitudinal direction A toward the target area T on the pressure side 102 or toward the target area T on the suction side 104. Although in the example of Fig. 5 such a target area T is shown as being formed at the suction side 104, it can be appreciated by one skilled in the art that more such target areas T can be realized on the suction side 104 and that one or more such target areas T can be realized on the pressure side 102 as an alternative to the one or more target areas T realized on the suction side 104 or in addition to the one or more target areas T realized on the suction side 104. Each land 60 can include one or more flow deflectors 80 that can realize one or more target areas T. Each target area T can be realized by one flow deflector 80 or, in other words, one flow deflector 80 can direct cooling air to a target area T.Alternatively, multiple target areas T can be realized by one flow deflector 80, or in other words, one flow deflector 80 can deflect and / or direct cooling air to multiple target areas T. One example is a 'V'-shaped flow deflector 80 (the 'V' shape is merely an example - other shapes are also possible, e.g., a 'Y' shape or a trapezoidal shape) having a first surface (represented in the present example by a branch of the 'V' shape) for directing or deflecting the cooling air to at least one target area T so realized on the pressure side 102, and a second surface (represented in the present example by another branch of the 'V' shape) for directing or deflecting the cooling air to at least one target area T so realized on the suction side 104.

[0069] It can be mentioned that although the example of Fig. 4A shows five flow deflectors 80 (each being inclined) formed on the web 60, it can be appreciated by a person skilled in the art that 1 or 2 or 3 or 4 or 6 or more flow deflectors 80 can be formed on one web 60 of the present technique, e.g., the web 60 of the example of Fig. 4A, instead of the five flow deflectors 80 formed on the web 60, as in the example of Fig. 4A. Each of the five flow deflectors 80 deflects cooling air to a different target area T, thereby implementing five target areas on the pressure side 102 of the airfoil. According to the present technique, each flow deflector 80 is shaped and / or oriented and / or sized such that a blocking factor B caused due to the flow deflector 80 is equal to or greater than 0.15. In a more specific example, the blocking factor may be greater than 0.15 and equal to or less than 0.5. When the blocking factor is greater than 0.15, the cooling efficiency is further improved, while being equal to or less than 0.9, preferably equal to or less than 0.5, ensures that the cooling air flow through the flow deflector 80 is not adversely restricted or limited.

[0070] In yet another example, the flow deflector 80 may be shaped / sized / oriented such that the blocking factor may be equal to or greater than 0.2 and equal to or less than 0.5. The blocking factor between 0.2 and 0.5 provides increased cooling efficiency without adversely restricting or limiting the cooling air flow through the flow deflector 80.

[0071] As in Fig. 6A and Fig. As shown in Figure 6B, the blocking factor can be defined as follows: Blocking factor=DH,wo−DH,wDH,wo, where D H,wo represents the hydraulic diameter of the cooling channel 70 without the flow deflector 80 and D H,w represents the hydraulic diameter of the cooling channel 70 with the flow deflector 80.

[0072] The hydraulic diameter D H,woof the cooling channel 70 without the flow deflector 80 can be defined by the following: DH,wo=4AwoPwo, where

[0073] A wo represents an area of ​​a cross section of the cooling channel 70 without the flow deflector 80 and P wo represents a circumference of the cross section of the cooling channel 70 without the flow deflector 80.

[0074] The hydraulic diameter D H,w of the cooling channel 70 with the flow deflector 80 can be defined by the following: DH,w=4AwPw, where A w represents an area of ​​a cross section of the cooling channel 70 with the flow deflector 80 and P w represents a circumference of the cross section of the cooling channel 70 with the flow deflector 80.

[0075] All references to the cooling channel 70 without the flow deflector 80 can be understood as the cooling channel 70 without the flow deflector 80, which, however, has all other parameters consistent with those of the cooling channel 70 with the flow deflector 80. An example can be seen from Fig. 7B, where a cross section at line QQ is an example of Fig. 6A, whereas a cross section at line PP would be an example of Fig. 6B. Another example can be seen from Fig. 7G, where a cross section at line SS is an example of Fig. 6A, whereas a cross section at line RR would be an example of Fig. 6B would represent.

