Component with cooling channels for a turbine engine

Abstract

An engine component for a turbine engine having a working airflow that is separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface through which the combustion airflow flows, the outer surface defining a first side and a second side. The engine component further comprises at least one cooling conduit disposed in the interior and having a conduit sidewall, and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one cooling passage of the set of cooling passages comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot is located in the primary cooling passage portion, and a impingement zone is fluidly coupled to the diffusion slot.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority to U.S. Patent Application No. 17 / 520,146, filed November 5, 2021, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This disclosure generally relates to cooling channels for engines, and more specifically, to a set of cooling channels for cooling the upstream edge of an airfoil. Background Technology

[0004] A turbine engine, especially a gas or combustion turbine engine, is a rotating engine that extracts energy from a stream of combustible gas that passes through the engine and flows over multiple airfoils, including stationary impeller blades and rotating turbine blades.

[0005] Gas turbine engines used in aircraft are designed to operate at high temperatures to maximize engine efficiency, so cooling certain engine components, such as the high-pressure turbine and the low-pressure turbine, can be beneficial. Typically, cooling is accomplished by piped cooler air from the high-pressure and / or low-pressure compressors to the engine components that need cooling. The temperature in the high-pressure turbine is approximately 1000°C to 2000°C, and the cooling air from the compressor is approximately 500°C to 700°C. Although the compressor air is hot, it is cooler than the turbine air and can be used to cool the turbine.

[0006] Modern turbine blades and other engine components generally include one or more internal cooling circuits for directing cooling air through the engine component to cool different parts of the engine component, and may include dedicated cooling circuits for cooling different parts of the engine component. Attached Figure Description

[0007] In the specification with reference to the accompanying drawings, a complete and feasible disclosure, including its best mode, is set forth for those skilled in the art, wherein:

[0008] Figure 1 This is a schematic cross-sectional view of a gas turbine engine used in aircraft.

[0009] Figure 2 It is in the form of blades that include a set of cooling channels. Figure 1 A perspective view of the airfoil component of the engine.

[0010] Figure 3 It is along Figure 2 A cross-sectional view of an airfoil with a set of cooling channels, taken from line III-III.

[0011] Figure 4 This is an enlarged view of a variation of a cooling channel from a set of cooling channels, based on one aspect disclosed in this article.

[0012] Figure 5 It is along Figure 4 The line VV intercepted from Figure 4 A cross-sectional view of the cooling channel.

[0013] Figure 6 This is a perspective view of a portion of the airfoil shown in dashed lines, with a set of cooling channels shown in solid lines.

[0014] Figure 7 This is a front view of the upstream edge of a modified airfoil with a set of cooling channels, according to one aspect disclosed herein.

[0015] Figure 8 It is along Figure 7 The cross-sectional view taken by line VIII-VIII shows the various geometries of the stagnant cooling channels for a set of cooling channels.

[0016] Figure 9A It is based on one aspect disclosed in this article. Figure 7 The cross-sectional view taken by line IX-IX shows the stagnant cooling channel.

[0017] Figure 9B This is based on another aspect disclosed in this article. Figure 7 The cross-sectional view taken by line IX-IX shows a variation of the stagnant cooling channel.

[0018] Figure 10 This is an enlarged view of a variation of the arrangement of a set of cooling channels as disclosed in this article.

[0019] Figure 11 This is an enlarged view of another variation of the arrangement of a set of cooling channels according to another aspect disclosed in this article.

[0020] Figure 12 This is an enlarged view of yet another variation of the arrangement of a set of cooling channels as disclosed in this article.

[0021] Figure 13 This is an enlarged view of yet another variation of the arrangement of a set of cooling channels as disclosed in this article.

[0022] Figure 14 This is a top view of any cooling channel with a set of flow enhancers, as shown in this article.

[0023] Figure 15 yes Figure 14 A cross-sectional view along line XV-XV, where the flow enhancer is a pin. Detailed Implementation

[0024] The aspects of this disclosure described herein relate to cooling holes disposed in engine components. More specifically, this disclosure relates to one or more cooling holes disposed in airfoils adjacent to the edges of engine components. For illustrative purposes, this disclosure will be described with respect to the upstream edge of a turbine blade for an aircraft gas turbine engine. However, it will be understood that the aspects of this disclosure described herein are not limited thereto and can have general applicability in engines including compressors as well as in non-aircraft applications such as other mobile applications and non-mobile industrial, commercial, and residential applications. Dedicated cooling circuits utilizing the cooling holes described herein can be implemented in airfoil components, including but not limited to the leading edge, trailing edge, or tip of the airfoil. Other contemplated engine components include, but are not limited to, platform edges, endwalls, etc.

[0025] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "front" or "in front" mean in front of something, and "back" or "behind" means behind something. For example, when used in relation to fluid flow, "front" / "in front" can mean upstream, and "back" / "behind" can mean downstream.

[0026] Additionally, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction of a ray extending between the engine's central longitudinal axis and the engine's outer perimeter. Furthermore, as used herein, the term "group" or a "set" of elements can be any number of elements, including only one.

[0027] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are for illustrative purposes only to aid the reader in understanding this disclosure and should not be construed as limiting the embodiments, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connection references (e.g., attachment, coupling, connection, and joining) are to be interpreted broadly and may include intermediate elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, connection references do not necessarily imply that two elements are directly connected and in a fixed relationship with each other. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the accompanying drawings may vary. As used herein, they are essentially meant to be within 5%.

[0028] Figure 1This is a schematic cross-sectional view of a gas turbine engine 10 for an aircraft. The engine 10 has a generally longitudinally extending axis or engine centerline 12 extending from the front 14 to the rear 16. The engine 10 includes the following downstream sequential flow relationships: a fan section 18 including a fan 20; a compressor section 22 including a supercharger or low-pressure (LP) compressor 24 and a high-pressure (HP) compressor 26; a combustion section 28 including a combustor 30; a turbine section 32 including an HP turbine 34 and an LP turbine 36; and an exhaust section 38.

[0029] Fan section 18 includes a fan housing 40 surrounding fan 20. Fan 20 includes a plurality of fan blades 42 arranged radially around engine centerline 12. HP compressor 26, combustor 30 and HP turbine 34 form core 44 of engine 10, which generates combustion gases. Core 44 is surrounded by core housing 46, which can be coupled to fan housing 40.

[0030] An HP shaft or spool 48, coaxially arranged around the engine centerline 12 of the engine 10, drives the HP turbine 34 to the HP compressor 26. An LP shaft or spool 50, coaxially arranged within a larger diameter annular HP spool 48 around the engine centerline 12 of the engine 10, drives the LP turbine 36 to the LP compressor 24 and the fan 20. The HP spool 48 and LP spool 50 are rotatable around the first engine centerline and are connected to multiple rotatable elements that collectively define the rotor 51.

