Trailing edge cooling circuit for turbomachine airfoil

Abstract

To provide a trailing edge cooling circuit for a turbomachine airfoil.SOLUTION: An airfoil includes a leading edge, a trailing edge, and a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge. The pressure side wall and the suction side wall define a body region and a trailing edge region. The body region extends from the leading edge to the trailing edge region and defines an upstream plenum. The trailing edge region extends from the body region to the trailing edge. The trailing edge region defines pressure side channels and suction side channels in fluid communication with the upstream plenum and arranged in a trussed structure to reduce stress in the trailing edge region. The pressure side channels are disposed adjacent to the pressure side wall, and the suction side channels are disposed adjacent to the suction side wall.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present disclosure relates generally to an airfoil for a turbomachine having a trailing edge cooling circuit, and more particularly, to a trailing edge cooling circuit having separate pressure side and suction side cooling channels. [Background technology]

[0002] Turbomachines are used in various industries and applications for the purpose of energy transfer. For example, a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (such as natural gas) are mixed in the combustion section and burned in the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to produce work. For example, the expansion of the combustion gases in the turbine section rotates a rotor shaft connected to a generator, for example, to generate electricity. The spent combustion gases are then exhausted from the turbine section via the exhaust section.

[0003] During turbomachine operation, various hot gas path components in the system are exposed to high temperature flows that can cause stress on the hot gas path components and reduce their service life. Generally, higher temperatures lead to better turbomachine performance, efficiency, and power output, so hot gas path components exposed to higher temperatures must be cooled to enable the gas turbine system to operate with higher temperatures.

[0004] Forced air cooling becomes necessary when the maximum localized temperature of a hot gas path component approaches the melting temperature of the hot gas path component. For this reason, turbine rotor blades and static nozzle airfoils often require complex cooling schemes in which air (usually bleed air from the compressor section) is forced through internal cooling passages in the airfoil and exhausted through cooling holes in the airfoil surface to transfer heat from the hot gas path component.

[0005] The trailing edge region of an airfoil generally experiences higher thermal stresses than other regions of the airfoil. Conventional trailing edge regions often include a pin bank (or pin array) that includes multiple pins, each of which extends directly between the pressure and suction side walls of the airfoil. However, there are problems with the use of pin banks. The pressure side wall is often hotter than the suction side wall, and because the pin bank provides a direct and discrete connection between the pressure and suction sides, heat is conductively transferred from the pressure side to the suction side. This is disadvantageous because it places undesirable thermal stresses on the individual pins of the pin bank, especially those near the airfoil platform. Furthermore, the pins in the pin bank configuration are relatively weak structures when compared to other shapes of the airfoil. Therefore, there is a need for an improved trailing edge cooling circuit that redistributes and reduces operational stresses in the trailing edge region without the use of pin banks. Summary of the Invention

[0006] Aspects and advantages of the airfoils and turbomachines according to the present disclosure will be set forth in part in the description which follows, or will be obvious from the description, or may be learned by practice of the art.

[0007] According to one embodiment, an airfoil is provided. The airfoil includes a leading edge, a trailing edge, a pressure sidewall extending between the leading edge and the trailing edge, and a suction sidewall extending between the leading edge and the trailing edge. The pressure sidewall and the suction sidewall define a body region and a trailing edge region. The body region extends from the leading edge to the trailing edge region, and the trailing edge region extends from the body region to the trailing edge. The body region defines an upstream plenum extending along a span of the airfoil. The trailing edge region is in flow communication with the upstream plenum and defines a plurality of pressure side channels and a plurality of suction side channels disposed in a truss structure. The plurality of pressure side channels are disposed adjacent the pressure sidewall, and the plurality of suction side channels are disposed adjacent the suction sidewall.

[0008] According to another embodiment, a turbomachine is provided. The turbomachine includes a compressor section, a combustion section disposed downstream of the compressor section, and a turbine section disposed downstream of the combustion section. A rotor blade is disposed in one of the compressor section or the turbine section. The rotor blade includes a shank portion and an airfoil extending from the shank portion. The airfoil includes a leading edge, a trailing edge, a pressure sidewall extending between the leading edge and the trailing edge, and a suction sidewall extending between the leading edge and the trailing edge. The pressure sidewall and the suction sidewall define a body region and a trailing edge region. The body region extends from the leading edge to the trailing edge region, and the trailing edge region extends from the body region to the trailing edge. The body region defines an upstream plenum extending along a span of the airfoil. The trailing edge region is in flow communication with the upstream plenum and defines a plurality of pressure side channels and a plurality of suction side channels arranged in a truss structure. The plurality of pressure side channels are disposed adjacent to the pressure sidewall and the plurality of suction side channels are disposed adjacent to the suction sidewall.

[0009] These and other features, aspects, and advantages of the airfoil and turbomachine of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present technology and, together with the description, serve to explain the principles of the technology. [Brief description of the drawings]

[0010] A full and enabling disclosure of the present airfoil and turbomachine, including the best mode of making and using the present system and method, directed to one of ordinary skill in the art, is set forth in this specification, which makes reference to the accompanying drawings. [Figure 1] 1 is a schematic diagram of a turbomachine according to an embodiment of the present disclosure. [Diagram 2] 1 illustrates a perspective, partial cutaway view of a rotor blade according to an embodiment of the present disclosure. [Diagram 3] FIG. 2 is a cross-sectional perspective view of a portion of an airfoil trailing edge region including a trailing edge cooling circuit according to an embodiment of the present disclosure. [Figure 4] 2 illustrates a cross-sectional view in a radial-cross section of an airfoil trailing edge region having a trailing edge cooling circuit according to an embodiment of the present disclosure; [Diagram 5] 2 illustrates a cross-sectional view in a radial-cross section of an airfoil trailing edge region having a trailing edge cooling circuit according to an embodiment of the present disclosure; [Figure 6] 6 illustrates a cross-sectional view of the trailing edge region of the airfoil of FIG. 4 taken along line 6-6, in accordance with an embodiment of the present disclosure. [Figure 7] 2 illustrates a cross-sectional view of a trailing edge region of an airfoil according to an embodiment of the present disclosure. [Figure 8] 2 is a cross-sectional view of a trailing edge region of an airfoil according to an embodiment of the present disclosure; [Figure 9] 2 illustrates a cross-sectional view of a trailing edge region of an airfoil according to an embodiment of the present disclosure. [Figure 10] 2 illustrates a cross-sectional view in a radial-cross section of an airfoil trailing edge region having a trailing edge cooling circuit according to an embodiment of the present disclosure; [Figure 11] 11 illustrates a cross-sectional view of the trailing edge region of the airfoil of FIG. 10 taken along line 11-11, in accordance with an embodiment of the present disclosure. [Figure 12] 1 is a perspective view of a rotor blade according to an embodiment of the present disclosure; [Figure 13] FIG. 13 is a top view of the airfoil trailing edge portion of the rotor blade of FIG. 12. [Figure 14]13 is a perspective cross-sectional view of a trailing edge portion of the rotor blade of FIG. 12. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] Next, embodiments of the airfoil and turbomachine of the present invention will be described in detail. Each example is provided for purposes of explanation, not limitation. Indeed, it will be apparent to those skilled in the art that modifications and variations can be made in the present technology without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield still a further embodiment. Thus, the present disclosure is intended to cover such modifications and variations as come within the scope of the appended claims and their equivalents.

[0012] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Moreover, unless otherwise specified, all embodiments described herein should be considered exemplary.

[0013] The detailed description uses numbers and letters to refer to features in the drawings. Like or similar designations in the drawings and description are used to refer to like or similar parts of the invention. In this specification, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another, and are not intended to imply the position or importance of the individual components.

[0014] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that two or more regions defining a channel are joined to one another such that fluid can communicate (i.e., flow) between the defined regions.

[0015] As used herein, the terms "upstream" (or "forward") and "downstream" (or "rearward") refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction in which a fluid flows, and "downstream" refers to the direction in which a fluid flows. However, as used herein, the terms "upstream" and "downstream" can also refer to electrical flow. The term "radial" refers to a relative direction that is substantially perpendicular to an axial centerline of a particular component, the term "axial" refers to a relative direction that is substantially parallel and / or coaxially aligned with an axial centerline of a particular component, and the term "circumferential" refers to a relative direction that extends around an axial centerline of a particular component.

