KR102553194B1 - Turbomachine component for a gas turbine and a gas turbine having the same - Google Patents

Abstract

The present technology provides turbomachine parts having airfoils such as blades or vanes of a gas turbine. Turbomachine parts include a platform and an airfoil extending from the platform. The airfoil includes a pressure side, a suction side, a leading edge and a trailing edge defining the interior space of the airfoil. At least one cooling channel is formed in the interior space and extends along the longitudinal direction of the airfoil. The airfoil includes at least one web extending between the pressure side and the suction side of the airfoil. The flow deflecting plate projects outwardly from the web into the cooling channel and is shaped to deflect at least a portion of the cooling air flowing in the cooling channel towards the target area on the pressure side and/or suction side. The flow deflection plate may be shaped so that the blocking coefficient by the flow deflection plate is 0.15 or more.

Description

Turbo machine parts for gas turbines and gas turbines including the same

The present invention relates to a turbomachine part for a gas turbine and a gas turbine including the same, and more particularly, to cooling of an airfoil of the gas turbine.

Turbomachines include various turbomachine parts that benefit from cooling so that the operating life of the parts is increased.

Certain turbomachine parts include airfoils such as blades or vanes. The airfoil encloses an interior space and is internally cooled or cooled from the interior by flowing cooling air through the interior space of the airfoil or through one or more cooling channels formed in the interior space of the airfoil.

Turbomachine parts - hereinafter also referred to as blades or vanes - generally include airfoils (also referred to as aerofoils) protruding from the platform.

An airfoil protrudes adjacent to the surface of the platform.

The airfoil for the working fluid path of the turbomachine extends along the span direction from the base portion to the tip portion. Thus, the aerodynamic body includes a suction side surface, a pressure side surface, a leading edge and a trailing edge.

During operation of the gas turbine, the airfoils of the vanes or blades of the turbine section of the gas turbine are placed in the hot gas path. The airfoil also includes one or more webs extending from the pressure side to the suction side to create cooling channels in the interior space of the airfoil. Moreover, these webs provide mechanical reinforcement of the airfoil. The web divides the inner space of the airfoil into at least two cooling channels extending in the longitudinal direction of the airfoil according to the number of webs. Cooling air generally flows along the length of the airfoil within these cooling channels after being introduced to the airfoil. This enhancement of the internal cooling of the airfoil will have a beneficial effect on the efficiency of the gas turbine and/or the structural integrity of the airfoil.

Moreover, the effect/impact of thermal stress experienced by different regions or parts of the airfoil during operation of the gas turbine is not uniform. For example, some areas of the airfoil may have more hot gas due to the hot gas flow or position or orientation relative to the shape receiving the hot gas flow and/or due to changes in wall thickness and/or due to less local cooling, etc. Because it is subject to flow, it can experience higher stresses than other areas. Enhanced internal cooling of those airfoil regions that are prone to experience higher thermal stresses has a beneficial effect on the efficiency of the gas turbine and/or the structural integrity of the airfoil.

Also, for cooling gas turbine components, a portion of the air is withdrawn from the compressor section of the gas turbine and used as cooling air and flowed to other parts of the gas turbine that may be at different distances. To achieve the proper flow of cooling air, the cooling air flow must be maintained at optimum pressure in different areas of the turbomachine and in different areas of the turbomachine part. Also, for efficient impingement cooling, it is important to maintain an optimum pressure. However, increasing the amount of air drawn from the compressor for cooling reduces the amount of air available for combustion, which can adversely affect the efficiency of the gas turbine.

: Korea Patent Publication 2019-0082003 A (2019.07.09)

Thus, it is advantageous to achieve targeted cooling of a desired or specific target area of the airfoil while at least partially eliminating the pressure loss to a sub-optimal level, preferably by enhancing the internal cooling of the airfoil.

This object is achieved by the subject matter of the independent claim, preferably by a turbomachine part for a gas turbine. Advantageous embodiments of the technology are presented in the dependent claims.

This turbomachine part comprising an airfoil is exemplified below as a blade, but unless otherwise specified, the description is applicable to other turbomachine parts comprising an airfoil such as a vane.

In a first aspect of the present technology, a turbomachine component for a gas turbine is provided. Turbomachine parts may include platforms and airfoils.

An airfoil may extend from the platform. The airfoil may have a base portion adjacent to the platform and a leading end spaced apart from the base portion along the longitudinal direction of the airfoil.

The tip may be on a platform or shroud, so vane and shrouded blades are also included.

The airfoil includes a pressure side and a suction side that meet at the leading and trailing edges. The pressure side, suction side, leading edge and trailing edge form the inner space of the airfoil.

At least one web may be disposed in the inner space of the airfoil. A web may extend between the pressure side and the suction side.

The inner space of the airfoil may include at least two cooling channels for the flow of cooling air. The cooling channel may extend along the length of the airfoil. The cooling channel can be at least partially formed by the web and the pressure side and/or the suction side.

The airfoil may further include a flow deflector projecting outward from the web into the cooling channel. The flow deflecting plate may be shaped to deflect at least a portion of the cooling air flowing along the length of the airfoil in the cooling channel toward the at least one target area on the pressure side and/or the suction side.