[0076] It can be mentioned that although the examples of Fig. 4A, Fig. 4B and Fig. 5 show flow deflectors 80 intended to be formed on only one such web 60, one or more flow deflectors 80 may be formed on surfaces of such webs 60—such that they are arranged in the same or further cooling channels 70. Furthermore, flow deflectors 80 may be formed on both surfaces of any webs 60 such that they are arranged in different cooling channels 70.

[0077] Further exemplary embodiments of the present technique are described below.

[0078] As in the example of Fig. 4A, the cooling channel 70 may include an inlet 72 at a horizontal or circumferential position with respect to the platform 200 where the base portion 100b of the airfoil 100 meets a top surface 201 of the platform 200. The flow deflector 80 may be confined within the airfoil 100 or may be completely confined therein by being spaced from the inlet 72 of the cooling channel 70. In other words, the land 60 may be extended into the platform 200, but the one or more flow deflectors 80 are not extended or are physically confined within the portion of the wall of the land 60 that is located within the airfoil 100. Thus, the one or more deflectors protrude from the land at a longitudinal height of the land above the height of the platform. Fig. 7A- Fig. 7L each show various exemplary embodiments of flow deflectors 80, wherein the one or more flow deflectors 80 - either an extended flow deflector 80, as in Fig. 7B to Fig. 7F, or a plurality of flow deflectors 80 arranged in an array arranged in the longitudinal direction A, as shown in Fig. 7A and Fig. 7G to Fig. 7L - in any event, the one or more flow deflectors 80 do not extend beyond the blade 100, ie, do not extend into the platform 200, which in Fig. 7A- Fig. 7L is shown schematically. However, the flow deflector can alternatively start under the platform or the shroud.

[0079] As in the examples of Fig. 7B to Fig. 7F, the flow deflector 80 may be an extended flow deflector 80. The flow deflector 80 may have an elongated shape and may be oriented to extend between the base portion 100b of the airfoil 100 and the tip portion 100a of the airfoil 100.

[0080] As in the examples of Fig. 7A and Fig. 7G to Fig. 7L, a plurality of flow deflectors 80 may be illustrated in the turbomachine component 1 of the present technique. The flow deflectors 80 may be arranged in an array in the longitudinal direction A of the airfoil 100. Each of the plurality of flow deflectors 80 may be web-shaped, as shown in Fig. 7G to Fig. 7L, and / or pin-ribbed, as shown in Fig. 7A. Alternatively, the plurality of differently shaped flow deflectors 80 may have different shapes—e.g., one or more ridge-shaped and one or more pin-rib-shaped.

[0081] Fig. Fig. 7A schematically illustrates an exemplary embodiment of the flow deflector 80 formed as a plurality of flow deflectors 80. Each flow deflector 80 is pin-rib-shaped. The flow deflectors 80 are oriented in the direction A (which is shown in Fig. 2). Each flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to displace or deflect the flow to a target area T, ie, a predetermined or desired target area T.

[0082] Fig. Figure 7B schematically illustrates an exemplary embodiment of the flow deflector 80 formed as a one-piece or single flow deflector 80. The flow deflector 80 has an extended ridge shape. The extension direction of the ridge shape is in the direction A (which is Fig. 2). The flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to bias the flow or deflect the flow toward a target area T, i.e., a predetermined or desired target area T. The flow deflector may extend along a straight line or rectilinearly without bending. The flow deflector 80 may be angled with respect to direction A to guide the air flowing over the surface of the flow deflector 80 to the desired target area T. The extension length of the ridge-shaped flow deflector may start at -10% of an airfoil height (the negative sign means that the flow deflector starts below the platform) and end at 90% of an airfoil height, preferably from 20% to 70% of an airfoil height.