[0016] Approximate terms such as "about," "approximately," "generally," and "substantially" are not limited to the exact value specified. In at least some instances, the approximation term may correspond to the precision of an instrument for measuring a value, or the precision of a method or machine for constructing or manufacturing a component and / or system. For example, it may refer to being within a margin of 1, 2, 4, 5, 10, 15, or 20 percent for an individual value, a range of values, and / or any of the endpoints defining a range of values. When used in the context of an angle or direction, such terms include a range of 10 degrees greater or less than the stated angle or direction. For example, "approximately vertical" includes a direction within 10 degrees of vertical in any direction, such as clockwise or counterclockwise.

[0017] Terms such as "coupled," "fixed," "attached," and the like, unless otherwise specified herein, refer to both direct coupling, fixing, or attachment, as well as indirect coupling, fixing, or attachment through one or more intermediate components or features. Terms such as "directly coupled," "directly fixed," "directly attached," and the like, mean that two components are joined in contact with each other and that there are no intermediate components or features present.

[0018] As used herein, the terms "comprises," "comprising," "includes," "has," "having," or other variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, article, or apparatus consisting of a list of features is not necessarily limited to only those features, but may include other features not expressly listed or inherent to such process, method, article, or apparatus. Furthermore, unless expressly stated to the contrary, "and / or" refers to a condition that is satisfied by any one of the following: A is true (or present) and B is false (or absent), A is false (or absent) and B is true (or present), and both A and B are true (or present).

[0019] Throughout this specification and claims, where range limitations are combined and interchanged, unless the context or language dictates otherwise, such ranges are specific and include all subranges contained therein. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0020] Referring now to the drawings, Figure 1 is a schematic diagram of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine engine 10. Although industrial or land-based gas turbine engines are shown and described herein, the present disclosure is not limited to industrial or land-based gas turbine engines unless otherwise specified in the claims. For example, the invention described herein may be used with any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0021] As shown in Figure 1, a gas turbine engine 10 generally includes a compressor section 12. The compressor section 12 includes a compressor 14. The compressor section 12 includes an inlet 16 disposed at an upstream end of the gas turbine engine 10. The gas turbine engine 10 further includes a combustion section 18 having one or more combustors 20 disposed downstream from the compressor section 12. The gas turbine engine 10 further includes a turbine section 22 (i.e., an expansion turbine) downstream from the combustion section 18. A shaft 24 extends generally axially through the gas turbine engine 10 and couples the compressor section 12 and the turbine section 22.

[0022] The compressor section 12 may generally include a number of rotor disks 21 and a number of rotor blades 23 extending radially outward from and coupled to each rotor disk 21. Each rotor disk 21, in turn, may be coupled to or form a forward portion of a shaft 24 extending through the compressor section 12. The rotor blades 23 of the compressor section 12 may include turbomachine airfoils that define an airfoil (e.g., having a leading edge, a trailing edge, and a sidewall extending between the leading edge and the trailing edge). Additionally, the compressor section 12 includes stator vanes 19 disposed between the rotor blades 23. The stator vanes 19 may extend from and be coupled to the compressor casing 11.

[0023] The turbine section 22 may generally include a number of rotor disks 27 and a number of rotor blades 28 extending radially outward from and interconnected to each rotor disk 27. Each rotor disk 27 may in turn be coupled to or form an aft end portion of a shaft 24 extending through the turbine section 22. The turbine section 22 further includes an outer casing 32 circumferentially surrounding the aft end portion of the shaft 24 and the rotor blades 28. The turbine section 22 may include stator vanes or static nozzles 26 extending radially inward from the outer casing 32. The rotor blades 28 and the stator vanes 26 may be alternately and stepped along an axial centerline 30 of the gas turbine engine 10. Both the rotor blades 28 and the stator vanes 26 may include turbomachine airfoils that define airfoils (e.g., having a leading edge, a trailing edge, and sidewalls extending between the leading edge and the trailing edge).

[0024] During operation, ambient air or other working fluid is drawn into the inlet 16 of the compressor 14 and gradually compressed to provide compressed air 35 to the combustion section 18. The compressed air 35 enters the combustion section 18 and is mixed with fuel to form a combustible mixture. The combustible mixture is combusted in the combustion chamber 25 of the combustor 20 to generate combustion gases 41 that enter the combustion chamber 25 and enter the turbine section 22. Energy (kinetic and / or thermal energy) is transferred from the combustion gases 41 to the rotor blades 28, which rotate the shaft 24 to produce mechanical work. The spent combustion gases 41 (also referred to as "exhaust gases") exit the turbine section 22 and flow through the exhaust diffuser 34 and across a number of struts or main airfoils 43 located within the exhaust diffuser 34.

[0025] Gas turbine engine 10 may define a cylindrical coordinate system having an axial direction A extending along axial centerline 30, a radial direction R perpendicular to axial centerline 30, and a circumferential direction C extending around axial centerline 30.

[0026] FIG. 2 provides a perspective partial cutaway view of an exemplary rotor blade 50. The rotor blade 50 may be the rotor blade 23 disposed in the compressor section 12 or the rotor blade 28 disposed in the turbine section 22, as described above with reference to FIG. 1. As shown in FIG. 2, the rotor blade 50 generally includes a shank portion 37 and an airfoil 40 extending outwardly from the shank portion 37. For example, the shank portion 37 may include a mounting portion 38 and a platform 42, and the airfoil 40 may extend along a radial direction R from the platform 42. The platform 42 generally serves as a radially inner boundary for gases flowing through the gas turbine engine 10 (e.g., air flowing through the compressor section 12 or combustion gases 41 flowing through the hot gas path of the turbine section 22, as shown in FIG. 1). The platform 42 extends along an axial direction A from a leading face 84 to a trailing face 82. 2, the attachment portion 38 of the shank portion 37 may extend radially inward from the platform 42 and may include a root structure, such as a dovetail, configured to interconnect or secure the rotor blade 50 to the rotor disk 21, 27 (FIG. 1). In an exemplary embodiment, the rotor blade 50 may be a turbine rotor blade (such as rotor blade 28 described above with reference to FIG. 1), which may benefit from one or more of the present cooling circuits.

[0027] The airfoil 40 includes a pressure sidewall 44 and an opposing suction sidewall 46. The pressure sidewall 44 and the suction sidewall 46 extend substantially radially outward from the platform 42 in a span from a root 48 of the airfoil 40, which may be defined at an intersection between the airfoil 40 and the platform 42, to a tip 51 of the airfoil 40. The pressure sidewall 44 is connected to the suction sidewall 46 at a leading edge 52 and a trailing edge 54 downstream of the leading edge 52 of the airfoil 40, the airfoil 40 thus extending between the leading edge 52 and the trailing edge 54. The pressure sidewall 44 generally defines an aerodynamically concave outer surface of the airfoil 40. Similarly, the suction sidewall 46 may generally define an aerodynamically convex outer surface of the airfoil 40. The tip 51 is located radially opposite the root 48. As such, tip 51 generally defines the radially outermost portion of rotor blade 50 and thus may be configured to be disposed adjacent a stationary shroud or seal (not shown) of gas turbine engine 10. Tip 51 may include a tip cavity 66 or tip shroud (not shown).

[0028] As shown in FIG. 2, the rotor blade 50 may be at least partially hollow, for example, the rotor blade 50 may include a cooling circuit 72 defined therein. The cooling circuit 72 may include a plurality of cooling passages 56 (shown partially in dashed lines in FIG. 2) that may be circumscribed within the rotor blade 50 for passing a coolant 58 through the airfoil 40 between the pressure sidewall 44 and the suction sidewall 46, thus providing convection cooling thereto. The cooling passages 56 may be at least partially defined by and between a plurality of ribs 74. The ribs 74 extend partially through the cooling circuit 72 generally along the radial direction R, as shown in FIG. 2, for example. The ribs 74 may extend completely through the cooling circuit 72 between the pressure sidewall 44 and the suction sidewall 46. The plurality of ribs 74 may thereby partition the cooling circuit 72 and at least partially form or define the cooling passages 56. For example, each rib 74 may terminate radially adjacent one of the root turn 76 or the tip turn 78. The root turn 76 may be defined in part by a floor 77 that defines the radially innermost boundary of the root turn 76.