The flow deflector can have a shape and/or size such that the blockage factor due to the flow deflector is greater than or equal to 0.15, preferably greater than or equal to 0.2 and less than or equal to 0.5.

The clogging factor can be defined as:

Blockage factor = (D _H,wo - D _H,w )/D _H,wo

Here, D _H,wo denotes the hydraulic diameter of the cooling channel without a flow deflector, and D _H,w denotes the hydraulic diameter of the cooling channel with a flow deflector.

The hydraulic diameter (D _H,wo ) of a cooling channel without a flow deflector can be defined as:

D _H,wo = 4(A _wo /P _wo )

Here, A _wo denotes the cross-sectional area of the cooling channel without the flow deflection plate, and P _wo denotes the circumference of the cross-section of the cooling channel without the flow deflection plate.

The hydraulic diameter (D _H,w ) of the cooling channel with the flow deflector plate can be defined as:

D _H,w = 4(A _w /P _w )

Here, A _w denotes the cross-sectional area of the cooling channel with the flow deflection plate, and P _wo denotes the circumference of the cross-section of the cooling channel with the flow deflection plate.

The cooling channel may include an inlet where the base of the airfoil meets the upper surface of the platform.

The flow deflector plate may be confined, confined or completely contained within the airfoil as spaced apart from the inlet of the cooling channel.

The flow deflecting plate may have an elongated shape and may be oriented to extend between the base of the airfoil and the tip of the airfoil.

In the turbomachine part of the present technology, there may be a plurality of floating deflection plates. The flow deflector plates may be arranged in an array in the longitudinal direction of the airfoil.

The flow deflector can be ribbed and/or pin-fin.

The target area may include at least one heat transfer enhancing element.

The heat transfer enhancing element may be at least one of a rib, a pin, and a dimple.

The flow deflection plate may be shaped to deflect the cooling air towards the at least one heat transfer enhancing element, such that the cooling air deflected by the flow deflecting plate directly impacts the at least one heat transfer enhancing element.

The role of the flow deflector is to direct cooling air from one side (eg pressure side) to the other side (eg suction side) to improve heat transfer to the other side (eg suction side).

The flow deflection plate may be integrally formed with the web. Alternatively, the flow deflection plate may be formed as a separate entity and attached to the web.

The deflection plate may be bonded to the web by brazing or welding, for example.

The flow deflection plate may include a base portion adjacent to the surface of the web from which the flow deflector plate projects outward into the cooling channel and a tip spaced from the base portion. The leading end of the flow deflection plate may hang freely, ie not directly contact any wall of the cooling channel or any other structure disposed on the wall of the cooling channel, such as the cooling channel.

Turbomachine parts can be blades or vanes.

In a second aspect of the present technology, a turbomachine assembly is provided. The turbomachine assembly includes at least one turbomachine part as described above in the first aspect of the present technology. Turbomachine parts can be blades or vanes of a gas turbine. The turbomachine part may be a blade of a turbine section of a gas turbine and may be assembled on a rotor disk of a gas turbine.

In a third aspect of the present technology, a gas turbine is provided. A gas turbine may include at least one turbomachine assembly. A turbomachine assembly may be according to the second aspect of the present technology as described above.

In a fourth aspect of the present technology, a gas turbine is provided. The gas turbine may include at least one turbomachine component according to the first aspect of the present technology as described above.

The above-mentioned attributes, other features and advantages of the present technology and how to achieve them will become more apparent, and the technology itself will be better understood by referring to the following description of embodiments of the present technology taken in conjunction with the accompanying drawings. . In the drawing:
1 illustrates, in cross section, a portion of a gas turbine incorporating a turbomachine component of the present technology;
2 schematically illustrates a turbomachine assembly incorporating turbomachine parts of the present technology;
3A is a vertical cross-sectional view of a conventional blade;
Fig. 3b is a horizontal cross-sectional view of a conventional airfoil in the conventional blade of Fig. 3a;
4A is a vertical cross-sectional view of an exemplary embodiment of a blade of the present technology, illustrating a turbomachine part according to the present technology;
FIG. 4B is a horizontal cross-sectional view of an exemplary embodiment of an airfoil of the present technology in the blade of FIG. 4A;
5 schematically illustrates another exemplary embodiment of an airfoil of the present technology illustrating operation of the present technology;
6A illustrates a portion of a cross-sectional view of an airfoil section without a flow deflection plate of the present technology;
6b illustrates a portion of a cross-sectional view of an airfoil section having a flow deflection plate of the present technology;
7A-7M schematically illustrate various exemplary embodiments of a flow deflection plate of the present technology, according to an aspect of the present technology.

Hereinafter, features and other features of the present technology described above will be described in detail. Various embodiments are described with reference to the drawings, in which like reference numbers are used throughout to refer to like elements. In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. It will be appreciated that the illustrated embodiments are illustrative rather than limiting of the present invention. It will be apparent that these embodiments may be practiced without these specific details.