[0031] LP compressor 24 and HP compressor 26 each include multiple compressor stages 52 and 54, respectively, in which a set of compressor blades 56 and 58 rotate relative to a corresponding set of static compressor blades 60 and 62 to compress or pressurize the fluid flow passing through the stage. In a single compressor stage 52 or 54, the multiple compressor blades 56 and 58 can be arranged in a ring and can extend radially outward from the blade platform relative to the engine centerline 12 to the blade tips, while the corresponding static compressor blades 60 and 62 are positioned upstream of and adjacent to the rotating compressor blades 56 and 58. It is worth noting that... Figure 1 The number of blades, impellers, and compressor stages shown is selected only for illustrative purposes, and other numbers are also possible.

[0032] Rotary compressor blades 56, 58 for the first stage of the compressor can be mounted to (or integrated into) a disc 61, which is mounted to a corresponding one of the HP spool 48 and the LP spool 50. Static compressor blades 60, 62 for the first stage of the compressor can be mounted to the core housing 46 in a circumferential arrangement.

[0033] HP turbine 34 and LP turbine 36 each comprise multiple turbine stages 64 and 66, respectively, in which a set of turbine blades 68 and 70 rotate relative to a corresponding set of static turbine blades 72 and 74 (also referred to as nozzles) to extract energy from the fluid flow passing through the stage. In a single turbine stage 64 and 66, multiple rotating turbine blades 68 and 70 can be arranged in a ring and can extend radially outward relative to the engine centerline 12, while the corresponding static turbine blades 72 and 74 are positioned upstream of and adjacent to the rotating turbine blades 68 and 70. It is worth noting that... Figure 1 The number of blades, impellers, and turbine stages shown is selected only for illustrative purposes, and other numbers are also possible.

[0034] Rotary turbine blades 68 and 70 for the first stage of the turbine can be mounted to a turbine rotor disk 71, which is mounted to a corresponding one of the HP spool 48 and LP spool 50. Static turbine blades 72 and 74 for the first stage of the compressor can be mounted to the core housing 46 in a circumferential arrangement.

[0035] In addition to the rotor section, the stationary parts of the engine 10, such as the static blades 60, 62, 72, and 74 in the compressor section 22 and the turbine section 32, are also individually or collectively referred to as the stator 63. Therefore, the stator 63 can refer to the combination of the non-rotating elements of the entire engine 10.

[0036] In operation, the airflow leaving fan section 18 is split, with a portion directed to LP compressor 24. LP compressor 24 then supplies pressurized airflow 76 to HP compressor 26, which further pressurizes the air. The pressurized airflow 76 from HP compressor 26 mixes with fuel in combustor 30 and is ignited, generating combustion gases. HP turbine 34 extracts some work from these gases to drive HP compressor 26. The combustion gases are discharged to LP turbine 36, which extracts additional work to drive LP compressor 24, and the exhaust gases are finally discharged from engine 10 via exhaust section 38. The drive of LP turbine 36 drives LP spool 50 to rotate fan 20 and LP compressor 24.

[0037] A portion of the pressurized gas flow 76 can be drawn from the compressor section 22 as bleed air 77. Bleed air 77 can be drawn from the pressurized gas flow 76 and supplied to engine components requiring cooling. The temperature of the pressurized gas flow 76 entering the combustor 30 is significantly increased to above the bleed air temperature. Bleed air 77 can be used to reduce the temperature of core components downstream of the combustor.

[0038] The remaining airflow 78 bypasses the LP compressor 24 and engine core 44, and exits the engine 10 at the fan exhaust side 84 via a stationary blade row, and more specifically, via an outlet guide vane assembly 80 comprising multiple airfoil guide vanes 82. More specifically, a circumferential row of radially extending airfoil guide vanes 82 is used near the fan section 18 to exert some directional control on the airflow 78.

[0039] Some of the air supplied by fan 20 can bypass engine core 44 and be used to cool parts of engine 10, particularly the hot parts of engine 10, and / or to cool other aspects of the aircraft or to power other aspects of the aircraft. In the context of a turbofan engine, the hot parts of the engine are typically downstream of combustor 30, particularly turbine section 32, with HP turbine 34 being the hottest part as it is directly downstream of combustion section 28. Other sources of cooling fluid may be, but are not limited to, fluid discharged from LP compressor 24 or HP compressor 26.

[0040] Now for reference Figure 2 This shows the location from Figure 1 The turbine blade 68 is an engine component in the form of an engine 10. Alternatively, in a non-limiting example, the engine component may be a wheel blade, strut, service pipe, shroud, or combustion liner, or any other engine component that may require or use a cooling passage. The turbine blade 68 includes a dovetail 90 and an airfoil 92. The dovetail 90 further includes at least one inlet passage 100, shown as three exemplary inlet passages 100, each extending through the dovetail 90 to provide internal fluid communication with the airfoil 92 at a supply outlet 102. It should be understood that the dovetail 90 is shown in cross-section such that the inlet passages 100 are accommodated within the body of the dovetail 90. For example, the dovetail 90 may be configured to be mounted to... Figure 1 The turbine rotor disk 71 on the engine 10.

[0041] Airfoil 92 extends radially between tip 94 and root 96, defining a spanwise direction therebetween. Airfoil 92 is mounted at root 96 to a dovetail 90 at platform 98. Platform 98 facilitates radial containment of the turbine engine's mainstream airflow. Additionally, airfoil 92 includes an outer wall 104 comprising a first side 106 and a second side 108, extending between an upstream edge 110 and a downstream edge 112 to define a streamline direction therebetween. It should be understood that the upstream edge 110 may be the leading edge of airfoil 92, and the downstream edge 112 may be the trailing edge of airfoil 92. Further, as shown, the first side 106 may be the pressure side of the rotating blade, and the second side 108 may be the suction side of the rotating blade. It is also further contemplated that airfoil 92 may be a non-steering blade, such as a frame fairing as a non-limiting example. It is also further contemplated that neither the first side 106 nor the second side 108 is curved to form the pressure side and / or suction side.

[0042] In operation, a hot gas flow (Hot), such as a burner flow, may pass along the exterior of the outer wall 104 of the airfoil 92. A cooling fluid flow (C) may be supplied to the inlet passage 100 and enter the airfoil 92 at the supply outlet 102. A stagnation line (SL) is located where the hot gas flow (Hot) contacts the airfoil 92 at a 90-degree angle and the velocity of the hot gas flow (Hot) is zero. The edge of the airfoil 92 may be defined by a variation of angles equal to 15 degrees, 135 degrees, or between 15 and 135 degrees across a 0.5-inch arc length. The edge may be a sharp angle variation, such as a machined edge of an engine component, where, as a non-limiting example, the tip 94 intersects with the first side 106 or the second side 108, or, as in the case of the upstream edge 110 in the airfoil 92, a rounded or mixed edge. In other non-limiting examples, the edge may be the downstream edge 112, the front, side, or rear end of the platform 98, the root 96, or other areas of the engine component where the angle changes along the arc length. In some embodiments, the angle change may be equal to 45 degrees, 135 degrees, or between 45 and 135 degrees. In some cases, the stagnation line (SL) is collinear with the upstream edge 110; however, it should be understood that the stagnation line (SL) may vary to some extent along the upstream edge 110. Furthermore, the stagnation line (SL) may vary temporarily or permanently from all or part of the upstream edge 110 during all or part of the operating conditions. In some embodiments, there is no stagnation line (SL) at all.