[0029] The coolant 58 may include a portion of compressed air from the compressor section 12 ( FIG. 1 ), and / or steam, or other suitable gas or other fluid for cooling the airfoil 40. One or more cooling passage inlets 60 are disposed along the rotor blade 50. In some embodiments, the one or more cooling passage inlets 60 are formed in, along, or by the mounting portion 38. The cooling passage inlets 60 are in fluid communication with at least one corresponding cooling passage 56. A plurality of coolant outlets 64 may be in fluid communication with a tip cavity 66. Each cooling passage 56 is in fluid communication with at least one coolant outlet 64. In some embodiments, the tip cavity 66 may be at least partially surrounded by a pressure side tip rail 68 and a suction side tip rail 70.

[0030] 2, the cooling passages 56 extend inside each of the shank portion 37 and the airfoil 40. For example, the cooling passages 56 may extend between the shank portion 37 and the airfoil 40, e.g., from the shank portion 37 to the airfoil 40, e.g., from one or more cooling passage inlets 60 in the shank portion 37 to at least one coolant outlet 64 in the tip 51 of the airfoil 40.

[0031] The airfoil 40 may define a camber axis 94 intermediate the pressure sidewall 44 and the suction sidewall 46. The camber axis 94 may extend (intersect) between the leading edge 52 and the trailing edge 54. That is, the camber axis 94 may be an imaginary line extending from the leading edge 52 to the trailing edge 54, and the camber axis 94 may be the average curvature of the pressure sidewall 44 and the suction sidewall 46. The camber axis 94 may be curved and / or contoured to correspond to the curvatures of the pressure sidewall 44 and the suction sidewall 46. The lateral direction T may be defined as being perpendicular to the camber axis 94.

[0032] The cooling passages 56 may include a leading edge passage 88, one or more intermediate passages 90, and a trailing edge passage 92. The leading edge passage 88 may be defined by the leading edge 52 and the ribs 74. The leading edge passage 88 may be the cooling passage 56 located closest to the leading edge 52. Each of the intermediate passages 90 may be defined between two ribs 74. The intermediate passages 90 may be located between the leading edge passage 88 and the trailing edge passage 92. The trailing edge passage 92 may be defined by the ribs 74 and the trailing edge cooling circuit 100.

[0033] In many embodiments, the airfoil 40 may include a body region 101 and a trailing edge region 102. The body region 101 and the trailing edge region 102 may extend across the entire span of the airfoil 40 (e.g., radially between the root 48 and the tip 51). The body region 101 may extend along the camber axis 94 between the leading edge 52 and the trailing edge region 102, and the trailing edge region 102 may extend along the camber axis 94 from the body region 101 to the trailing edge 54. Further, the trailing edge region 102 may extend from the trailing edge 54 along the camber axis 94 between about 10% and about 40% of the total length of the camber axis 94, or between about 10% and about 35% of the total length of the camber axis 94, or between about 10% and about 30% of the total length of the camber axis 94, or between about 10% and about 25% of the total length of the camber axis 94, or between about 10% and about 20% of the total length of the camber axis 94, etc. As will be appreciated, the trailing edge region 102 may generally be subject to higher thermal stresses during operation of the gas turbine engine 10. The trailing edge cooling circuit 100 may be disposed in the trailing edge region 102 to provide convection cooling to the trailing edge region 102, which may increase the hardware life of the airfoil 40.

[0034] 3, a cross-sectional perspective view of a trailing edge region 102 of an airfoil 40 having a trailing edge cooling circuit 100 is shown in accordance with an embodiment of the present disclosure. As shown, the trailing edge cooling circuit 100 includes a plurality of pressure side channels 104 and a plurality of suction side channels 106. The pressure side channels 104 and the suction side channels 106 may be radially spaced apart from one another. Additionally, the plurality of pressure side channels 104 and the plurality of suction side channels 106 may be fluidly isolated. For example, a plurality of shared walls 108 may radially separate the plurality of pressure side channels 104 and the plurality of suction side channels 106. In particular, the pressure side channels 104 and the suction side channels 106 may each be partially defined by a shared wall 108 of the plurality of shared walls 108. The shared walls 108 form a truss structure that distributes stress across the shared walls 108 and the trailing edge region 102.

[0035] For example, each shared wall 108 can define a pressure side channel 104 of the plurality of pressure side channels 104 and an adjacent suction side channel 106 of the plurality of suction side channels 106. Each shared wall 108 of the plurality of shared walls 108 can extend generally obliquely relative to the radial direction R between an interior of the suction side wall 46 and an interior of the pressure side wall 44. In some embodiments, each shared wall 108 can slope radially outward as the shared wall 108 extends between one of the pressure side wall 44 or the suction side wall 46 to the other of the pressure side wall 44 or the suction side wall 46.

[0036] Each pressure side channel 104 of the plurality of pressure side channels 104 may extend from a pressure side inlet 118 to a pressure side outlet 120. Similarly, each suction side channel 106 of the plurality of suction side channels 106 may extend from a suction side inlet 122 to a suction side outlet 124. As shown in FIG. 3 , the pressure side channels 104 may converge in cross-sectional area as the pressure side channels 104 extend between the pressure side inlet 118 and the pressure side outlet 120. Additionally, the suction side channels 106 may converge in cross-sectional area between the suction side inlet 122 and the suction side outlet 124. In particular, both the radial and transverse lengths (e.g., perpendicular to the camber axis 94) of the channels 104, 106 may converge (or decrease) as the channels 104, 106 extend toward the trailing edge 54.

[0037] In at least one exemplary embodiment, because the plurality of pressure side channels 104 and the plurality of suction side channels 106 are fluidically isolated, the shape of the pressure side channel 104 and the shape of the suction side channel 106 may be customized independently of the other. For example, the size, shape, radial length, lateral length, and / or cross-sectional area of ​​one or more of the pressure side channels 104 of the plurality of pressure side channels 104 may be altered or different from another one or more of the pressure side channels 104 of the plurality of pressure side channels 104 and / or one or more of the suction side channels 106 of the plurality of suction side channels 106. Similarly, the size, shape, radial length, lateral length, and / or cross-sectional area of ​​one or more of the plurality of suction side channels 106 may be altered or different from another one or more of the plurality of suction side channels 106 and / or one or more of the plurality of pressure side channels 104. Regardless of the differences in shape, in one embodiment, the plurality of pressure side channels 104 and the plurality of suction side channels 106 include walls that extend from one of the pressure side walls 44 or the suction side walls 46 to the other of the pressure side walls 44 or the suction side walls 46, thus forming a truss structure. As previously mentioned, in some embodiments, the plurality of pressure side channels 104 and the plurality of suction side channels 106 are defined in part by a shared wall 108 that is common to one of the pressure side channels 104 and an adjacent one of the suction side channels 106.

[0038] 4, a cross-sectional view of a trailing edge region 102 of an airfoil 40 having a trailing edge cooling circuit 100 in a radial cross section is illustrated in accordance with an embodiment of the present disclosure. As illustrated, the plurality of shared walls 108 may include a plurality of first shared walls 110 and a plurality of second shared walls 112. In forming a truss structure, each of the plurality of first shared walls 110 may extend obliquely relative to the radial direction R from the pressure side wall 44 to the suction side wall 46, and the plurality of second shared walls 112 may extend obliquely relative to the radial direction R from the suction side wall 46 to the pressure side wall 44. Each of the first shared walls 110 may intersect with one of the second shared walls 112 at the pressure side wall 44 (at a first intersection 114) and with a different one of the second shared walls 112 at the suction side wall 46 (at a second intersection 116). Stated another way, each of the second shared walls 112 may intersect with one of the first shared walls 110 at the pressure side wall 44 (at a first intersection 114) and with a different one of the first shared walls 110 at the suction side wall 46 (at a second intersection 116). The extension of the walls 112, 114 between the pressure and suction side walls 44, 46 distributes stresses and reduces discrete stress points that can occur in conventional pin banks.

[0039] The pressure-side channel 104 may be collectively defined by a first shared wall 110 of the plurality of first shared walls 110, a second shared wall 112 of the plurality of second shared walls 112, and an interior of the pressure side wall 44. Similarly, the suction-side channel 106 may be collectively defined by a first shared wall 110 of the plurality of first shared walls 110, a second shared wall 112 of the plurality of second shared walls 112, and an interior of the suction side wall 46.