1 illustrates an example of a gas turbine 10 in cross section. The gas turbine 10 may include an inlet 12, a compressor or compressor section 14, a combustor section 16 and a turbine section 18 in a flow series, which are generally arranged in a flow series and are generally longitudinal or They are arranged in that direction around the axis of rotation (20). The gas turbine 10 may further include a shaft 22 rotatable about the rotation axis 20 and extending longitudinally through the gas turbine 10 . Shaft 22 may drively connect turbine section 18 to compressor section 14 .

In operation of the gas turbine 10 , air 24 introduced through the air inlet 12 is compressed by the compressor section 14 and delivered to the combustor section or burner section 16 . Burner section 16 may include a burner plenum 26 , one or more combustion chambers 28 and at least one burner 30 fixed to each combustion chamber 28 . Combustion chamber 28 and burner 30 may be located inside burner plenum 26 . Compressed air passing through the compressor 14 may enter the diffuser 32 and exit the diffuser 32 to a burner plenum 26, from which a portion of the air may flow to the burner 30. It is introduced and mixed with gaseous or liquid fuel. Then, the air/fuel mixture is combusted and combustion gases 34 or working gases from the combustion are delivered through the combustion chamber 28 to the turbine section 18 via a transition duct 17. .

This exemplary gas turbine 10 may have a cannulated combustor section arrangement 16 consisting of an annular array of combustor cans 19 each having burners 30 and combustion chambers 28, transition ducts 17 includes a generally circular inlet and an outlet in the form of an annular segment that interfaces with the combustion chamber 28 . The transition duct outlets in the annular arrangement may form an annulus for directing the combustion gases to the turbine 18 .

Hollow section 18 may include a number of blade retaining disks 36 attached to shaft 22 . In this example, two disks 36 are represented, each holding an annular array of turbine blades 38 . However, the number of blade bearing disks may be different, ie only one disk or three or more disks. Also, guide vanes 40 fixed to the stator 42 of the gas turbine 10 may be disposed between the rows of the annular array of turbine blades 38 . A guide vane 44 is provided between the outlet of the combustion chamber 28 and the inlet of the leading turbine blade 38 to divert the flow of working gas to the turbine blade 38 .

Combustion gases from the combustion chamber 28 enter the turbine section 18 and drive the turbine blades 38 which in turn rotate the shaft 22 . The guide vanes 40 and 44 serve to optimize the angle of the combustion or working gas relative to the turbine blades 38 .

A turbine section (18) drives a compressor section (14). Compressor section 14 includes axially a series of rows of vanes 46 and rows of rotor blades 48. Rotor blade row 48 may include a rotor disk supporting an annular array of blades. The compressor section 14 may also include a casing 50 surrounding the rotor rows and supporting the vane rows 48 . The guide vane row may include an annular array of radially extending vanes mounted to casing 50 . The vanes are provided to provide gas flow at an optimum angle to the blades at a given turbine operating point. Some of the guide vane rows may have variable vanes, in which the angle of the vanes about their longitudinal axis can be angularly adjusted according to airflow characteristics that may occur under different turbine operating conditions. Casing 50 may form a radially outer surface 52 of passage 56 of compressor 14 . The radial inner surface 54 of the passage 56 may be formed at least in part by the rotor drum 53 of the rotor, which may be formed in part by the annular array of blades 48 .

The present technology is described with reference to the above exemplary gas turbine having a single multi-stage compressor and a single shaft or spool connecting more than one stage of the turbine. However, it should be noted that the present technology is equally applicable to two or three shaft gas turbines and may be used in industrial, aeronautical or marine applications.

The terms upstream and downstream refer to the flow direction of the air flow and/or working gas flow through the gas turbine unless otherwise stated. The terms forward and backward refer to the general flow of gas through the gas turbine. The terms axial, radial and circumferential refer to the axis of rotation 20 of the gas turbine.

In the present art, a turbomachine part 1 comprising an airfoil 100 is provided, for example as illustrated in FIGS. 4A, 4B and 5 . The turbomachine part 1 of the present technology may be the blade 38 of the gas turbine 10 described above. The turbomachine part 1 of the present technology may be the vanes 40 and 44 of the gas turbine 10 described above. Hereinafter, for the sake of simplicity and conciseness, the turbomachine part 1 is exemplified without intending to be limiting unless otherwise specified, and is also referred to as a blade of a gas turbine, but the turbomachine part 1 according to the present technology is also It may be another turbomachine part (1) comprising an airfoil according to, for example, the turbomachine part (1) may be vanes (40, 44).

2 schematically illustrates a turbomachine assembly. The assembly may include turbine blades 38 as turbomachine parts 1 arranged on a rotor disk 36 . Turbine blade 38 may include a platform 200 , an airfoil 100 and optionally a root 300 . The blade 38 may be fixed or mounted to the disk 36 via the root portion 300 .

Hereinafter, the turbomachine part 1 according to the present technology has been described with reference to the example of FIGS. 4a and 4b in combination with the example of FIG. 2 and in comparison with FIGS. 3a and 3b. 3a and 3b show a conventional blade 38' for comparative understanding of the turbomachine part 1 of the present art.