[0043] A set of cooling channels 114 may discharge adjacent to the upstream edge 110. The set of cooling channels 114 may include various cooling channels and their orientations. A cooling fluid flow (C) may be provided throughout the airfoil 92 and discharged as a cooling film from the set of cooling channels 114. At least one of the cooling channels 114 may be a stagnant cooling channel 116. Depending on the implementation, the stagnant cooling channel 116 may be positioned along a stagnation line (SL) or the upstream edge 110. For the airfoil 92 as described herein, the stagnant cooling channel 116 is positioned along the stagnation line (SL). An outlet slot 118 may be provided at or near the upstream edge 110. The outlet slot 118 may be located on the side of the stagnant cooling channel 116, such that another outlet slot may be provided on the other side of the stagnant cooling channel 116, but... Figure 2 Perspective masking.

[0044] At least one of the cooling channels 114 may be a tank cooling channel 120. The tank cooling channel 120 may extend to the outer wall along the stagnation line (SL) or adjacent to the upstream edge 110. Further, the tank cooling channel 120 may be oriented in a streamlined or spanwise direction. It is further contemplated that the tank cooling channel 120 is located to the side of the stagnation line (SL). The tank cooling channel 120 may also discharge into an outlet tank 118 or directly onto the outer wall at the channel outlet 150.

[0045] A set of cooling channels 114 may include any one or any combination of stagnant cooling channels 116, outlet channels 118, or channel cooling channels 120. Further, the set of cooling channels 114 may be arranged in a spanwise row. Optionally, another set of cooling channels may be provided on the second side 108, but... Figure 2 Perspective masking.

[0046] Now for reference Figure 3 , showed Figure 2Section III-III, with an outer wall 104 defining an interior 122. The outer wall 104 may have a thickness extending between an inner surface 124 and an outer surface 126, the inner surface 124 defining the interior 122. At least one rib 128 may extend from a first side 106 of the outer wall 104 to a second side 108 of the outer wall 104, effectively separating the interior 122 into separate cooling conduits 130. The cooling conduits 130 may form at least a portion of a cooling circuit 132 within the interior 122 of the airfoil 92 and are supplied by a supply outlet 102. It should be understood that the at least one rib 128, cooling conduit 130, and cooling circuit 132 shown are exemplary, and numerous different cooling circuits 132 may be formed within the airfoil 92, including but not limited to cooling conduits, grooves, channels, pipes, cooling inlets, full-length or partial-length ribs in the spanwise or streamlined plane, near-wall cooling channels, turbulence generators, pins, fins, or one or more of any other structures forming the airfoil 92.

[0047] An exhaust port 134 may be provided in the outer wall 104 at the downstream edge 112. The exhaust port 134 can fluidly connect the cooling circuit 132 to the downstream edge 112, and more specifically, fluidly connect the aftercooling conduit 130 to the downstream edge 112 for discharging cooling fluid at the downstream edge 112.

[0048] A set of cooling channels 114 can fluidly connect the interior 122 to the exterior of the airfoil 92 at the outer surface 126, and provide cooling fluid in the cooling fluid flow (C) near any part of the airfoil 92 that needs to be cooled. A set of cooling channels 114 may be formed in the outer wall 104, and as a non-limiting example, at least one cooling conduit 130 is fluidly connected to the outer surface 126 near the upstream edge 110 as shown.

[0049] At least one of the cooling channels 114 may include a primary cooling channel portion 140 and a secondary cooling channel portion 142. The primary cooling channel portion 140 may discharge into an outlet trough 118. As shown, either or both of the primary cooling channel portion 140 and the secondary cooling channel portion 142 may be bent. The cooling channel set 114 may include a first side group of cooling channels 144 discharging onto a first side 106 and a second side group of cooling channels 146 discharging onto a second side 108. The first side group of cooling channels 144 and the second side group of cooling channels 146 may be located on the sides of the upstream edge 110. The cooling channel set 114 may include a stagnant cooling channel 116 that connects the internal 122 fluid to the upstream edge 110 at a stagnation line (SL). The first side group of cooling channels 144 and the second side group of cooling channels 146 may be located on the sides of the stagnant cooling channel 116.

[0050] Figure 4 This is an enlarged view of the cooling passage of the second side cooling passage 144 (as a non-limiting example, the slot cooling passage 120). The slot cooling passage 120 can discharge into the outlet slot 118. The primary cooling passage portion 140 can have a passage outlet 150 leading to the outer surface 126. The secondary cooling passage portion 142 can intersect with the primary cooling passage portion 140 at a junction 152. The secondary cooling passage portion 142 can have an inlet 154 fluidly connected to the cooling duct 130, and an intermediate outlet 156 at the junction 152 fluidly connecting the secondary cooling passage portion 142 to the primary cooling passage portion 140.

[0051] The cooling channel 120 may extend between the inlet 154 and the channel outlet 150 to define a flow direction (F), shown in dashed lines, between the cooling conduit 130 and the outer surface 126. The primary cooling channel portion 140 may include a diffusion channel 160 having a channel sidewall 162 extending along a first centerline (CL1) in the flow direction (F) between the rear wall 164 and the channel outlet 150. An intermediate outlet 156 may be positioned adjacent to the rear wall 164, or, as shown, spaced apart from the rear wall 164, to define a bag portion 166.

[0052] The secondary cooling channel portion 142 may define a metering section 170 with a circular cross-section, although it may have any cross-sectional shape. The metering section 170 may have a cross-sectional area that is the minimum or smallest cross-sectional area of ​​the tank cooling channel 120. The metering section 170 may extend along a second centerline (CL2) from the inlet 154 to the intermediate outlet 156. It is further anticipated that the cross-sectional area be maintained as a constant cross-sectional area from the inlet 154 to the intermediate outlet 156. Maintaining a constant cross-sectional area enables controlled flow of the cooling fluid (C) as it enters the diffuser 160.

[0053] It is also anticipated that the metering section 170 has no length and is located at any point within the smallest cross-sectional area of ​​the tank cooling channel 120. Further, it is anticipated that the inlet 154 may define the metering section 170 without extending into the tank cooling channel 120 at all. The tank cooling channel 120 may include multiple metering sections, and is not limited to the one shown in the figure. The metering section 170 is used to meter the mass flow rate of the cooling fluid flow (C).

[0054] The impact zone 158 can be formed at the junction 152 by the intersection of the primary cooling channel portion 140 and the secondary cooling channel portion 142. The primary cooling channel portion 140 can define an impact surface 168 facing the intermediate outlet 156 of the secondary cooling channel portion 142. The impact zone 158 can include the intermediate outlet 156 and the impact surface 168, at which the cooling fluid (C) leaving the intermediate outlet 156 from the secondary cooling channel portion 142 impacts or impinges.