[0040] In some embodiments, as shown in FIG. 4, the pressure side channel 104 and the suction side channel 106 may define a triangular shaped region 109 (e.g., cross-sectional area). In particular, the pressure side channel 104 and the suction side channel 106 may define a triangular shaped region 109 in a radial-cross-section. Briefly returning to FIG. 3, the pressure side channel 104 may converge in cross-sectional area between the pressure side inlet 118 and the pressure side outlet 120. Similarly, the suction side channel 106 may converge in cross-sectional area between the suction side inlet 122 and the suction side outlet 124. For example, the triangular shaped region 109 may converge (or continuously decrease) as the pressure side channel 104 and the suction side channel 106 extend from their respective inlets 118, 122 to their respective outlets 120, 124.

[0041] 5, a cross-sectional view of a trailing edge region 102 of an airfoil 40 having a trailing edge cooling circuit 100 in a radial cross-section is illustrated in accordance with another embodiment of the present disclosure. As illustrated, the trailing edge cooling circuit 100 may include a plurality of pressure side channels 206 and a plurality of suction side channels 208 defined by conduits (not separately numbered). In particular, the pressure side channels 206 and the suction side channels 208 may be arranged in radial rows 212, 214. For example, the plurality of pressure side channels 206 may be arranged in the pressure side radial row 212, and the plurality of suction side channels 208 may be arranged in the suction side row 214. In particular, the plurality of pressure side channels 206 may each be centrally disposed along a first radial line 216 proximate to the pressure side wall 44 (e.g., closer to the pressure side wall 44 than the suction side wall 46). Similarly, each of the plurality of suction side channels 208 may be centrally disposed along a second radial line 218 proximate to the suction sidewall 46 (eg, closer to the suction sidewall 46 than to the pressure sidewall 44).

[0042] 5, each of the pressure-side channel 206 and the suction-side channel 208 may define an oval-shaped cross-sectional area 209. In particular, the oval-shaped area 209 may be defined in a radial-cross-section, and the oval-shaped area 209 may include a major axis 220 and a minor axis 222. The major axis 220 may be the longest dimension of the oval-shaped area 209, and the minor axis 222 may be the shortest dimension of the oval-shaped area 209. The major axis 220 may be parallel to the radial direction R, and the minor axis 222 may be parallel to the lateral direction T.

[0043] In many embodiments, as shown in FIG. 5, the plurality of suction side channels 208 may be radially offset relative to the plurality of pressure side channels 206 such that each suction side channel 208 radially overlaps at least one (or two) of the plurality of pressure side channels 206. For example, each suction side channel 208 may be radially disposed between two of the plurality of pressure side channels 206. Similarly, each pressure side channel 206 may be radially disposed between two of the plurality of suction side channels 208. The channels 206, 208 may be defined via a solid material connecting the pressure side wall 44 and the suction side wall 46 (as shown), or each channel 206, 208 may be defined by a channel wall that surrounds the respective channel 206, 208 and is joined to the channel wall of a laterally adjacent channel 208, 206, thereby forming a stress-mitigating lattice.

[0044] 6, a cross-sectional view of a trailing edge region 102 of the airfoil 40 including a trailing edge cooling circuit 100 is illustrated along line 6-6 shown in FIG. 4 in accordance with an embodiment of the present disclosure. The trailing edge region 102 of the airfoil 40 may include a portion of the suction sidewall 46 and a portion of the pressure sidewall 44, with the camber axis 94 extending through the trailing edge region 102 between the suction sidewall 46 and the pressure sidewall 44 to the trailing edge 54.C may extend along the camber axis 94, and the transverse direction T may extend along the axial direction A C. 6, the trailing edge cooling circuit 100 may include a pressure side channel 104 and a suction side channel 106 (shown in phantom).

[0045] The pressure-side channels 104 may be at least partially disposed on a first side (e.g., a first transverse side) of the camber axis 94, and the suction-side channels 106 may be at least partially disposed on a second side (e.g., a second transverse side) of the camber axis 94. The first side may be transverse between the camber axis 94 and the pressure sidewall 44, and the second side may be transverse between the camber axis 94 and the suction sidewall 46. In particular, a majority of the pressure-side channels 104 (e.g., about 50% or more, or about 65% or more, or about 75% or more, or about 90% or more, etc.) may be disposed on the first side of the camber axis 94. Similarly, a majority of the suction-side channels 106 (e.g., about 50% or more, or about 65% or more, or about 75% or more, or about 90% or more) may be disposed on the second side of the camber axis 94.

[0046] In an exemplary embodiment, as shown in FIG. 6 , the pressure side channels 104 may extend between a pressure side inlet 118 and a pressure side outlet 120 and along a pressure side centerline 126 on a first side of the camber axis 94. Similarly, the suction side channels 106 extend between a suction side inlet 122 and a suction side outlet 124 and along a suction side centerline 128 on a second side of the camber axis 94. In such an embodiment, the pressure side centerline 126 may converge toward the camber axis 94 between the pressure side inlet 118 and the pressure side outlet 120, and the suction side centerline 128 may converge toward the camber axis 94 between the suction side inlet 122 and the suction side outlet 124. Thus, the pressure side channels 104 and the suction side channels 106 may be said to converge toward the trailing edge 54 as the pressure side channels 104 and the suction side channels 106 extend toward the trailing edge 54.

[0047] In many embodiments, the pressure side channel 104 and the suction side channel 106 may each extend to a common plenum, such as the downstream plenum 130, and may be in direct fluid communication with it. For example, the pressure side channel 104 may extend from a pressure side inlet 118 to a pressure side outlet 120 in the downstream plenum 130. Similarly, the suction side channel 106 may extend from a suction side inlet 122 to a suction side outlet 124 in the downstream plenum 130. The downstream plenum 130 may be centered on the camber axis 94 (such that the centerline of the downstream plenum 130 is aligned with the camber axis 94). In an exemplary embodiment, as shown in FIGS. 3 and 6, the pressure side channel 104 and the suction side channel 106 may have their respective centerlines 126, 126 disposed in different radial (spanwise) planes, and thus may converge (intersect) with the downstream plenum 130 via outlets 120, 124 disposed in different radial planes.

[0048] In the exemplary embodiment, one or more outlet channels 132 may extend from the downstream plenum 130 to corresponding outlets 134 at the trailing edge 54. One or more outlet channels 132 may extend directly along the camber axis 94 from the downstream plenum 130 to the trailing edge 54 to exhaust coolant from the trailing edge cooling circuit 100 (and the entire cooling circuit 72).

[0049] 7, a cross-sectional view of the trailing edge region 102 of the airfoil 40 is shown in accordance with another embodiment of the present disclosure. As shown, the pressure side channel 104 and the suction side channel 106 may be defined at least partially within the same axial cross-section. In such an embodiment, a dividing wall 136 may separate and partially define the pressure side channel 104 and the suction side channel 106. The dividing wall 136 may extend generally axially and be disposed laterally between the suction channel 106 and the pressure side channel 104. Additionally, the dividing wall 136 may extend at least partially along the camber axis 94. Other walls defining the channels 104, 106 (e.g., walls spanning between the pressure side wall 44 and the suction side wall 46 in various radial planes) are not shown.

[0050] In various embodiments, the pressure-side channels 104 may terminate forward (or upstream) of the trailing edge 54 such that the suction-side channels 106 extend axially beyond the pressure-side channels 104. For example, the suction-side channels 106 may extend from the suction-side inlets 122 to the outlet channels 132 at the trailing edge 54, and the pressure-side channels 104 may extend from the pressure-side inlets 118 to the pressure-side outlet channels 138. The pressure-side outlet channels 138 may extend from the pressure-side channels 104 to an outlet on the pressure sidewall 44. The pressure-side outlet channels 138 may be generally oblique to the camber axis 94 (and pressure sidewall 44) in the axial-transverse plane such that the pressure-side outlet channels 138 advantageously discharge coolant obliquely to film cool the pressure sidewall 44 upstream of the trailing edge 54.