[0083] Fig. Figure 7C schematically illustrates another exemplary embodiment of the flow deflector 80, which is also formed as a one-piece or single flow deflector 80. The flow deflector 80 has an extended ridge shape. The extension direction of the ridge shape is in the direction A (which is shown in Fig. 2). The flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to offset or deflect the flow to a target area T, i.e., a predetermined or desired target area T. The flow deflector may extend along a straight line or rectilinearly without bending. The flow deflector 80 may be angled with respect to the direction A to guide the air flowing over the surface of the flow deflector 80 to the desired target area T. The extension length of the web-shaped flow deflector may start at -10% of an airfoil height and end at 90% of an airfoil height, preferably from 5% to 80% of an airfoil height.

[0084] Fig. Fig. 7D schematically illustrates yet another exemplary embodiment of the flow deflector 80, which is also formed as a one-piece or single flow deflector 80. The flow deflector 80 has an extended ridge shape. The extension direction of the ridge shape is in the direction A (which is Fig. 2). The flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to offset or deflect the flow to a target area T, i.e., a predetermined or desired target area T. The flow deflector may extend along a curved line, or in other words, may be bent in the direction A. Optionally, the flow deflector 80 may be angled with respect to the direction A to guide the air flowing over the surface of the flow deflector 80 to the desired target area T. The extension length of the ridge-shaped flow deflector may start at -10% of an airfoil height and end at 90% of an airfoil height, preferably from 5% to 75% of an airfoil height.

[0085] Fig. Fig. 7E schematically illustrates yet another exemplary embodiment of the flow deflector 80, which is also formed as a one-piece or single flow deflector 80. The flow deflector 80 has a U-shape. The extension direction of the U-shape is in the direction A (which is shown in Fig. 2). The two branches of the U-shape are of equal length. The bent portion of the U-shape may face the incoming airflow, and the branches of the U-shape may deflect the airflow. The flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to bias the flow or deflect the flow to a target area T, i.e., a predetermined or desired target area T. Each branch of the U-shape may extend along a straight line in the direction A. Optionally, one or both branches of the flow deflector 80 may be angled with respect to the direction A to direct the air flowing over the surface of the flow deflector 80 to the desired target area T.

[0086] Fig. Fig. 7F schematically illustrates yet another exemplary embodiment of the flow deflector 80, which is also formed as a one-piece or single flow deflector 80. The flow deflector 80 has a U-shape. The extension direction of the U-shape is in the direction A (which is shown in Fig. 2) or aligned with it. The two branches of the U-shape are of different lengths. The bent part of the U-shape may face the incoming airflow, and the branches of the U-shape may deflect the airflow. The flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to bias the flow or deflect the flow to a target area T, i.e., a predetermined or desired target area T. Each branch of the U-shape may extend along a straight line in the direction A. Optionally, one or both branches of the flow deflector 80 may be angled with respect to the direction A to guide the air flowing over the surface of the flow deflector 80 to the desired target area T. The deflector, shaped as one or more lines, may have a meandering shape, or any other shape that helps improve heat transfer in the target area T.

[0087] Fig. 7G- Fig. 7L schematically illustrate further exemplary embodiments of the flow deflector 80 formed as a plurality of, ie, a plurality of flow deflectors 80. Each flow deflector 80 is ridge-shaped or wedge-shaped. The flow deflectors 80 are oriented in the direction A (which is Fig. 2). Each flow deflector 80 is shaped and / or sized and / or positioned and / or oriented to displace or deflect the flow to a target area T, ie, a predetermined or desired target area T.

[0088] Flow deflectors can be angled in the range of 5 degrees to 85 degrees with respect to direction A. In Fig. 7G to Fig. 7L shows preferred embodiments.