The turbomachine part 1 includes a platform 200 and an airfoil 100 extending from the platform 200 . Platform 200 may include an upper surface 201 and a lower surface 210 . The airfoil 100 may extend from the top surface 201 of the platform 200. Upper surface 201 may extend circumferentially about the axis of rotation of the disk and axially along the shaft. Similarly, lower surface 210 can extend circumferentially and axially. The airfoil 100 extends radially outwardly from the top surface 201 of the platform 200 or radially inwardly from the outer housing or platform.

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 surface or convex surface/side). The pressure side 102 and the suction side 104 intersect each other at the leading edge 106 and trailing edge 108 of the airfoil 100 .

The airfoil 100 may include a base portion 100b adjacent to the platform 200 and a front end portion 100a spaced apart from the base portion 100b along the longitudinal direction A of the airfoil 100 . The height of the airfoil 100 can be understood as the distance between the airfoil tip 100a and the base 100b, or in other words, the distance between the airfoil tip and the upper surface 201 of the platform 200. . Simply put, the height of the airfoil 100 can be understood as the total protruding length of the airfoil 100 from the top surface 201 of the platform 200.

The pressure side 102, the suction side 104, the leading edge 106 and the trailing edge 108 define the interior space 100s of the airfoil 100. The inner space 100s of the airfoil 100 may be limited by the front end 100a and the base 100b of the airfoil 100.

The inner space can be further expanded or connected through the platform and the root. A cooling air supply may be provided at the bottom of the root portion.

At least one web 60 may be disposed in the inner space 100s of the airfoil 100 . A web 60 may extend between the pressure side 102 and the suction side 104 . More precisely, each web 60 is the inner surface of the wall of the airfoil 100 on the pressure side 102 of the airfoil 100 and the airfoil 100 on the suction side 104 of the airfoil 100. It may extend between the interior surfaces of the walls of (100). The example of FIG. 4B illustrates four such webs 60, but it should be noted that for illustrative purposes, an airfoil 100 may have one or two or three or five or more webs 60. . Each web 60 is connected to a pressure side 102 and a suction side 104. More precisely, each web 60 is connected to the inner surface of the pressure-side wall and the inner surface of the suction-side wall.

In a preferred embodiment, the web may have a Y-shape, for example, one leg of the Y-shape is not directly connected to the pressure or suction side, or all three legs are connected to the inner surface of the airfoil outer wall. to form three cooling channels.

The wall of the airfoil 100 including the pressure side 102 and the suction side 104 and defining the leading edge 106 and trailing edge 108 is the outer wall of the airfoil 100 or the outer wall of the airfoil 100. It may also be referred to as a main wall. The peripheral wall of the airfoil 100 defines the appearance of the airfoil, that is, the shape of the airfoil.

Each web 60 can also be understood as being formed by the walls of the airfoil 100, but the walls forming the webs 60 are different from the main walls and can be referred to as the inner or secondary walls of the airfoil 100. there is.

When the airfoil 100 is located in the hot gas path of the gas turbine 100, the peripheral wall of the airfoil 100 is directly located in the hot gas path of the gas turbine. That is, the peripheral walls of the airfoil 100, that is, the surfaces (outer surface or outer surface) of the pressure side 102 and the suction side 104 of the airfoil come into direct contact with the hot gas. However, when the airfoil 100 is located in the hot gas path of the gas turbine 100, the secondary wall of the airfoil 100, i.e., the web 60, is not directly located in the hot gas path of the gas turbine. That is, none of the surfaces or sides of the web 60 are in direct contact with the hot gases. The web 60 can be understood to be completely surrounded by the perimeter walls of the airfoil 100 .

As shown in the examples of FIGS. 4A and 4B , the inner space 100s of the airfoil 100 may include at least one cooling channel 70 for the flow of cooling air 5 . The cooling channel 70 may be understood as a subdivision of the inner space 100s of the airfoil 100 formed by the web 60 . Although the example of FIG. 4B illustrates five such cooling channels 70, for illustrative purposes, an airfoil 100 may include one or two or three or four or six or more cooling channels 70. You should know that you can have it. The cooling air 5 is formed from the outside of the airfoil 100 or outside the airfoil 100 by, for example, a cooling air flow path (not shown) formed at the root portion 300 of the blade 1, but air Cooling air flow paths (not shown) connected in fluid communication with the airfoil 100 may be provided into the cooling channels 70 at the base portion 100b and/or the leading portion 100a of the foil 100 . Alternatively or in addition to the above, the cooling air 5 is used for further cooling of the airfoil 100, for example by means of a cooling air flow path (not shown) formed in the root portion 300 of the blade 1. A cooling air flow path from the channel 70 or formed external to the airfoil 100 but connected in fluid communication with the airfoil 100 at the base 100b and/or tip 100a of the airfoil 100 ( not shown) into the cooling channel 70 .

The cooling channel 70 may extend along the longitudinal direction A of the airfoil 100 as shown in the examples of FIGS. 2, 4a and 4b. As shown in the example of FIG. 4B , each cooling channel 70 may be formed by a web 60 and one or more of a pressure side 102 and a suction side 104 . The example in FIG. 4B illustrates a first cooling channel 70 formed by one of the webs 60 , a portion of the pressure side 102 , a portion of the suction side 104 and a leading edge 106 . The example of FIG. 4B also illustrates a second cooling channel 70 formed by one of the webs 60 , a portion of the pressure side 102 , a portion of the suction side 104 and a trailing edge 108 . The example of FIG. 4B also illustrates a third cooling channel 70 formed by two adjacent webs 60 facing each other, a portion of the pressure side 102 and a portion of the suction side 104 . The example of FIG. 4B illustrates three such third cooling channels 70 disposed between the first and second cooling channels 70 .