[0055] One or both of the primary cooling channel section 140 and the secondary cooling channel section 142 may be bent, in Figure 4 The figure shows that both are bent. Additionally, the primary cooling channel portion 140 and the secondary cooling channel portion 142 can be bent in opposite directions as shown, or they can be bent in the same direction. Either or both of the primary cooling channel portion 140 and the secondary cooling channel portion 142 can be bent to include a bend 172; as a non-limiting example, the secondary cooling channel portion 142 is bent. The slot cooling channel 120 can include multiple turning portions; as a non-limiting example, multiple turning portions are included at the joint 152 and the bend 172, causing a change in the direction of flow (F). The joint 152 can be defined by the intersection of a first centerline (CL1) and a second centerline (CL2), the intersection of which can form a 90-degree angle, while angles equal to 0 degrees, 180 degrees, or any angle between 0 degrees and 180 degrees are contemplated.

[0056] Now for reference Figure 5 , showing the passage Figure 4 The cross-sectional view of section VV extending in the spanwise direction. The shape of the diffuser 160 can be better understood as having multiple channel outlets 150 discharging into the outlet channel 118. The diffuser 160 may have a rounded rectangular cross-sectional shape defined along a curved plane. Additionally, other shapes are contemplated such that fluid discharged from the intermediate outlet 156 can diffuse within the diffuser 160. Non-limiting examples of additional shapes defined in the plane along the diffuser 160 may include rounded square shapes, triangular shapes, truncated triangular shapes, rounded triangular shapes, circular or semi-circular shapes, oval or semi-oval shapes, and any suitable geometric, linear, curved, or variable shape, or any combination thereof.

[0057] Each channel outlet 150, schematically shown in dashed lines, may be defined upstream of the outer surface 126 of the outer wall 104 and may be further defined by a set of structures 174 between adjacent channel outlets 150 of adjacent diffuser channels 160. The set of structures 174 may be formed as part of the outer wall 104 defining the cooling channels 120 of adjacent channels. This provides discharge to a common outlet channel 118 before positioning the channel outlets 150 on the outer surface 126. Further, it is contemplated that the diffuser channels 160 may intersect along their sides, having a smaller or eliminated set of structures 174. Further, the channel outlets 150 may be directly disposed on the outer surface 126 and may define an outlet channel 118 or have no outlet channel 118.

[0058] The intermediate outlet 156 may have a circular cross-sectional shape of a curved cylindrical conduit extending along and defining the secondary cooling channel portion 142. In a non-limiting example, additional cross-sectional shapes, such as square, circular, oval, or racetrack-shaped cross-sectional shapes, are generally contemplated for the secondary cooling channel portion 142 and the metering section.

[0059] Now for reference Figure 6 The image shows a perspective view of a portion of the upstream edge 110 of the airfoil 92 in an inverted manner, featuring a hollow outer wall 104 shown in dashed lines and a set of cooling channels 114 shown in solid lines for better understanding of the geometry. It should be understood that the finished product will include a solid outer wall 104 and a hollow set of cooling channels 114. Figure 6 The inverted arrangement is shown only to understand the three-dimensional geometry of a set of cooling channels 114 extending through the outer wall 104.

[0060] A set of cooling channels 114 includes at least one (four shown) stagnant cooling channels 116. Each stagnant cooling channel 116 extends between a stagnant inlet 176 and a stagnant outlet 178, the stagnant inlet 176 being fluidly connected to a cooling duct 130 and the stagnant outlet 178 being fluidly connected to the exterior of the airfoil 92 at the outer surface 126. Although the stagnant cooling channels 116 are shown as linear cooling holes, it is contemplated that the stagnant cooling channels 116 may have different geometries, such as being curved in the spanwise direction. It should be understood that although illustrated as oriented along a stagnant line (SL), the stagnant cooling channels 116 may be formed along the edge of the engine component, forming, as a non-limiting example, along the upstream edge 110 described herein.

[0061] The secondary cooling channel portion 142 may terminate at an intermediate outlet 156, which intersects with the diffuser groove 160 at a junction 152. The junction 152 may be a common junction shared by adjacent diffuser grooves 160. Discrete diffuser grooves 160 and junctions 152 are also contemplated. The diffuser groove 160 may include a curved planar geometry that is wider in the spanwise direction than the geometry of the secondary cooling channel portion 142. The curved planar geometry refers to a substantially constant height (H) measured in the streamline direction, while having a width (W) that gradually widens in the chordal plane near the outer surface 126. The curved geometry helps to lay a cooling film along the outer surface 126 of the airfoil 92, which provides improved film adhesion and effectiveness.

[0062] Now for reference Figure 7 The image shows a front view of the upstream edge 110 of the airfoil 92, wherein a set of cooling channels 114 includes stagnant cooling channels 116 with a shape similar to the slot cooling channels 120 described herein. Stagnant cooling channels 116 may include diffuser slots 160 having rectangular channel outlets 150. Figure 6 Although illustrated as a rectangle, it should be understood that the channel outlet 150 can be embodied in any shape extending in a direction substantially orthogonal to the stagnation line (SL). Although shown as discharging the channel outlet 150 into the outlet trough 118, it should be understood that the channel outlet 150 can be disposed directly along the outer wall 104 and does not need to include the outlet trough 118, see [reference needed]. Figure 2 Furthermore, although the illustration shows a first side cooling channel 144 and a second side cooling channel 146, it should be understood that a cooling channel 114 may include only the stagnant cooling channel 116.

[0063] Figure 8 It is along Figure 7 The cross-sectional view is taken from line VIII-VIII. A set of cooling channels 114 may include various geometries for stagnant cooling channels 116 within the outer wall 104. Stagnant cooling channels 116 may be arranged radially or along the stagnation line (SL) in the spanwise direction to help reduce or eliminate stagnation zones along the upstream edge 110. The illustrated stagnant cooling channels 116 may each include a primary cooling channel portion 140 and a secondary cooling channel portion 142 as described herein.

[0064] The first stagnant cooling channel 116a may include a linear primary cooling channel portion 140a and a first curved secondary cooling channel portion 142b. The linear primary cooling channel portion 140a may extend substantially toward the root 96 (bottom of the page). The first curved secondary cooling channel portion 142b may be curved in a direction substantially parallel to the stagnant line (SL). For example, it opens upward toward the tip 94 (top of the page), as shown.

[0065] The second stagnant cooling channel 116b may include a first curved primary cooling channel portion 140b and a first curved secondary cooling channel portion 142b. The curvatures of both the first curved primary cooling channel portion 140b and the first curved secondary cooling channel portion 142b may be the same as shown, with both curvatures opening upwards toward the tip 94. Further contemplated is that the curvatures are opposite, with one curvature opening upwards toward the tip 94 and the other curvature opening downwards toward the root 96.

[0066] The third stagnant cooling channel 116c may include a first curved primary cooling channel portion 140b and a linear secondary cooling channel portion 142a.

[0067] The fourth stagnant cooling channel 116d may include a linear primary cooling channel portion 140a extending substantially toward the tip 94. A second curved secondary cooling channel portion 142c may have substantially orthogonal curvature. The second curved secondary cooling channel portion 142c may fluidly connect the linear primary cooling channel portion 140a to the interior 122. "Substantially orthogonal" means changing from the first direction 180 to the second direction 182 within 5% of each other's perpendicularity. As a non-limiting example, the first direction 180 may face the outer surface 126, and more specifically, along the streamline direction toward the upstream edge 110. As a non-limiting example, the second direction 182 may face the tip 94 in the spanwise direction.