[0051] 8 and 9, a cross-sectional view of the trailing edge region 102 of the airfoil 40 is illustrated in accordance with an embodiment of the present disclosure. As illustrated, the divider 136 may include an axial portion 142 and a transverse portion 144. The pressure side channel 104 may terminate forward (or upstream) of the trailing edge 54 at the transverse portion 144 of the divider 136 such that the suction side channel 106 extends axially beyond the pressure side channel 104. In such an embodiment, the suction side channel 106 may include a first portion 146 and a second portion 148. The first portion 146 may extend from the suction side inlet 122 to the transverse portion 144 of the divider 136, and the second portion 148 may extend from the transverse portion 144 of the divider 136 to the outlet channel 132 and / or 152. The first portion 146 may have a smaller transverse width than the second portion 148. The first portion 146 may be defined (transversely) between the suction sidewall 46 and the partition wall 136, and the second portion 148 may be defined (transversely) between the pressure sidewall 44 and the suction sidewall 46.

[0052] 8 and 9, both the pressure side channel 104 and the suction side channel 106 may include separate pressure side outlet channels. For example, the pressure side channel 104 may extend to a first pressure side outlet channel 150, and the suction side channel 106 may include a second pressure side outlet channel 152 disposed downstream of the first pressure side outlet channel 150. The first pressure side outlet channel 150 may extend generally obliquely (with respect to the camber axis 94 and the pressure side wall 44) from a terminus of the pressure side channel 104 to an outlet on the pressure side wall 44.

[0053] In some embodiments, the second pressure side outlet channel 152 may extend generally diagonally (relative to the camber axis 94 and the pressure side wall 44) from the end of the suction side channel 106 to an outlet on the pressure side wall 44, as shown in FIG. 8. In such embodiments, the second pressure side outlet channel 152 may be the only outlet channel to the suction side channel 106 (e.g., the trailing edge cooling circuit 100 may not include an outlet channel at the trailing edge 54). In other embodiments, the suction side channel 106 may further include a trailing edge outlet channel 132 downstream of the second pressure side outlet channel 152 with respect to coolant flow (left to right) through the trailing edge cooling circuit 100, as shown in FIG.

[0054] 10, a cross-sectional view of a trailing edge region 102 of an airfoil 40 having a trailing edge cooling circuit 100 in a radial-cross section is shown in accordance with another embodiment of the present disclosure. As shown, the trailing edge cooling circuit 100 may include a plurality of pressure side channels 306 and a plurality of suction side channels 308. In particular, the pressure side channels 306 and the suction side channels 308 may be arranged in radial rows 312, 314. For example, the plurality of pressure side channels 306 may be arranged in the pressure side radial row 312 and the plurality of suction side channels 308 may be arranged in the suction side radial row 314. In particular, the plurality of pressure side channels 306 may each be centrally disposed along a first radial line 316 proximate to the pressure side wall 44 (e.g., closer to the pressure side wall 44 than to the suction side wall 46). Similarly, each of the plurality of suction side channels 308 may be centrally disposed along a second radial line 318 proximate to the suction sidewall 46 (eg, closer to the suction sidewall 46 than to the pressure sidewall 44).

[0055] 10 , each of the pressure side channel 306 and the suction side channel 308 may define an elliptical region 309. In particular, the elliptical region 309 may be defined in a radial-transverse plane, and the elliptical region 309 may include a major axis 320 and a minor axis 322. The major axis 320 may be the longest dimension of the elliptical region 309, and the minor axis 322 may be the shortest dimension of the elliptical region 309. The major axis 320 may be parallel to the radial direction R, and the minor axis 322 may be parallel to the transverse direction T.

[0056] In many embodiments, as shown in Fig. 10, the plurality of suction side channels 308 may be radially offset relative to the plurality of pressure side channels 306 such that each suction side channel 308 radially overlaps at least one (or two) of the plurality of pressure side channels 306. Additionally, as shown in Fig. 10, the area (e.g., cross-sectional area in a radial cross section) of one of the pressure side channels 306 or the suction side channel 308 may be larger than the area (e.g., cross-sectional area in a radial cross section) of the other of the pressure side channel 306 or the suction side channel 308. For example, the area 309 of the elliptical shape of one of the pressure side channel 306 or the suction side channel 308 may be larger than the area 309 of the elliptical shape of the other of the pressure side channel 306 or the suction side channel 308. In the illustrated exemplary embodiment, the major and minor axes 320, 322 of the elliptical region 309 of the suction side channel 308 may be longer than the major and minor axes 320, 322 of the elliptical region 309 of the pressure side channel 306. In this manner, the flow of cooling air to the pressure side channel 306 and / or the suction side channel 308 may be metered based on the cooling needs by adjusting the size of the channels 306, 308.

[0057] In various embodiments, the airfoil 40 may define a dead space 324 disposed between the pressure side channel 306 and the suction side channel 308. In some embodiments, the dead space 324 may be a cavity that extends radially the entire span of the airfoil 40 (e.g., from the root 48 to the tip 51). In other embodiments, the dead space 324 may be a cavity that extends only a portion of the span of the airfoil 40. In particular, the first partition wall 326 may extend radially through the airfoil 40 and partially define the dead space 324 and one or more of the pressure side channels 306. The second partition wall 328 may extend radially through the airfoil 40 and partially define the dead space 324 and one or more of the suction side channels 308. That is, the partition walls 326 , 328 may be spaced apart from one another in the lateral direction T such that a dead space 324 is defined between the first partition wall 326 and the second partition wall 328 .

[0058] 11, a cross-sectional view of the trailing edge region 102 of the airfoil 40 including the trailing edge cooling circuit 100 taken along line 11-11 shown in FIG. 10 is illustrated in accordance with an embodiment of the present disclosure. As illustrated, the pressure side channel 306 may be defined by the first partition wall 326 and by the interior of the pressure side wall 44. The suction side channel 308 may be defined by the second partition wall 328 and the interior of the suction side wall 46. The channels 308 may each extend to a common plenum 330, and the outlet channel 332 may extend from the common plenum 330 to the trailing edge 54. The dead space 324 may include an open end 334 and a closed end 336, which may partially define the common plenum 330. In this manner, air entering the dead space 324 does not immediately exit the airfoil 40 (e.g., from the dead space 324). Rather, all air that enters the dead space 324 must eventually exit the dead space 324 and enter one of the channels 306 , 308 .

[0059] As used herein, "cooling proximity" refers to the relationship between a cooling channel (such as suction side channel 106 or pressure side channel 104) and the respective surface along which the majority of the cooling channel lies (e.g., suction sidewall 46 and pressure sidewall 44) such that the temperature of the respective surface is reduced by fluid flowing through the cooling channel. For example, pressure side channel 104 may be in cooling proximity to pressure sidewall 44 but not to suction sidewall 46. Similarly, suction side channel 106 may be in cooling proximity to suction sidewall 46 but not to pressure sidewall 44.

[0060] Figure 12 illustrates a perspective view of a rotor blade 1250 according to an embodiment of the present disclosure. Rotor blade 1250 may be the same as or similar to rotor blade 50 described above with respect to Figures 2-11. For example, rotor blade 1250 may be incorporated into gas turbine engine 10 in place of rotor blade 23 disposed in compressor section 12 or rotor blade 28 disposed in turbine section 22 described above with reference to Figure 1.

[0061] As shown in FIG. 12, the rotor blade 1250 generally includes a shank portion 1237 and an airfoil 1240 extending outwardly from the shank portion 1237. For example, the shank portion 1237 may include an attachment portion 1238 and a platform 1242, and the airfoil 1240 may extend from the platform 1242 along a radial direction R (FIG. 2). The platform 1242 generally serves as a radially inner boundary for gases flowing through the gas turbine engine 10 (e.g., air flowing through the compressor section 12 or combustion gases 41 flowing through the hot gas path of the turbine section 22, as shown in FIG. 1). The platform 1242 extends along an axial direction A (FIG. 2) from a leading face 1284 to a trailing face 1282. As shown in FIG. 12, the attachment portion 1238 of the shank portion 1237 may extend radially inward from the platform 1242 and may include a root structure configured to interconnect or secure the rotor blade 1250 to a rotor disk 21, 27 (FIG. 1). The root structure may be a dovetail in some exemplary embodiments. Further, the rotor blade 1250 may be a turbine rotor blade (such as rotor blade 28 described above with reference to FIG. 1) in some exemplary embodiments, which may benefit from one or more of the present cooling circuits.