As illustrated in the example of FIG. 4b and in the example of FIG. 4a which schematically shows a cross-section of the turbomachine part 1 along the line N-N in FIG. Compared to the conventional blade shown in FIGS. 3A and 3B , it may further include a flow deflection plate 80 protruding outward from the web 60 into the cooling channel 70 . Figure 3a schematically shows a cross-section of a conventional blade along line M-M in Figure 3b.

As shown in the example of FIG. 5 , according to the present technology, the flow deflection plate 80 is at least part of the cooling air 5 flowing along the longitudinal direction A of the airfoil 100 in the cooling channel 70 . to deflect and guide (or in other words, deflection of As a result, it can be shaped (deflected in a guided manner to give the cooling air a desired direction). More precisely, a flow deflection plate 80 in which a target area T is formed, or deflects or guides the cooling air 5 directly towards the area of the inner surface of the pressure side 102 and/or the suction side 104. is the area of the inner surface of the pressure side 102 and/or suction side 104 of the airfoil 100 formed or realized by

The flow deflection plate 80 may be shaped to direct or deflect the cooling air 5 to the target area T by the geometry or shape of the flow deflection plate 80 . For example, the flow deflector plate 80 may be inclined with respect to the longitudinal direction A towards the target area T on the pressure side 102 or towards the target area T on the suction side 104. may have a surface. In the example of FIG. 5 , one such target area T is illustrated as being formed on the suction side 104, but one skilled in the art can realize more such target areas T on the suction side 104; One or more of these target areas T is realized on the pressure side ( 102) can be realized.

Each web 60 may include one or more flow deflecting plates 80 capable of realizing one or more target areas T. Each target area T can be realized by one flow deflection plate 80, in other words, one flow deflection plate 80 can lead the cooling air to the target area T. Alternatively, multiple target areas T can be realized by means of one flow deflection plate 80, in other words, one flow deflection plate 80 directs cooling air to multiple target areas T. can bias and/or induce. For example, the 'V'-shaped flow deflection plate 80 ('V'-shaped is illustrative, and other shapes, for example, 'Y'-shaped or trapezoidal shapes are also possible) is used to direct cooling air to the pressure side 102. A first surface for directing or deflecting towards at least one realized target area T (represented in this example as one 'V' shaped arm) and cooling air to the suction side 104 at least one realized target area ( T) a second surface (represented in this example as the other 'V' shaped arm) which guides or deflects toward the side.

Although the example of FIG. 4A shows five flow deflecting plates 80 (each inclined) formed on a web 60, one skilled in the art will recognize five flow deflecting plates 80 formed on a web 60 as shown in the example of FIG. 4A. Instead of deflection plate 80, one or two or three or four or six or more floating deflection plates 80 on any web 60 of the present technology, e.g., web 60 in the example of FIG. 4A. You will know that there may be. Each of the five flow deflecting plates 80 deflects the cooling air to a different target area T, realizing five target areas on the pressure side 102 of the airfoil.

According to the present technology, each flow deflection plate 80 has a shape and/or orientation and/or size such that the clogging coefficient B caused by the flow deflection plate 80 is equal to or greater than 0.15. In a more precise example, the clogging factor may be greater than 0.15 and less than 0.5. If the blockage coefficient is greater than 0.15, the cooling efficiency is further improved, whereas if it is less than 0.9, preferably less than 0.5, the flow of cooling air is not adversely confined or limited by the flow deflection plate 80.

In yet another example, the flow deflector plate 80 may have a shape/size/orientation such that the blockage factor may be greater than 0.2 and less than 0.5. A clogging factor of 0.2-0.5 provides increased cooling efficiency without causing adverse confinement or restriction of the cooling air flow by the flow deflection plate 80 .

As illustrated in FIGS. 6A and 6B , the clogging factor can be defined as:

Blockage factor = (D _H,wo - D _H,w )/D _H,wo

Here, D _H,wo represents the hydraulic diameter of the cooling channel 70 without the flow deflection plate 80, and D _H,w represents the hydraulic diameter of the cooling channel 70 with the flow deflection plate 80.

The hydraulic diameter D _H,wo of the cooling channel 70 without flow deflection plate 80 can be defined as:

D _H,wo = 4(A _wo /P _wo )

Here, A _wo represents the cross-sectional area of the cooling channel 70 without the flow deflection plate 80, and P _wo represents the circumference of the cross-section of the cooling channel 70 without the flow deflection plate 80.

The hydraulic diameter D _H,w of the cooling channel 70 with the flow deflection plate 80 can be defined as:

D _H,w = 4(A _w /P _w )

Here, A _w represents the cross-sectional area of the cooling channel 70 with the flow deflection plate 80, and P _wo represents the circumference of the cross section of the cooling channel 70 with the flow deflection plate 80.