[0068] Primary cooling channel portions 140a and 140b may include diffusion channels 160 as described herein. Further, primary cooling channel portions 140a and 140b may include impact zones 158 as described herein. Secondary cooling channel portions 142a, 142b, and 142c may include metering sections 170 as described herein. Primary cooling channel portions 140a and 140b may extend at an angle from secondary cooling channel portions 142a and 142b in the spanwise direction.

[0069] It is further anticipated that the primary cooling channel portions 140a and 140b can bend into or out of the page. Similarly, it is anticipated that the secondary cooling channel portions 142a and 142b can bend into or out of the page, opposite to the spanwise direction. Therefore, it should be understood that the primary and secondary cooling channel portions 140, 140a, 140b, 142, 142a, and 142b as described herein can bend in any direction, such as in the chord direction, spanwise direction, or any combination thereof, and in the axial, radial, or circumferential direction relative to the engine carrying the airfoil or engine components.

[0070] Figure 9A It is simply labeled as 116. Figure 8 Along any stagnant cooling channels 116a, 116b, 116c, 116d Figure 7 The cross-sectional view along line IX-IX shows that the diffuser 160 extends in a third direction 183, which is substantially orthogonal to the first direction 180 and the second direction 182 as described herein. As shown, the third direction 183 can be generally oriented towards / away from the first side 106 and the second side 108. The intermediate outlet 156 can be defined by a diameter (D). Although illustrated as circular, it should be understood that if the intermediate outlet 156 has a non-circular cross-section, the diameter (D) is the hydraulic diameter of the non-circular shape.

[0071] Figure 9B It is based on the orientation variation of the fifth stagnant cooling channel 116e disclosed in this article. Figure 7 The cross-sectional view is shown along line IX-IX. The primary cooling channel portion 140 may include a diffusion groove 160 extending in a third direction 183, which is substantially orthogonal to the stagnation line (SL). The secondary cooling channel portion 142 may be a third curved secondary cooling channel portion 142d similar to the second curved secondary cooling channel portion 142c previously described herein. The third curved secondary cooling channel portion 142d may be curved from a first direction 180 to a third direction 183, which is substantially orthogonal to the first direction 180. In other words, the third curved secondary cooling channel portion 142d may be curved away from the second side 108 and toward the first side 106. It should be understood that the third curved secondary cooling channel portion 142d may also be formed as a dashed line, as shown, curving away from the first side 106 and toward the second side 108.

[0072] refer to Figure 2-9BIt should be understood that the set of cooling channels 114 described herein, with a primary cooling channel portion 140 having a diffuser groove 160 and a secondary cooling channel portion having a metering section 170, can improve the dispersion of cooling fluid, which provides an overall improved cooling film on the outer surface 126 of the airfoil 92. Additionally, the curvature of both the first curved primary cooling channel portion 140b and the first curved secondary cooling channel portion 142b provides an increased length compared to any of the cooling channels 116, 120 described herein. This can provide improved cooling film effectiveness. Furthermore, the curved secondary cooling channel portion 142 provides orthogonal impact on the impact surface 168 of the cooling fluid entering the diffuser groove 160, which improves localized cooling of the airfoil 92 or engine components. Alternatively, non-orthogonal impact is contemplated and can be used where advantageous or where the arrangement requires non-orthogonal impact. Similarly, the curved primary cooling channel portion 140 provides the discharge of cooling fluid that is more complementary to the outer surface 126 of the outer wall 104, which provides improved film adhesion on the airfoil 92. Furthermore, compared to the conventional "nozzle" leading edge construction requiring multiple rows of individual orifices, the elongated diffuser 160 can provide a wider cooling film dispersion, which can cover a larger area of ​​the airfoil 92 with the cooling film, requiring fewer overall cooling channels. Even further, compared to using an outlet with a smaller shape (such as...) Figure 6 Compared to the stagnant outlet 178, the channel outlet 150 can provide a wider cooling film coverage. Therefore, the set of cooling channels 114 described herein can improve film cooling of the airfoil 92 or engine components, providing a reduced required volume of cooling fluid, which can improve overall engine efficiency and fuel consumption. Furthermore, the improved cooling film efficiency can provide higher operating temperatures, which can further improve engine efficiency.

[0073] Now for reference Figure 10 This illustrates another arrangement of a first set of cooling channels 114a, similar to the set of cooling channels 114 described herein. The first set of cooling channels 114a may include a first side group of cooling channels 144 discharging onto a first side 106 and a second side group of cooling channels 146 discharging onto a second side 108. The first side group of cooling channels 144 and the second side group of cooling channels 146 may be located on the sides of the upstream edge 110 or the stagnation line (SL). The first side group of cooling channels 144 and the second side group of cooling channels 146 may each include a first pair of slot cooling channels 186 located on the sides of the stagnation cooling channels 116.

[0074] Each slot cooling channel 120 in the first pair of slot cooling channels 186 may include a primary cooling channel portion 140 and a secondary cooling channel portion 142 as described herein. The primary cooling channel portion 140 may be a second curved primary cooling channel portion 140c having a curvature depending on which of the first pair of slot cooling channels 186 of the first side group cooling channels 144 and the second side group cooling channels 146 is away from the stagnant cooling channel 116 and faces either the first side 106 or the second side 108. The primary cooling channel portion 140 may discharge onto the outer surface 126 at a channel outlet 150. The channel outlet 150 may be spaced from the upstream edge 110 by up to 100 diameters (D) measured along the outer surface 126. Further contemplated, the channel outlets 150 for a set of cooling channels 114a are arranged at a distance from the upstream edge 110 equal to 75, 100, or between 75 and 100 diameters (D). In other embodiments, this arrangement may be equal to 0, 75, 100, or between 0 and 75 or 0 and 100 diameters (D). This spacing between the channel outlet 150 and the upstream edge 110 can be implemented for any set of cooling channels 114 described herein. Further, the spacing, expressed in terms of proximity, can be defined as "proximity" as used herein, meaning within 0 and 100 diameters (D).

[0075] Secondary cooling channel portion 142 may be a third curved secondary cooling channel portion 142d as previously described herein, and opens toward the stagnant cooling channel 116 as shown. It is contemplated that, as shown, the curvature directions of the first cooling channel portion 140 and the second cooling channel portion 142 are opposite to each other. Although shown as a first pair of slot cooling channels 186, it should be understood that any number of slot cooling channels 120 may be located on the side of the stagnant cooling channel 116. The slot cooling channels 120 may be a pair of sequential cooling channels spaced apart from each other by a first linear distance (X) and a second linear distance (Y). The first linear distance (X) may be measured along a straight line between the sequential centers of the slot cooling channels 120 at outlet 150. The second linear distance (Y) may be measured along a straight line between the sequential centers of the slot cooling channels 120 at rear wall 164. The X:Y ratio may range between 1 and 6 or equal to 1, 6. In other words, 1 ≤ X / Y ≤ 6. In other embodiments, the X:Y ratio may range between 1 and 2 or equal to 1, 2. In other words, 1 ≤ X / Y ≤ 2. If only a single slot cooling channel 120 is located on the side of the stagnant cooling channel 116, then the distance (X) is still a straight line between the sequential centers, illustrated as (X'), and the distance (Y) is the shortest distance between the center of the rear wall of the slot cooling channel 120 and the first center line of the stagnant cooling channel 116, illustrated as (Y'). In this case, the parameter range still holds, 1 ≤ X' / Y' ≤ 6. In other embodiments, 1 ≤ X' / Y' ≤ 2. Although in Figure 10 The range is shown in the figure, but it should be understood that this range can be applied to any pair of sequential slot cooling channels 120 discussed herein.