[0062] The airfoil 1240 includes a pressure sidewall 1244 and a suction sidewall 1246 opposite the pressure sidewall 1244. The pressure sidewall 1244 and the suction sidewall 1246 extend substantially radially outward from the platform 1242 and span from a root 1248 of the airfoil 1240, which may be defined at an intersection between the airfoil 40 and the platform 42, to a tip 1251 of the airfoil 1240. The pressure sidewall 1244 is connected to the suction sidewall 1246 at a leading edge 1252 and a trailing edge 1254 downstream of the leading edge 1252 of the airfoil 1240, and the airfoil 1240 thus extends between the leading edge 1252 and the trailing edge 1254. The pressure sidewall 1244 generally constitutes an aerodynamic concave outer surface of the airfoil 1240. Similarly, suction sidewall 46 may generally define an aerodynamic convex outer surface of airfoil 1240. Tip 1251 is disposed radially opposite root 1248. As such, tip 1251 generally defines a radially outermost portion of rotor blade 1250 and thus may be configured to be disposed adjacent a stationary shroud or seal (not shown) of gas turbine engine 10. Tip 1251 may include a tip cavity or tip shroud (not shown), such as tip cavity 66 (shown in FIG. 2 ).

[0063] The airfoil 1240 may define a camber axis 1294 intermediate the pressure sidewall 1244 and the suction sidewall 1246. The camber axis 1294 may extend (intersect) between the leading edge 1252 and the trailing edge 1254. That is, the camber axis 1294 may be an imaginary line extending from the leading edge 1252 to the trailing edge 1254, and the camber axis 1294 may be the average curvature of the pressure sidewall 1244 and the suction sidewall 1246. The camber axis 1294 may be curved and / or contoured to correspond to the curvature of the pressure sidewall 1244 and the suction sidewall 1246.

[0064] In at least one exemplary embodiment, the airfoil 1240 includes a body region 1201 and a trailing edge region 1202. The body region 1201 and the trailing edge region 1202 may extend across the span of the airfoil 1240 (e.g., radially between the root 1248 and the tip 1251). The body region 1201 may extend along a camber axis 1294 between the leading edge 1252 and the trailing edge region 1202, and the trailing edge region 1202 may extend along the camber axis 1294 from the body region 1201 to the trailing edge 1254. Further, the trailing edge region 1202 may extend from the trailing edge 1254 along the camber axis 1294 to between about 10% and about 40% of the total length of the camber axis 1294, or between about 10% and about 35% of the total length of the camber axis 1294, or between about 10% and about 30% of the total length of the camber axis 1294, or between about 10% and about 25% of the total length of the camber axis 1294, or between about 10% and about 20% of the total length of the camber axis 94, etc. As will be appreciated, the trailing edge region 1202 may generally be exposed to higher thermal stresses during operation of the gas turbine engine 10. Thus, the trailing edge cooling circuit 100 may be disposed in the trailing edge region 1202 to provide convection cooling to the trailing edge region 1202, thereby increasing the hardware life of the airfoil 1240.

[0065] Figure 13 shows a top view of a portion of airfoil 1240 of rotor blade 1250 of Figure 12. Figure 14 shows a perspective cross-sectional view of a portion of rotor blade 1250 of Figure 12.

[0066] 12-14 , the body region 1201 defines an upstream plenum 1205 that extends along the span (i.e., radially) of the airfoil 1240. The upstream plenum 1205 is in fluid communication with the trailing edge region 1202. For example, the upstream plenum 1205 may be configured to receive the coolant 58 and supply the coolant 58 to the trailing edge cooling circuit 100 of the trailing edge region 1202. The coolant 58 may include a portion of the compressed air from the compressor section 12 ( FIG. 1 ), and / or steam, or any other suitable gas or other fluid for cooling the airfoil 40.

[0067] 14, the cooling circuit 100 disposed in the trailing edge region 1202 of the airfoil 1240 is the same or similar to the cooling circuit 100 disposed in the trailing edge region 102 of the airfoil 40 described above with respect to FIGS. 3-11. For example, the cooling circuit 100 includes a plurality of pressure side channels 104 and a plurality of suction side channels 106. The plurality of pressure side channels 104 and the plurality of suction side channels 106 are in fluid communication with an upstream plenum 1205 such that the flow of coolant entering the channels 104, 106 is turned (e.g., around the ribs 74) before entering the channels 104, 106 and directed primarily axially toward the trailing edge 1254 rather than being imparted with a partial radial component.

[0068] 14 , the upstream plenum 1205 and the cooling circuit 100 are disposed within the airfoil 1240. In some exemplary embodiments, the upstream plenum 1205 and / or the cooling circuit 100 may extend at least partially within the shank portion 1237 of the rotor blade 1250.

[0069] The trailing edge cooling circuits 100 described herein advantageously reduce peak thermal stresses experienced in the trailing edge region 102 by distributing the stresses over a larger connected structure (e.g., a truss structure) as opposed to concentrating the stresses on a single individual pin of the pin bank. The shared walls and / or staggered cooling channels allow the heat to spread more gradually through the trailing edge region 102 while structurally sharing the loads, reducing peak stresses. Additionally, the pressure side cooling channels 104 and the suction side cooling channels 106 can be shaped to have a large surface area adjacent the pressure side 44 and the suction side 46, respectively, which enhances cooling. Thus, the design of the pressure side cooling channels 104 and the suction side cooling channels 106 can be customized to meet desired needs, such as meeting the thermal demands of the airfoil 40, 1240, which can further reduce thermal stresses.

[0070] This specification uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems, and performing the incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they contain structural elements that do not differ from the literal language of the claims, or if they contain equivalent structural elements that do not differ insubstantially from the literal language of the claims.

[0071] Further aspects of the invention are provided by the subject matter of the following clauses. [Embodiment 1] a leading edge, a trailing edge, a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge, wherein a camber axis is defined halfway between the pressure side wall and the suction side wall; and a cooling circuit defined in the airfoil, the cooling circuit having a trailing edge cooling circuit comprising a pressure side channel and a suction side channel, the pressure side channel disposed in cooling proximity to the pressure side wall and the suction side channel disposed in cooling proximity to the suction side wall. wall) and an airfoil. [Embodiment 2] 13. The airfoil of any preceding embodiment, wherein the pressure side channel is disposed at least partially on a first side of the camber axis and the suction side channel is disposed at least partially on a second side of the camber axis, and the pressure side channel and the suction side channel each converge towards the trailing edge as the pressure side channel and the suction side channel extend towards the trailing edge. [Embodiment 3] 13. The airfoil of any preceding embodiment, wherein the pressure side channel and the suction side channel are partially defined by a shared wall disposed between the pressure side wall and the suction side wall. [Embodiment 4] 2. The airfoil of any preceding embodiment, wherein the pressure side channel extends between a pressure side inlet and a pressure side outlet and along a pressure side centerline on a first side of the camber axis, and the suction side channel extends between a suction side inlet and a suction side outlet and along a suction side centerline on a second side of the camber axis. [Embodiment 5] 13. The airfoil of any preceding embodiment, wherein the pressure side centerline converges towards the camber axis between the pressure side inlet and the pressure side outlet, and the suction side centerline converges towards the camber axis between the suction side inlet and the suction side outlet. [Embodiment 6]

[0023] The airfoil of any preceding embodiment, wherein the pressure side channel and the suction side channel are radially spaced apart from one another. [Embodiment 7] 13. The airfoil of any preceding embodiment, wherein the pressure side channel converges in cross-sectional area between the pressure side inlet and the pressure side outlet, and the suction side channel converges in cross-sectional area between the suction side inlet and the suction side outlet. [Embodiment 8]