All references to a cooling channel 70 without a flow deflection plate 80 refer to a cooling channel without a flow deflection plate 80, but with all other parameters identical to the cooling channel 70 with a flow deflection plate 80 ( 70) can be understood. One example can be understood from FIG. 7B , where the cross section at line Q-Q represents the example of FIG. 6A while the cross section at line P-P represents the example of FIG. 6B . Another example can be appreciated from FIG. 7G , where the cross section at line S-S represents the example of FIG. 6A while the cross section at line R-R represents the example of FIG. 6B .

4a, 4b and 5 illustrate the flow deflection plate 80 being formed on only one web 60, but other flow deflector plates 80 may be disposed on the same or different cooling channels 70. It can be seen that it can be formed on the surface of the web 60. Also, flow deflecting plates 80 may be formed on both sides of any web 60 to be disposed in different cooling channels 70 .

Other exemplary embodiments of the present technology are described below.

As shown in the example of FIG. 4A , the cooling channel 70 may include an inlet 72 at a horizontal or circumferential position relative to the platform 200 where the base 100b of the airfoil 100 is It intersects the upper surface 201 of the platform 200. The flow deflection plate 80 may be entirely confined or confined within the airfoil 100 at a distance from the inlet 72 of the cooling channel 70 . That is, web 60 may extend into platform 200, but one or more flow deflection plates 80 do not extend into, or are physically within, a portion of the wall of web 60 that is internal to airfoil 100. limited Thus, at least one deflection plate projects from the web at a longitudinal level of the web above the level of the platform. 7A-7L each illustrate a different exemplary embodiment of a flow deflection plate 80, wherein the flow deflection plate(s) 80 are one extended flow deflection plate as shown in FIGS. 7B-7F, respectively. 80 or a plurality of flow deflector plates 80 are arranged in an array arranged in the longitudinal direction A as illustrated in FIGS. 7A and 7G-7L, in each case the flow deflector plate(s) ( 80) does not extend beyond the airfoil 100, that is, into the platform 200 schematically shown in FIGS. 7A-7L. Alternatively, however, the flow deflector plate may be started under a platform or shroud.

As shown in the examples of FIGS. 7B-7F , the flow deflection plate 80 may be an elongated flow deflection plate 80 . The flow deflection plate 80 may have a long shape and may be oriented to extend between the base portion 100b of the airfoil 100 and the front end portion 100a of the airfoil 100 .

As shown in the examples of FIGS. 7A and 7G-7L, the turbomachine part 1 of the present technology may be provided with a plurality of flow deflection plates 80. The flow deflection plates 80 may be arranged in an array in the longitudinal direction A of the airfoil 100 . Each of the plurality of flow deflection plates 80 may be ribbed as shown in FIGS. 7G-7L and/or pin-fin as shown in FIG. 7A. Alternatively, the plurality of flow deflection plates may have flow deflection plates 80 of different shapes, for example, one or more rib type and one or more pin-pin type.

7A schematically illustrates an exemplary embodiment of a flow deflection plate 80 formed in a plurality of flow deflection plates 80 . Each flow deflection plate 80 is pin-pin type. The flow deflection plate 80 is arranged along direction A (shown in FIG. 2). Each flow deflecting plate 80 has a shape and/or size and/or position and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T.

7B schematically illustrates an exemplary embodiment of a flow deflection plate 80 formed of a single or one flow deflection plate 80 . The flow deflection plate 80 has an extended rib shape. The extension direction of the rib shape is arranged or aligned along direction A (shown in FIG. 2). The flow deflecting plate 80 has a shape and/or size and/or location and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T. The flow deflection plate may extend linearly along a straight line or without bending. The flow deflection plate 80 may be inclined with respect to the direction A to guide the air flowing over the surface of the flow deflection plate 80 toward a desired target area T. The extended length of the ribbed flow deflection plate starts at -10% of the airfoil height (minus sign means the flow deflector starts below the platform) to 90% of the airfoil height, preferably 20% of the airfoil height. % to 70%.

7C schematically illustrates another exemplary embodiment of a flow deflection plate 80 formed of a single or one flow deflection plate 80 . The flow deflection plate 80 has an extended rib shape. The extension direction of the rib shape is arranged or aligned along direction A (shown in FIG. 2). The flow deflecting plate 80 has a shape and/or size and/or location and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T. The flow deflection plate may extend linearly along a straight line or without bending. The flow deflection plate 80 may be inclined with respect to the direction A to guide the air flowing over the surface of the flow deflection plate 80 toward a desired target area T. The extended length of the ribbed flow deflector plate may start at -10% of the airfoil height and end at 90% of the airfoil height, preferably between 5% and 80% of the airfoil height.

7d schematically illustrates another exemplary embodiment of a flow deflection plate 80 formed of a single or one flow deflection plate 80 . The flow deflection plate 80 has an extended rib shape. The extension direction of the rib shape is arranged or aligned along direction A (shown in FIG. 2). The flow deflecting plate 80 has a shape and/or size and/or location and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T. The flow deflector plate can be extended along a curve or, in other words, can be bent along direction A. Optionally, the flow deflection plate 80 may be inclined with respect to the direction A to direct the air flowing over the surface of the flow deflection plate 80 toward a desired target area T. The extended length of the ribbed flow deflector plate may start at -10% of the airfoil height and end at 90% of the airfoil height, preferably between 5% and 75% of the airfoil height.