[0076] The orientation of the diffuser groove 160 can have curvature such that the curvature of the diffuser groove 160 is complementary to the local curvature of the outer surface 126 of the airfoil 92. The complementary curvature can be defined as having a radius of curvature similar to or the same as the local radius of curvature of the outer surface 126 of the airfoil 92. Additionally, the angle β of the first centerline (CL1) of the diffuser groove at the outer surface 126 can be equal to 45 degrees, 90 degrees, or between 45 degrees and 90 degrees. Even at steep angles equal to 45 degrees, 90 degrees, or between 45 degrees and 90 degrees, the complementary local curvature of the diffuser groove 160 can provide cooling fluid as a cooling film along the outer surface 126 without requiring the diffuser groove to discharge fluid at small angles (such as 15 degrees). However, it should be understood that angles less than 45 degrees, such as equal to 30 degrees, 90 degrees, or between 30 degrees and 90 degrees, and angles equal to 0 degrees, 30 degrees, or between 0 degrees and 30 degrees, are also possible.

[0077] This complementary curvature provides reduced fluid separation for the cooling fluid discharged from the first set of cooling channels 114a, resulting in increased cooling film adhesion and effectiveness. Additionally, the multiple stagnant cooling channels 116 and slotted cooling channels 120 extending in the spanwise direction provide greater cooling film coverage on the airfoil 92 at or near the upstream edge 110, resulting in improved film cooling, higher operating temperatures, reduced cooling bleed air, increased engine efficiency, and lower overall fuel consumption.

[0078] Although the diagram shows a linear stagnant cooling channel 116, it should be understood that the stagnant cooling channel 116 can be any stagnant cooling channel 116a, 116b, 116c, 116d, 116e described herein.

[0079] Now for reference Figure 11 This illustrates another arrangement of a second set of cooling channels 114b, similar to the set of cooling channels 114 described herein. The second set of cooling channels 114b may include a first set of side cooling channels 144 discharging onto a first side 106 and a second set of side cooling channels 146 discharging onto a second side 108. The first set of side cooling channels 144 and the second set of side cooling channels 146 may be located on the side of a stagnation line (SL). The first set of side cooling channels 144 and the second set of side cooling channels 146 may each include a second pair of slot cooling channels 188 located on the side of the stagnation cooling channel 116.

[0080] Each of the first pair of slot cooling channels 186, each slot cooling channel 120, may include a primary cooling channel portion 140 and a secondary cooling channel portion 142 as described herein. The primary cooling channel portion 140 may be a tortuous primary cooling channel portion 140d with curvature including at least one inflection point 190. As shown, the inflection point 190 may define a curvature change from opening toward the upstream edge 110 to away from the upstream edge 110. It should be understood that the opposite direction is also anticipated. The two-part geometry for the tortuous primary cooling channel portion 140d enables a more orthogonal orientation at the junction 152, providing improved localized shock cooling in the impact zone 158. The two-part geometry also provides complementary curvatures for the outer surface 126, in relation to... Figure 10 The description is similar. In this way, the complex two-part geometry can simultaneously increase local shock cooling and improve film adhesion emitted along the outer surface 126.

[0081] Secondary cooling channel portion 142 may be a fourth curved secondary cooling channel portion 142e with curvature opening toward the stagnant cooling channel 116. The difference between the third curved secondary cooling channel portion 142d and the fourth curved secondary cooling channel portion 142e is that the third curved secondary cooling channel portion 142d is substantially orthogonal, while the fourth curved secondary cooling channel portion 142e is subtle, exhibiting variation in the direction defining the obtuse angle. Although illustrated as a second pair of slot cooling channels 188, it should be understood that any number of slot cooling channels 120 may be located on the side of the stagnant cooling channel 116.

[0082] Although the diagram shows a linear stagnant cooling channel 116, it should be understood that the stagnant cooling channel 116 can be any stagnant cooling channel 116a, 116b, 116c, 116d, 116e described herein.

[0083] Now for reference Figure 12 This illustrates another arrangement of a third set of cooling channels 114c, similar to the set of cooling channels 114 described herein. The third set of cooling channels 114c may include a first set of side cooling channels 144 discharging onto a first side 106 and a second set of side cooling channels 146 discharging onto a second side 108. The first set of side cooling channels 144 and the second set of side cooling channels 146 may be located on the sides of a stagnation line (SL). The first set of side cooling channels 144 and the second set of side cooling channels 146 may each include a third pair of slot cooling channels 192 located on the sides of the stagnation cooling channel 116.

[0084] Stagnant cooling channel 116 is shown as the slot cooling channel previously described herein. The third pair of slot cooling channels 192 may be similar to the first pair of slot cooling channels 186 and the second pair of slot cooling channels 188 previously described herein. As a non-limiting example, the third pair of slot cooling channels 192 may include a second primary cooling channel portion 140c and a fourth secondary cooling channel portion 142e. In the third pair of slot cooling channels 192, adjacent rows of slot cooling channels 120 may overlap each other in the spanwise direction. The overlap need not be limited to the spanwise direction, but may occur in both the spanwise and chordwise directions, such that one or more cooling channels interweave with each other. Furthermore, such overlap or interweaving is not limited to only two adjacent rows of slot cooling channels 120, but may include multiple rows of slot cooling channels 120 or discrete local slot cooling channels 120, which may be positioned based on local cooling or membrane pore requirements. Therefore, it should be understood that interweaving or overlapping configurations for the slot cooling channels 120 are contemplated. In this way, localized cooling can be increased or decreased near the upstream edge 110, wherein a greater concentration of the tank cooling channels 120 can provide advantageous greater localized cooling.

[0085] Although the stagnant cooling channel 116 is illustrated as a tank cooling channel 120, it should be understood that the stagnant cooling channel 116 can be linear or any of the stagnant cooling channels 116a, 116b, 116c, 116d, 116e described herein.

[0086] Now for reference Figure 13 This illustrates another arrangement of a fourth set of cooling channels 114d, similar to the set of cooling channels 114 described herein. The fourth set of cooling channels 114d may include a first set of side cooling channels 144 discharging onto a first side 106 and a second set of side cooling channels 146 discharging onto a second side 108. The first set of side cooling channels 144 and the second set of side cooling channels 146 may be located on the sides of the upstream edge 110. Unlike the previous sets of cooling channels described herein, the fourth set of cooling channels 114d does not have stagnant cooling channels. Instead, the first set of side cooling channels 144 and the second set of side cooling channels 146 are located on the sides of the upstream edge 110.