[0023] The airfoil of any preceding embodiment, wherein the pressure side channel and the suction side channel each extend to a common plenum. [Embodiment 9] The airfoil of any preceding embodiment, wherein one or more exit channels extend from the common plenum to the trailing edge. [Embodiment 10] The airfoil of any preceding embodiment, wherein the pressure side channel extends to a pressure side exit channel. [Embodiment 11] 2. The airfoil of any preceding embodiment, wherein the pressure side exit channel is a first pressure side exit channel and the suction side channel includes a second pressure side exit channel disposed downstream of the first pressure side exit channel. [Embodiment 12] 13. The airfoil of any preceding embodiment, wherein the pressure side channel and the suction side channel define one of a triangle-shaped or oval-shaped cross-sectional area. [Embodiment 13] 13. The airfoil of any preceding embodiment, wherein the pressure side channel is one of a plurality of pressure side channels, the suction side channel is one of a plurality of suction side channels, and the plurality of suction side channels is radially staggered relative to the plurality of pressure side channels such that each suction side channel radially overlaps with at least one pressure side channel of the plurality of pressure side channels. [Embodiment 14] 13. The airfoil of any preceding embodiment, wherein the airfoil further defines a dead space disposed between the pressure side channel and the suction side channel. [Embodiment 15] 13. The airfoil of any preceding embodiment, wherein an area of ​​one of the pressure side channel or the suction side channel is larger than an area of ​​the other of the pressure side channel or the suction side channel. [Embodiment 16] 1. A turbomachine including a compressor section, a combustion section disposed downstream of the compressor section, and a turbine section disposed downstream of the combustion section, wherein a rotor blade is disposed in one of the combustion section or the turbine section, the rotor blade having a leading edge, a trailing edge, and a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge, wherein a camber axis is defined halfway between the pressure side wall and the suction side wall. and a cooling circuit defined in the airfoil, the cooling circuit having a trailing edge cooling circuit comprising a pressure side channel and a suction side channel, the pressure side channel being positioned in coolable proximity to the pressure side wall and the suction side channel being positioned in coolable proximity to the suction side wall.the pressure side channel disposed in cooling proximity to the pressure side wall and the suction side channel disposed in cooling proximity to the suction side wall. [Embodiment 17] 2. The turbomachine of any preceding embodiment, wherein the pressure side channel is disposed at least partially on a first side of the camber axis and the suction side channel is disposed at least partially on a second side of the camber axis, and the pressure side channel and the suction side channel each converge towards the trailing edge as the pressure side channel and the suction side channel extend towards the trailing edge. [Embodiment 18] 4. The turbomachine of any preceding embodiment, wherein the pressure side channel and the suction side channel are partially defined by a shared wall disposed between the pressure side wall and the suction side wall. [Embodiment 19] 2. The turbomachine of any preceding embodiment, wherein the pressure side channel extends between a pressure side inlet and a pressure side outlet and along a pressure side centerline on a first side of the camber axis, and the suction side channel extends between a suction side inlet and a suction side outlet and along a suction side centerline on a second side of the camber axis. [Embodiment 20] 13. The turbomachine of any preceding embodiment, wherein the pressure side centerline converges towards the camber axis between the pressure side inlet and the pressure side outlet, and the suction side centerline converges towards the camber axis between the suction side inlet and the suction side outlet. [Embodiment 21] 1. An airfoil comprising: a leading edge; a trailing edge; a pressure side wall extending between the leading edge and the trailing edge; and a suction side wall extending between the leading edge and the trailing edge, the pressure side wall and the suction side wall define a main body region and a trailing edge region, the main body region extending from the leading edge to the trailing edge region, the trailing edge region extending from the main body region to the trailing edge, and the main body region defines an upstream plenum extending along a span of the airfoil. The trailing edge region defines a plurality of pressure side channels and a plurality of suction side channels in fluid communication with the upstream plenum and arranged in a trussed structure.a pressure side channel structure, the plurality of pressure side channels is disposed adjacent to the pressure side wall, the plurality of suction side channels is disposed adjacent to the suction side wall, and an airfoil. [Embodiment 22] 13. The airfoil of any preceding embodiment, wherein a camber axis is defined halfway between the pressure side wall and the suction side wall, the plurality of pressure side channels is disposed at least partially on a first side of the camber axis, and the plurality of suction side channels is disposed at least partially on a second side of the camber axis, and the plurality of pressure side channels and the plurality of suction side channels each converge towards the trailing edge as the plurality of pressure side channels and the plurality of suction side channels extend towards the trailing edge. [Embodiment 23] 13. The airfoil of any preceding embodiment, wherein each of the plurality of pressure side channels extends between a pressure side inlet and a pressure side outlet and along a pressure side centerline on a first side of the camber axis, and each of the plurality of suction side channels extends between a suction side inlet and a suction side outlet and along a suction side centerline on a second side of the camber axis. [Embodiment 24] 13. The airfoil of any preceding embodiment, wherein the pressure side centerline converges towards the camber axis between the pressure side inlet and the pressure side outlet, and the suction side centerline converges towards the camber axis between the suction side inlet and the suction side outlet. [Embodiment 25] 13. The airfoil of any preceding embodiment, wherein the plurality of pressure side channels converges in cross-sectional area between the pressure side inlet and the pressure side outlet, and the plurality of suction side channels converges in cross-sectional area between the suction side inlet and the suction side outlet. [Embodiment 26] 13. The airfoil of any preceding embodiment, wherein the trussed structure formed by the plurality of pressure side channels and the plurality of suction side channels is at least partially defined by shared walls of the plurality of pressure side channels and the plurality of suction side channels, the shared walls extend from the pressure side wall to the suction side wall. [Embodiment 27] 13. The airfoil of any preceding embodiment, wherein the plurality of pressure side channels and the plurality of suction side channels are radially spaced apart from one another. [Embodiment 28] 13. The airfoil of any preceding embodiment, wherein each of the plurality of pressure side channels and each of the plurality of suction side channels extend to a downstream plenum, the downstream plenum being defined between outlets of the plurality of pressure side channels and the plurality of suction side channels and the trailing edge. [Embodiment 29] The airfoil of any preceding embodiment, wherein one or more exit channels extends from the downstream plenum to the trailing edge. [Embodiment 30]

[0023] The airfoil of any preceding embodiment, wherein at least one of the plurality of pressure side channels extends to a pressure side exit channel. [Embodiment 31] 13. The airfoil of any preceding embodiment, wherein the pressure side exit channel is a first pressure side exit channel, and at least one of the plurality of suction side channels includes a second pressure side exit channel disposed downstream of the first pressure side exit channel. [Embodiment 32] 13. The airfoil of any preceding embodiment, wherein each of the plurality of pressure side channels and each of the plurality of suction side channels define one of a triangle-shaped or oval-shaped cross-sectional area. [Embodiment 33] 13. The airfoil of any preceding embodiment, wherein the plurality of suction side channels is radially staggered relative to the plurality of pressure side channels such that each suction side channel radially overlaps with at least one pressure side channel of the plurality of pressure side channels. [Embodiment 34] 13. The airfoil of any preceding embodiment, wherein the airfoil further defines a dead space disposed between the plurality of pressure side channels and the plurality of suction side channels. [Embodiment 35] 13. The airfoil of any preceding embodiment, wherein an area of ​​one of the plurality of pressure side channels or the plurality of suction side channels is larger than an area of ​​the other of the plurality of pressure side channels or the plurality of suction side channels. [Embodiment 36] a compressor section, a combustion section disposed downstream of the compressor section, and a turbine section disposed downstream of the combustion section, wherein a rotor blade is disposed in one of the compressor section or the turbine section, the rotor blade including a shank portion and an airfoil extending from the shank portion, the airfoil including a leading edge, a trailing edge, a pressure sidewall extending between the leading edge and the trailing edge, and a suction sidewall extending between the leading edge and the trailing edge, 1. A turbomachine comprising: a turbomachine defining a body region and a trailing edge region, the body region extending from the leading edge to the trailing edge region, the trailing edge region extending from the body region to the trailing edge, the body region defining an upstream plenum extending along a span of the airfoil, the trailing edge region defining a plurality of pressure side channels and a plurality of suction side channels in flow communication with the upstream plenum and disposed in a truss structure, the plurality of pressure side channels being disposed adjacent the pressure sidewall and the plurality of suction side channels being disposed adjacent the suction sidewall. [Embodiment 37] 2. The turbomachine of any preceding embodiment, wherein a camber axis is defined intermediate the pressure side wall and the suction side wall, the plurality of pressure side channels being disposed at least partially on a first side of the camber axis and the plurality of suction side channels being disposed at least partially on a second side of the camber axis, the plurality of pressure side channels and the plurality of suction side channels each converging toward the trailing edge as the plurality of pressure side channels and the plurality of suction side channels extend toward the trailing edge. [Embodiment 38] 2. The turbomachine of any preceding embodiment, wherein each of the plurality of pressure side channels extends along a pressure side centerline on a first side of the camber axis between the pressure side inlet and the pressure side outlet, and each of the plurality of suction side channels extends along a suction side centerline on a second side of the camber axis between the suction side inlet and the suction side outlet. [Embodiment 39] 2. The turbomachine of any preceding embodiment, wherein the pressure side centerline converges towards the camber axis between the pressure side inlet and the pressure side outlet, and the suction side centerline converges towards the camber axis between the suction side inlet and the suction side outlet. [Embodiment 40] 4. The turbomachine of any preceding embodiment, wherein a truss structure formed by the plurality of pressure side channels and the plurality of suction side channels is defined in part by a shared wall of the plurality of pressure side channels and the plurality of suction side channels, the shared wall extending from the pressure side wall to the suction side wall. [Explanation of symbols]