[0089] As in Fig. 7G, each flow deflector is angled in the range of 10 degrees to 40 degrees with respect to direction A. As shown in Fig. 7H, each flow deflector is angled in the range of 50 degrees to 80 degrees with respect to direction A. As shown in Fig. 7I, each flow deflector is angled in the range of 30 degrees to 60 degrees with respect to direction A. As shown in Fig. 7J, each flow deflector is angled in the range of 20 degrees to 50 degrees with respect to direction A. As shown in Fig. 7K, each flow deflector is angled in the range of 10 degrees to 40 degrees with respect to direction A. In addition, the number of deflectors can be adjusted, e.g., four inclined deflectors in Fig. 7G or six deflectors that are less inclined, in Fig. 7H.

[0090] The flow deflectors 80, whether one or more, may be spaced from the pressure side 102 and / or the suction side 104, as in the examples of Fig. 7A to Fig. 7L is shown.

[0091] As in the examples of Fig. 7A to Fig. 7L, the target region T may include at least one heat transfer enhancing element 90. The heat transfer enhancing element 90 may be a ridge and / or a pin and / or a recess formed on the inner surface of the pressure side 102 and / or the suction side 104 at least in the target region T. The heat transfer enhancing element 90 may be a turbulator for the cooling air 5 deflected by the flow deflector 80 to the target region T and / or act to increase a surface area of ​​the target region T to improve heat transfer from the target region T to the cooling air 5 deflected by the flow deflector 80 to the target region T.

[0092] The flow deflector 80 may be shaped to deflect the cooling air 5 toward the at least one heat transfer enhancing element 90 such that the cooling air 5 deflected by the flow deflector 80 directly impacts the at least one heat transfer enhancing element 90.

[0093] The flow deflector 80 may be formed integrally with the web 60, for example, but not limited to, by casting or additive manufacturing. Alternatively, the flow deflector 80 may be formed as a single unit and then attached to the web 60, for example, but not limited to, by brazing.

[0094] As in Fig. 6B, the flow deflector 80 may include a base portion 80b adjacent a surface 62 of the web 60 from which the flow deflector 80 projects outwardly into the cooling channel 70, and a head portion 80a spaced from the base portion 80b. The head portion 80a of the flow deflector 80 may be cantilevered, i.e., need not be in direct contact with a wall of the cooling channel 70 or any other structure disposed within the cooling channel, e.g., disposed on the wall of the cooling channel 70. Simply put, the head portion 80a of the flow deflector 80 need not be in contact with the pressure side 102 and / or the suction side 104 and / or the leading edge 106 and / or the trailing edge 108 and / or an adjacent land 60 facing the land 60 from which the flow deflector 80 projects and adjacent to the cooling channel 70 into which the flow deflector 80 projects, iewhich forms one of the walls of the cooling channel 70 into which the flow deflector 80 projects. Alternatively, the head portion 80a of the flow deflector 80 may be in contact with another web or may be formed integrally therewith. Simply put, in an embodiment not shown, the flow deflector 80 may extend between two webs 60. As shown in FIG. Fig. 7M, the side end of one or more flow deflectors 80 may be connected to the pressure side 102. In another embodiment, the flow deflector 80 may be connected to the suction side (not shown), or the one or more flow detectors 80 may alternatively be connected to the pressure side 102 and the suction side 104 (also not shown).

[0095] In addition, the height of the one or more flow deflectors 80a, 80 in the cooling channels may be different, as shown in Fig.7M, left side, is shown.

[0096] Furthermore, the height of an individual flow deflector 80 protruding from the surface of the web may vary, having the maximum height near the pressure side 102 and a lower height near the suction side 104, or vice versa.