[0087] Primary cooling channel portion 140 can be any of the primary cooling channel portions 140a, 140b, 140c, 140d described herein. Although illustrated as a third-bend secondary cooling channel portion 142d, secondary cooling channel portion 142 can be any of the secondary cooling channel portions 142a, 142b, 142c, 142d, 142e described herein.

[0088] Figure 14 This is a top-down view of any of the cooling channels 116, 116a, 116b, 116c, 116d, 116e, 120 described herein, and, as a non-limiting example, a top-down view of the slot cooling channel 120. It is contemplated that any of the cooling channels 116, 116a, 116b, 116c, 116d, 116e, 120 as described herein may include a set of flow enhancers 194, as a non-limiting example, full-height heat transfer coefficient (HTC) enhancement features (such as pins), or partial-height HTC enhancement features (such as turbulence generators, bumps, pits, etc.). Higher HTC results in increased cooling of the outer wall 104 and an increase in the temperature of the cooling fluid (C). By placing HTC enhancement features, a balance can be achieved where the cooling benefit in one area exceeds the increase in the temperature of the cooling fluid (C).

[0089] like Figure 15 As shown, a set of flow enhancers 194 can be pins that extend the full height of the cooling channel 120.

[0090] Any of the primary cooling channel portions 140, 140a, 140b, 140c, 140d described herein may include a diffusion groove 160. Further, any of the primary cooling channel portions 140, 140a, 140b, 140c, 140d may include the impact zone 158 described herein. Additionally, any of the secondary cooling channel portions 142, 142a, 142b, 142c, 142d, 142e may include the metering section 170 described herein.

[0091] The cooling channels and concepts described herein provide improved localized cooling, such as improved impingement cooling, where fluid is distributed from the metering section. Furthermore, the diffuser channels can provide a larger surface area for convective cooling of the airfoil, and a wider cooling film layer along the outer surface of the airfoil, resulting in a more effective cooling film with greater adhesion. Improved cooling may require less cooling air, which can lead to less bleed air. The reduced amount of cooling air required can result in increased engine efficiency and reduced fuel consumption. Additionally, improved film cooling can provide higher operating temperatures, which can increase engine efficiency, improve component life, and reduce maintenance.

[0092] Although the walls of the engine components described herein are illustrated as generally straight, with the inner and outer surfaces parallel to each other, the engine components or airfoils described herein may be curved and oriented at an angle relative to the combustion flow. Although illustrated as generally uniform or continuously widening, the cross-section of the passage as described herein may be a collapse, widening, etc., that is allowed to vary in both directions. The variation may be nonlinear, non-constant, etc.

[0093] A set of cooling channels as described herein may include at least two cooling channels having channel outlets that are merged together to form a groove on the outer surface. Further contemplated is that all cooling channels in a set of cooling channels have channel outlets that are merged together to form a groove on the outer surface. The groove may extend radially along the airfoil.

[0094] It should be understood that the cooling channels described herein can be located in any part of the airfoil or engine component. Furthermore, it should be understood that, for example, the cooling channels described herein can have additional applicability to other parts of the airfoil, such as the leading edge, trailing edge, pressure side, suction side, tip, root, or even the internal structure of the airfoil. Further, in a non-limiting example, the cooling hole geometry can be applicable to other engine components besides the airfoil, such as blades, impellers, struts, shrouds, or combustor liners.

[0095] Cooling channels and other complex geometries described herein can be formed, for example, through additive manufacturing, while also being anticipated using conventional manufacturing methods. Additive manufacturing (AM) processes build parts layer by layer through the continuous deposition of material. AM is the apt name for the technique of constructing 3D objects by adding layer after layer of material, whether the material is plastic or metal. AM technology can utilize computers, 3D modeling software (computer-aided design or CAD), machine tools, and layered materials. Once a CAD sketch is generated, an AM device can read data from the CAD file and place or add layers of liquid, powder, sheet, or other materials in a layer-by-layer manner to create a 3D object. It should be understood that the term "additive manufacturing" encompasses many techniques, including subsets such as 3D printing, rapid prototyping (RP), direct digital manufacturing (DDM), layered manufacturing, and additive manufacturing. Non-limiting examples of additive manufacturing that can be used to form additively manufactured parts include powder bed melting, vat photopolymerization, binder jetting, material extrusion, directional energy deposition, material jetting, or sheet lamination. Additive manufacturing, such as 3D printing, direct metal laser melting, direct metal laser sintering, or electroforming, can provide the ability to form complex geometries as described herein, where such formation via conventional manufacturing methods such as casting or drilling can be challenging, expensive, time-consuming, and have low yields. Furthermore, the cooling channels described herein can be produced via indirect additive methods, i.e., printing the core and casting, or the core can be fabricated using an additively manufactured core or via RMC.

[0096] It should be understood that the disclosed design is not limited to turbine engines with fan and supercharger sections, but is also applicable to turbojet engines and turbine engines.

[0097] Within the scope not yet described, various features and structures of different aspects may be combined or substituted for each other as needed. The fact that a feature is not illustrated in all examples does not mean that it cannot be illustrated in this way, but rather that it is done for the sake of brevity. Therefore, various features of different aspects may be mixed and matched as needed to form new aspects, regardless of whether the new aspects are explicitly described. All combinations or substitutions of the features described herein are covered by this disclosure.

[0098] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and any incorporation methods. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0099] Further aspects of this disclosure are provided by the subject matter of the following provisions:

[0100] An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising: a wall defining an interior and having an outer surface through which the combustion airflow passes, the outer surface defining a first side and a second side and having edges; at least one cooling duct disposed in the interior and having duct sidewalls; and a set of cooling channels formed in the wall and fluidly connecting the at least one cooling duct to the outer surface, at least one of the cooling channels comprising: a primary cooling channel portion extending between an intermediate outlet and a channel outlet, the channel outlet leading to an adjacent... The outer surface of the edge; a second channel portion extending between an inlet fluidly connected to the at least one cooling conduit and the intermediate outlet, the first channel portion and the second channel portion together defining the at least one cooling channel extending along the flow direction between the inlet and the channel outlet; a diffusion groove located in the primary cooling channel portion and extending along the flow direction between the rear wall and the channel outlet, the diffusion groove having a groove sidewall defining a first centerline of the groove; an impact zone fluidly connected to the diffusion groove adjacent to the rear wall, having an impact surface, and fluidly connected to the secondary cooling channel portion at a junction adjacent to the rear wall and opposite to the impact surface.

[0101] The engine component according to any one of the foregoing clauses, wherein at least one of the first cooling channel portion or the secondary cooling channel portion is bent.

[0102] The engine component according to any one of the foregoing clauses, wherein the secondary cooling passage portion is a curved passage.

[0103] The engine component according to any one of the foregoing clauses, wherein the diffuser groove is a curved diffuser groove, and the curved diffuser groove and the curved channel are curved in opposite directions.

[0104] The engine component according to any one of the foregoing clauses, wherein the primary cooling passage is partially curved and includes an inflection point.