[0072] 10: Gas turbine engine 11: Compressor casing 12: Compressor section 14: Compressor 16: Inlet 18: Combustion section 19: Stator vane 20: Combustor 21: Rotor disk 22: Turbine section 23: Rotor blade 24: Shaft 25: Combustion chamber 26: Stator vane / static nozzle 27: Rotor disk 28: Rotor blade 30: Axial centerline 32: Outer casing 34: Exhaust diffuser 35: Compressed air 37, 1237: Shank 38, 1238: Mounting 40, 1240: Airfoil 41: Combustion gas 42, 1242: Platform 43: Strut / main airfoil 44, 1244: Pressure sidewall 46, 1246: Suction sidewall 48, 1248: Root 50, 1250: Rotor blade 51, 1251: tip 52, 1252: leading edge 54, 1254: trailing edge 56: cooling passage 58: coolant 60: cooling passage inlet 64: coolant outlet 66: tip cavity 68: pressure side tip rail 70: suction side tip rail 72: cooling circuit 74: rib 76: root turn 77: floor 78: tip turn 82, 1282: trailing surface 84, 1284: leading surface 88: leading edge passage 90: intermediate passage 92: trailing edge passage 94, 1294: camber axis 100: trailing edge cooling circuit 101, 1201: body region 102, 1202: trailing edge region 104, 206, 306;Pressure side channel 106, 208, 308: Suction side channel 108: Shared wall 109: Triangular shaped area 110: First shared wall 112: Second shared wall 114: First intersection 116: Second intersection 118, 122: Inlet 120, 124, 134: Outlet 126: Pressure side centerline 128: Suction side centerline 130: Downstream plenum 132: Outlet channel 136: Partition wall 138: Pressure side outlet channel 142: Axial section 144: Lateral section 146: First section 148: Second section 150: First pressure side outlet channel 152: Second pressure side outlet channel 209, 309: Elliptical area 212, 214: Radial row 216, 316: First radial line 218, 318: second radial line 220, 320: major axis 222, 322: minor axis 312: pressure side radial row 314: suction side radial row 324: dead space 326: first partition wall 328: second partition wall 330: common plenum 332: outlet channel 334: open end 336: closed end 1205: upstream plenum A, AC: axial C: circumferential / circumferential R: radial T: transverse;

Claims

1. An airfoil (40, 1240), A leading edge (52, 1252); A trailing edge (54, 1254); a pressure sidewall (44, 1244) extending between a leading edge (52, 1252) and a trailing edge (54, 1254); a suction sidewall (46, 1246) extending between a leading edge (52, 1252) and a trailing edge (54, 1254); the pressure sidewall (44, 1244) and the suction sidewall (46, 1246) define a body region (101, 1201) and a trailing edge region (102, 1202); The body region (101, 1201) extends from the leading edge (52, 1252) to the trailing edge region (102, 1202); a trailing edge region (102, 1202) extending from the body region (101, 1201) to a trailing edge (54, 1254); the body region (101, 1201) defines an upstream plenum (1205) extending along the span of the airfoil (40, 1240); the trailing edge region (102, 1202) is in fluid communication with the upstream plenum (1205) and defines a plurality of pressure side channels (104) and a plurality of suction side channels (106) arranged in a truss structure; a plurality of pressure side channels (104) disposed adjacent the pressure side wall (44, 1244); A plurality of suction side channels (106) are disposed adjacent the suction sidewall (46, 1246) of the airfoil (40, 1240).

2. a camber axis (94, 1294) is defined intermediate the pressure sidewall (44, 1244) and the suction sidewall (46, 1246); the plurality of pressure side channels (104) are disposed at least partially on a first side of the camber axis (94, 1294); a plurality of suction side channels (106) disposed at least partially on a second side of the camber axis (94, 1294); 2. The airfoil of claim 1, wherein the plurality of pressure side channels and the plurality of suction side channels converge toward the trailing edge as the plurality of pressure side channels and the plurality of suction side channels extend toward the trailing edge.

3. Each of the plurality of pressure side channels (104) extends along a pressure side centerline (126) on a first side of the camber axis (94, 1294) between a pressure side inlet (118) and a pressure side outlet (120); 3. The airfoil of claim 2, wherein each of the plurality of suction side channels extends along a suction side centerline on a second side of the camber axis between a suction side inlet and a suction side outlet.

4. 4. The airfoil (40) of claim 3, wherein the pressure side centerline (126) converges toward the camber axis (94, 1294) between the pressure side inlet (118) and the pressure side outlet (120) and the suction side centerline (128) converges toward the camber axis (94, 1294) between the suction side inlet (122) and the suction side outlet (124).

5. 5. The airfoil (40) of claim 4, wherein the plurality of pressure side channels (104) converge in cross-sectional area between the pressure side inlet (118) and the pressure side outlet (120), and the plurality of suction side channels (106) converge in cross-sectional area between the suction side inlet (122) and the suction side outlet (124).

6. 2. The airfoil (40) of claim 1, wherein a truss structure formed by the plurality of pressure side channels (104) and the plurality of suction side channels (106) is defined at least in part by a common wall (108) of the plurality of pressure side channels (104) and the plurality of suction side channels (106), the common wall (108) extending from the pressure side wall (44) to the suction side wall (46).

7. 2. The airfoil of claim 1, wherein each of the plurality of pressure side channels and the plurality of suction side channels extend to a downstream plenum, the downstream plenum being defined between outlets of the plurality of pressure side channels and the plurality of suction side channels and the trailing edge.

8. The airfoil (40) of claim 7, wherein the one or more outlet channels (132) extend from the downstream plenum (130) to the trailing edge (54,1254).

9. The airfoil (40) of claim 1, wherein at least one of the plurality of pressure side channels (104) extends to a pressure side outlet channel (150).

10. 10. The airfoil (40) of claim 9, wherein the pressure side outlet channel (150) is a first pressure side outlet channel, and at least one of the plurality of suction side channels (106) includes a second pressure side outlet channel (152) disposed downstream of the first pressure side outlet channel (150).

11. The airfoil (40) of claim 1, wherein each of the plurality of pressure side channels (104) and each of the plurality of suction side channels (106) define one of a triangular or an elliptical shaped cross-sectional area (109, 209).

12. 2. The airfoil (40) of claim 1, wherein the plurality of suction side channels (106) are radially offset relative to the plurality of pressure side channels (104) such that each suction side channel (106) radially overlaps at least one of the plurality of pressure side channels (104).

13. The airfoil (40) of claim 1, further defining a dead space (324) disposed between the plurality of pressure side channels (104) and the plurality of suction side channels (106).

14. 2. The airfoil (40) of claim 1, wherein an area of ​​one of the plurality of pressure side channels (104) or the plurality of suction side channels (106) is greater than an area of ​​the other of the plurality of pressure side channels (104) or the plurality of suction side channels (106).

15. A turbomachine (10), comprising: A compressor section (12); a combustion section (18) disposed downstream of the compressor section (12); a turbine section (22) disposed downstream of the combustion section (18); Including, A rotor blade (50) is disposed in one of the compressor section (12) or the turbine section (22); The rotor blade (50) includes a shank portion (37) and an airfoil (40) extending from the shank portion (37); A turbomachine (10) wherein the airfoil (40) is defined according to any of claims 1 to 14.

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