Claims

[1] Turbomachine component (1) for a gas turbine (10), the turbomachine component (1) comprising: - a platform (200) and - an airfoil (100) extending from the platform (200) and having a base portion (100b) adjacent to the platform (200) and a head portion (100a) spaced from the base portion (100b) in a longitudinal direction (A) of the airfoil (100); wherein the airfoil (100) further comprises: - a pressure side (102) and a suction side (104) which meet at a leading edge (106) and a trailing edge (108) and define an interior space (100s) of the blade (100); - at least one web (60) arranged in the interior (100s) of the blade (100) and extending between the pressure side (102) and the suction side (104); - at least two cooling channels (70) for the cooling air flow (5), which are formed in the interior (100s) of the blade (100) and extend in the longitudinal direction (A) of the blade (100) and are defined at least by the web (60) and the pressure side (102) and suction side (104); and - a flow deflector (80) which projects outwardly from the web (60) into the cooling channel (70) and is shaped such that it deflects at least part of the cooling air (5) flowing in the longitudinal direction (A) of the blade (100) in the cooling channel (70) to at least one target area (T) on the pressure side (102) and / or on the suction side (104), characterized bythat the target area (T) comprises at least one heat transfer improvement element (90), and the flow deflector (80) is shaped such that it deflects the cooling air (5) to the at least one heat transfer improvement element (90) such that the cooling air (5) deflected by the flow deflector (80) has a direct effect on the at least one heat transfer improvement element (90), wherein the flow deflector (80) is configured such that a blocking factor due to the flow deflector (80) is equal to or greater than 0.15, where the blocking factor is defined as follows: Blocking factor=DH,wo−DH,wDH,wo, where D H,wo represents the hydraulic diameter of the cooling channel (70) without the flow deflector (80) and D H,w represents the hydraulic diameter of the cooling channel (70) with the flow deflector (80), where the hydraulic diameter (D H,wo ) of the cooling channel (70) without the flow deflector (80) is defined by the following: DH,wo=4AwoPwo, where A wo represents an area of ​​a cross section of the cooling channel (70) without the flow deflector (80) and P wo represents a circumference of the cross-section of the cooling channel (70) without the flow deflector (80); and / or the hydraulic diameter (D H,w ) of the cooling channel (70) with the flow deflector (80) is defined by the following: DH,w=4AwPw, where A w represents an area of ​​a cross section of the cooling channel (70) with the flow deflector (80) and P w represents a circumference of the cross section of the cooling channel (70) with the flow deflector (80). [2] Turbomachine component (1) according to claim 1, wherein the blocking factor is equal to or greater than 0.2 and equal to or less than 0.

9. [3] Turbomachine component (1) according to one of claims 1 to 2, wherein the cooling channel (70) comprises an inlet (72) where the base part (100b) of the blade (100) meets a top side (201) of the platform (200) and / or wherein the flow deflector (80) is spaced from the inlet (72) of the cooling channel (70) or the flow deflector (80) extends through the inlet (72). [4] Turbomachine component (1) according to one of claims 1 to 3, wherein the flow deflector (80) has an elongated shape and is oriented such that it extends between the base part (100b) of the airfoil (100) and the head part (100a) of the airfoil (100). [5] Turbomachine component (1) according to one of claims 1 to 4, comprising a plurality of flow deflectors (80), wherein the flow deflectors (80) are arranged in an array in the longitudinal direction (A) of the blade (100). [6] Turbomachine component (1) according to any one of the preceding claims, wherein the one or more flow deflectors (80) comprise a shape selected from at least one of the following: - bar-shaped, - pin-ribbed, - an elongated rod, which is straight or curved, or - a U-shaped bar that is open at the headboard, - bar-shaped and angled between 5-85% in relation to the longitudinal direction (A) and - adjacent to either the pressure side or the suction side. [7] Turbomachine component (1) according to one of claims 1 to 6, wherein the flow deflector (80) is formed integrally with the web (60). [8] Turbomachine component (1) according to one of claims 1 to 7, wherein the flow deflector (80) comprises: - a base portion (80b) adjacent to a surface (62) of the web (60) from which the flow deflector (80) projects outwardly into the cooling channel (70); and - a head portion (80a) spaced from the base portion (80b), wherein the head portion (80a) of the flow deflector (80) is freely suspended or the head portion (80a) of the flow deflector (80) is in contact with a further web (60). [9] Turbomachine component (1) according to one of claims 1 to 9, wherein the turbomachine component (1) is a rotor blade (38) or a blade (40, 44). [10] Gas turbine (10) comprising a turbomachine component (1) according to one of claims 1 to 9.

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