[0105] The engine component according to any one of the foregoing clauses, wherein the outer surface extends between the upstream edge and the downstream edge to define a chordal direction, and extends between the root and the tip to define a spanwise direction.

[0106] The engine component according to any one of the foregoing clauses, wherein the set of cooling channels is located on the upstream edge.

[0107] The engine component according to any one of the foregoing clauses, wherein the flow direction extends in the spanwise direction along at least a portion of the curved channel.

[0108] The engine component according to any one of the foregoing clauses, wherein the set of cooling channels is a plurality of cooling channels located on the side of the edge, extending in the spanwise direction, and positioned adjacent to or at the upstream edge.

[0109] The engine component according to any one of the foregoing clauses, wherein the plurality of cooling channels includes a first side group of cooling channels and a second side group of cooling channels located on the side of the edge.

[0110] The engine component according to any one of the foregoing clauses further includes at least one stagnation channel extending between a stagnation inlet fluidly connected to the at least one cooling duct and a stagnation outlet positioned along the edge.

[0111] The engine component according to any one of the foregoing clauses further includes an outlet groove extending along the outer surface in the spanwise direction, and the diffusion groove leads to the outlet groove.

[0112] The engine component according to any one of the foregoing clauses, wherein the intermediate outlet is spaced apart from the rear wall to define a pocket portion.

[0113] The engine component according to any one of the foregoing clauses, wherein the secondary cooling passage portion includes a metering section.

[0114] A method for cooling an engine component having an outer wall defining an interior, the method comprising: allowing cooling fluid to flow into the interior of the engine component; redirecting the cooling fluid from a first direction to a second direction different from the first direction via a curved channel; causing the cooling fluid to impinge on an impact surface in a diffusion groove located in the outer wall; diffusing the cooling fluid to the exterior of the engine component through the diffusion groove; and discharging the cooling fluid at a channel outlet along an edge at or adjacent to an upstream edge of the engine component.

[0115] The method according to any one of the foregoing clauses further includes discharging the cooling fluid from the diffusion tank through a channel outlet, the channel outlet opening onto the outer surface of the outer wall in a third direction, the third direction being different from the first direction or the second direction.

[0116] The method according to any one of the foregoing clauses further includes discharging the cooling fluid from the diffusion tank through a channel outlet, the channel outlet opening toward the outer surface of the outer wall in the first direction.

[0117] The method according to any one of the foregoing clauses further includes expanding the cooling fluid in the spanwise direction.

[0118] The method according to any one of the foregoing clauses further includes passing the cooling fluid through a stagnant channel that extends between the interior and the outer surface of the outer wall.

[0119] The method according to any one of the foregoing clauses further includes discharging the cooling fluid at a stagnant outlet at the edge.

Claims

1. An engine component for a turbine engine, the turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, characterized in that, The engine components include: An outer wall, defining an interior and having an outer surface through which the combustion gas stream flows, the outer surface defining a first side and a second side and having edges. At least one cooling conduit, the at least one cooling conduit being disposed inside and having conduit sidewalls; A set of cooling channels, said set of cooling channels being formed in the outer wall and fluidly connecting the at least one cooling conduit to the outer surface, wherein at least one of the cooling channels comprises: A primary cooling channel portion extends between an intermediate outlet and a channel outlet, the channel outlet leading to the outer surface adjacent to the edge; The secondary cooling channel portion extends between the inlet, which is fluidly connected to the at least one cooling duct, and the intermediate outlet. The primary cooling channel portion and the secondary cooling channel portion together define the at least one cooling channel extending along the flow direction between the inlet and the channel outlet. A diffusion channel, located within the primary cooling channel portion and extending along the flow direction between the rear wall and the channel outlet, the diffusion channel having sidewalls defining a channel centerline. An impact zone, fluidly connected to the diffusion channel adjacent to the rear wall, has an impact surface and is fluidly connected to the secondary cooling channel portion at a junction adjacent to the rear wall and opposite to the impact surface. The secondary cooling channel portion is a curved channel. The diffusion groove is a curved diffusion groove, and the curved diffusion groove and the curved channel are curved in opposite directions.

2. The engine component according to claim 1, characterized in that, The primary cooling channel is partially bent.

3. The engine component according to any one of claims 1-2, characterized in that, The primary cooling channel is partially curved and includes inflection points.

4. The engine component according to any one of claims 1-2, characterized in that, The outer surface extends between the upstream and downstream edges and between the root and the tip to define the spanning direction.

5. The engine component according to claim 4, characterized in that, The set of cooling channels is located on the upstream edge.

6. The engine component according to claim 5, characterized in that, The flow direction extends in the spanwise direction along at least a portion of at least one of the cooling channels.

7. The engine component according to claim 4, characterized in that, The set of cooling channels is a plurality of cooling channels located on the side of the edge, extending in the spanwise direction, and positioned adjacent to or at the upstream edge.

8. The engine component according to claim 7, characterized in that, The plurality of cooling channels includes a first side group of cooling channels and a second side group of cooling channels located on the sides of the edge.

9. The engine component according to claim 4, characterized in that, It further includes an outlet groove extending along the outer surface in the spanwise direction, and the diffusion groove leads to the outlet groove.

10. The engine component according to any one of claims 1-2, characterized in that, It further includes at least one stagnation channel extending between a stagnation inlet fluidly connected to the at least one cooling conduit and a stagnation outlet positioned along the edge.

11. The engine component according to any one of claims 1-2, characterized in that, The intermediate outlet is spaced apart from the rear wall to define the bag portion.

12. The engine component according to any one of claims 1-2, characterized in that, The at least one cooling channel is a pair of sequential cooling channels, the pair of sequential cooling channels being spaced apart by a first linear distance between the sequential centers of the cooling channels at the channel outlet, and a second linear distance being the closest distance between the sequential centers of the cooling channels, wherein the ratio between the first linear distance and the second linear distance is equal to 1, 6 or between 1 and 6.

13. A method for cooling an engine component according to claim 1, characterized in that, The method includes: Allowing cooling fluid to flow into the interior of the engine component; The cooling fluid is redirected from a first direction to a second direction different from the first direction by means of a curved channel; The cooling fluid is impacted on the impact surface in the diffusion groove located in the outer wall; The cooling fluid is diffused to the outside of the engine components through the diffusion channels; and The cooling fluid is discharged at the outlet of the channel.

14. The method according to claim 13, characterized in that, The method further includes discharging the cooling fluid from the diffusion tank through the channel outlet, the channel outlet opening onto the outer surface of the outer wall in a third direction, the third direction being different from the first direction or the second direction.

15. The method according to claim 13, characterized in that, The method further includes discharging the cooling fluid from the diffusion tank through the channel outlet, the channel outlet opening onto the outer surface of the outer wall in the first direction.

16. The method according to any one of claims 13-15, characterized in that, This further includes expanding the cooling fluid in the spanwise direction.

17. The method according to any one of claims 13-15, characterized in that, It further includes passing the cooling fluid through a stagnant channel that extends between the interior and the outer surface of the outer wall.

18. The method according to claim 17, characterized in that, This further includes discharging the cooling fluid at a stagnant outlet at the edge.

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