7E schematically illustrates another exemplary embodiment of a flow deflection plate 80 formed of a single or one flow deflection plate 80 . The flow deflection plate 80 has a U-shaped shape. The extension direction of the U-shaped shape is arranged or aligned along direction A (shown in FIG. 2). The two arms of the U-shaped shape are equal in length. The U-shaped bend faces the incoming air stream and the U-shaped arm can deflect the air stream. The flow deflecting plate 80 has a shape and/or size and/or location and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T. Each arm of the U-shaped shape may extend along a straight line along direction A. Optionally, one or both arms of the flow deflection plate 80 may be inclined with respect to the direction A to guide the air flowing over the surface of the flow deflection plate 80 toward a desired target area T.

7f schematically illustrates another exemplary embodiment of a flow deflection plate 80 also formed from a single or one flow deflection plate 80 . The flow deflection plate 80 has a U-shaped shape. The extension direction of the U-shaped shape is arranged or aligned along direction A (shown in FIG. 2). The two arms of the U-shaped shape are of different lengths. The U-shaped bend faces the incoming air stream and the U-shaped arm can deflect the air stream. The flow deflecting plate 80 has a shape and/or size and/or location and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T. Each arm of the U-shaped shape may extend along a straight line along direction A. Optionally, one or both arms of flow deflection plate 80 may be inclined with respect to direction A to guide air flowing over the surface of flow deflection plate 80 toward a desired target area T. The deflection plate in the form of line(s) may have a serpentine shape or any other shape that helps improve heat transfer to the target area T.

7G-7L schematically illustrates another exemplary embodiment of a flow deflection plate 80 formed in a plurality of flow deflection plates 80 . Each flow deflection plate 80 is rib or wedge-shaped. The flow deflection plate 80 is arranged along direction A (shown in FIG. 2). Each flow deflecting plate 80 has a shape and/or size and/or position and/or orientation that biases or deflects the flow towards a target area T, ie a predetermined or desired target area T.

The flow deflector plate may have a 5 degree to 85 degree angle to direction A. A preferred embodiment is illustrated in Figures 7g-7l.

As illustrated in Fig. 7g, each flow deflector plate is angled from 10 to 40 degrees to direction A. As shown in Fig. 7H, each flow deflection plate forms an angle of 50 to 80 degrees with respect to direction A. As shown in FIG. 7I, each flow deflection plate forms an angle of 30 to 60 degrees with respect to direction A. As shown in Fig. 7j, each flow deflector plate is angled between 20 and 50 degrees with respect to direction A. As shown in FIG. 7K, each flow deflection plate forms an angle of 10 to 40 degrees with respect to direction A. Also, the number of deflection plates can be adjusted so that, for example, the four inclined deflection plates in Fig. 7G or the six deflection plates in Fig. 7H are less inclined.

The flow deflection plates 80, if single or multiple, may be spaced from the pressure side 102 and/or the suction side 104, as shown in the example of FIGS. 7A-7L.

As shown in the examples of FIGS. 7A-7L , the target area T may include at least one heat transfer enhancing element 90 . The heat transfer enhancing element 90 is a rib formed on the inner surface of the pressure side 102 and/or the suction side 104 at least within the target area T. It may be at least one of pins and dimples. The heat transfer enhancing element 90 is formed by the flow deflection plate 80 to improve the heat transfer from the target region T to the cooling air 5 deflected toward the target region T by the flow deflection plate 80. may be turbulent flow for the cooling air 5 deflected towards T) or may serve to increase the surface area of the target area T.

The flow deflection plate 80 may be shaped to deflect the cooling air 5 toward the at least one heat transfer enhancing element 90, so that the cooling air 5 deflected by the flow deflection plate 80 is directed toward the at least one heat transfer enhancing element 90. The heat transfer enhancing element 90 is directly impacted.

The flow deflection plate 80 may be integrally formed with the web 60 by, for example, but not limited to, casting or additive manufacturing. Alternatively, the flow deflection plate 80 may be formed as a separate entity and then attached to the web 60 by, for example, but not limited to brazing.

As shown in FIG. 6B, the flow deflector plate 80 has a base portion 80b adjacent to the surface 62 of the web 60 from which the flow deflector plate 80 projects outward into the cooling channel 70 and a base portion 80b. It may include a tip 80a spaced apart from 80b. The leading end 80a of the flow deflection plate 80 can be freely suspended, i.e., it can be attached to any wall of the cooling channel 70, or any other structure disposed on the wall of the cooling channel, such as the cooling channel 70. may not come into direct contact. Briefly, the front end 80a of the flow deflection plate 80 is formed by the pressure side 102, the suction side 104, the leading edge 106, the trailing edge 108 and the web from which the flow deflection plate 80 projects ( 60) and adjacent to the cooling channel 70 from which the flow deflector plate 80 protrudes, i.e. any of the adjacent webs forming one of the walls of the cooling channel 70 from which the flow deflector plate protrudes. may not come into contact with any or all of the

Alternatively, the leading end 80a of the flow deflection plate 80 may contact or be integrally formed with another web. Briefly, in a non-illustrated embodiment, the flow deflection plate 80 may extend between the two webs 60.

As shown in FIG. 7M , the side end of one or more flow deflection plates 80 may be connected to the pressure side 102 . In other embodiments the flow deflection plate 80 may be connected to the suction side (not shown) or one or more flow deflector plates 80 may alternatively be connected to the pressure side 102 and the suction side 104 (also not shown). can be connected

Moreover, the heights of the one or more flow deflection plates 80a, 80 inside the cooling channel may be different, as shown on the left side of Fig. 7m.

Also, the height of the single flow deflector plate 80 protruding from the surface of the web can be varied to have a near maximum height on the pressure side 102 and a smaller height on the suction side 104 or vice versa.

Although the technology has been described in detail with reference to specific embodiments, it should be understood that the technology is not limited to these precise embodiments. Rather, in view of the present disclosure describing exemplary modes for practicing the invention, many modifications and variations will be suggested to those skilled in the art without departing from the scope of the appended claims. Accordingly, the scope of the present invention is indicated by the following claims rather than by the foregoing description. All changes, modifications and variations coming within the meaning and scope of equivalence of the claims are to be considered within their scope.

Claims (15)

A turbomachine part for a gas turbine, the turbomachine part comprising:
- platform; and
- an airfoil extending from the platform, comprising an airfoil having a base adjacent to the platform and a leading end spaced from the base along the longitudinal direction of the airfoil;
The airfoil is:
- a pressure side and a suction side which intersect at the leading and trailing edges and define the inner space of the airfoil;
- at least one web disposed in the interior space of the airfoil and extending between the pressure side and the suction side;
- at least two cooling channels for the flow of cooling air formed in the inner space of the airfoil and extending along the longitudinal direction of the airfoil and formed by at least the web and the pressure side and/or the suction side;
shaped to deflect at least a portion of the cooling air projecting outward from the web into the cooling channel and flowing in the cooling channel along the longitudinal direction of the airfoil towards the at least one target area on the pressure side and the suction side. Further comprising a floating deflection plate,
the cooling channel includes an inlet where the base of the airfoil intersects the top surface of the platform, and the flow deflection plate is spaced from the inlet of the cooling channel;
The flow deflection plate protrudes from the surface of the web,
The plurality of flow deflection plates are spaced apart from each other at predetermined intervals in the longitudinal direction of the airfoil and arranged in an array,
The plurality of flow deflection plates are inclined, turbomachine parts. According to claim 1,
The turbomachine part according to claim 1, wherein the flow deflector plate is configured such that a blockage coefficient due to the flow deflector plate is 0.15 or more. According to claim 2,
The blockage coefficient is greater than or equal to 0.2 and less than 0.9. According to claim 3,
The blockage coefficient is:
Blockage factor = (D _H,wo - D _H,w )/D _H,wo
- D _H,wo denotes the hydraulic diameter of the cooling channel without flow deflection plate and D _H,w denotes the hydraulic diameter of the cooling channel with flow deflection plate. According to claim 4,
The hydraulic diameter of the cooling channel without flow deflector is:
D _H,wo = 4(A _wo /P _wo )
A _wo denotes the cross-sectional area of the cooling channel without the flow deflector plate, and P _wo denotes the circumference of the cross-section of the cooling channel without the flow deflector plate; and/or
The hydraulic diameter of the cooling channel with flow deflector is:
D _H,w = 4(A _w /P _w )
- A _w denotes the cross-sectional area of the cooling channel with the flow deflection plate and P _wo denotes the circumference of the cross-section of the cooling channel with the flow deflection plate. delete According to claim 1,
wherein the flow deflecting plate has an elongated shape and is oriented to extend between a base of the airfoil and a tip of the airfoil. delete According to claim 1,
The at least one flow deflection plate is:
- rib type,
- pin-fin,
- straight or curved extension bars, or
- a U-shaped bar open at the tip,
- curved ribs between 5-75% relative to said longitudinal direction,
A turbomachine part comprising a shape selected from at least one of According to claim 1,
The turbomachine part according to claim 1 , wherein the target area comprises at least one heat transfer enhancing element. According to claim 10,
wherein the flow deflector plate is shaped to deflect the cooling air towards the at least one heat transfer enhancing element, the cooling air deflected by the flow deflecting plate directly impacting the at least one heat transfer enhancing element. According to claim 1,
The turbomachine part according to claim 1 , wherein the flow deflection plate is integrally formed with the web. According to claim 1,
The flow deflection plate,
- a base adjacent to the web surface from which the flow deflecting plate protrudes outward into the cooling channel; and
- comprising a tip spaced apart from the base,
The turbomachine part according to claim 1 , wherein the tip of the flow-deflecting plate is free hanging or the tip of the flow-deflecting plate is in contact with another web. According to claim 1,
The turbomachine part is a blade or vane, the turbomachine part. A gas turbine comprising a turbomachine part according to any one of claims 1 to 5, 7 and 9 to 14.

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