Components with cooling channels for turbine engines

Abstract

An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising a wall defining an interior and having an outer surface on which the combustion airflow flows, the outer surface extending between a leading edge and a trailing edge to define a first side and a second side in a chordal direction; at least one cooling duct located internally and fluidly coupled to the cooling airflow. A main cooling passage having at least one inlet fluidly coupled to the at least one cooling duct and a main outlet on the outer surface. The passage connecting the at least one inlet to the main outlet is divided into a first portion and a second portion. The main outlet is spaced a predetermined distance from the trailing edge.

Description

Technical Field

[0001] This disclosure generally relates to a cooling channel for an engine, and more specifically to a set of cooling channels for cooling the trailing edge of an airfoil. Background Technology

[0002] 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 fixed impeller blades and rotating turbine blades.

[0003] Gas turbine engines used in aircraft are designed to operate at high temperatures to maximize engine efficiency; therefore, 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 requiring cooling. Temperatures in the high-pressure turbine are approximately 1000°C to 2000°C, while 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.

[0004] Modern turbine blades typically include one or more internal cooling circuits to guide cooling air through the airfoil to cool different parts of the airfoil, and may include dedicated cooling circuits for cooling different parts of the airfoil (e.g., the leading edge, trailing edge, and tip of the airfoil). Summary of the Invention

[0005] The aspects and advantages of this disclosure will be set forth in part in the description which follows, or may be apparent from the description, or may be learned by practice of the disclosure herein.

[0006] In one aspect, this disclosure relates to 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 over which the combustion airflow flows, the outer surface extending between a leading edge and a trailing edge to define a first side and a second side in a chordal direction, wherein the wall has a thickness “T” near the trailing edge; at least one cooling duct located in the interior and fluidly coupled to the cooling airflow; a main cooling channel having at least one inlet fluidly coupled to the cooling duct, a main outlet on the outer surface, and a channel connecting the inlet to the outlet, wherein the main outlet has a downstream point spaced from the trailing edge by a first distance D1 and an upstream point spaced from the trailing edge by a second distance D2, wherein the thickness T is greater than or equal to the difference between the first distance D1 and the second distance D2 (T>(D2-D1)).

[0007] In another aspect, this disclosure relates to an airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising: a wall defining an interior and having an outer surface over which the combustion airflow flows, the outer surface defining a first side and a second side extending between a leading edge and a trailing edge to define a chordally oriented direction, wherein the wall has a thickness “T” near the trailing edge; at least one cooling duct located in the interior and fluidly coupled to the cooling airflow; a main cooling channel having at least one inlet fluidly coupled to the cooling duct, a main outlet on the outer surface, a channel connecting the at least one inlet to the main outlet, and an impact zone located within the channel between the at least one inlet and the main outlet, wherein the impact zone separates the channel into a first portion and a second portion, the first portion having a curved centerline extending between the at least one inlet and the impact zone, and the second portion having a diffusion section extending between the impact zone and the main outlet.

[0008] These and other features, aspects, and advantages of this disclosure will become more readily understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and form a part of this specification, illustrate the disclosure and, together with the description, serve to explain the principles disclosed herein. Attached Figure Description

[0009] This specification sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, with reference to the accompanying drawings, wherein:

[0010] Figure 1 This is a schematic cross-sectional view of a gas turbine engine used in aircraft.

[0011] Figure 2 yes Figure 1 A perspective view of the airfoil of an engine, the airfoil being a blade that includes a set of cooling channels.

[0012] Figure 3A It is along Figure 2 A cross-sectional view of a set of cooling channels taken from line III-III.

[0013] Figure 3B This is an enlarged view of a variant of the outlet portion of a cooling channel, based on one aspect disclosed in this article.

[0014] Figure 4 It comes from Figure 3A A schematic diagram of a cooling channel with a central opening.

[0015] Figure 5 It is along Figure 4 The image shows a cross-sectional view of the cooling channel taken by line VV, illustrating an exemplary shape of the central opening.

[0016] Figure 6 It is along Figure 4 An alternative cross-sectional view of the cooling channel, taken by line VV, shows another exemplary shape with a central opening.

[0017] Figure 7 It is along Figure 4 Another alternative cross-sectional view of the cooling channel, taken by line VV, shows yet another exemplary shape with a central opening.

[0018] Figure 8 This is based on another aspect disclosed in this article. Figure 2 An alternative cross-sectional view of a set of cooling channels taken from line III-III.

[0019] Figure 9 This is based on another aspect disclosed in this article. Figure 2 Another alternative cross-sectional view of a set of cooling channels cut off by line III-III.

[0020] Figure 10 It is along Figure 9 The image shows a cross-sectional view of the cooling channel taken by line XX, illustrating the distribution of flow enhancers within the cooling channel.

[0021] Figure 11 It is a cross-sectional view of the trailing edge of an alternative set of cooling channels, in which only one cooling channel has a supply channel and an outlet channel. Detailed Implementation

[0022] The various aspects of the disclosure described herein relate to cooling vents disposed in engine components. More specifically, this disclosure relates to one or more cooling vents disposed in an airfoil near the trailing edge of the airfoil. For illustrative purposes, this disclosure will be described with respect to turbine blades for aircraft gas turbine engines. 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.

[0023] 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" indicate what is in front of something, and "behind" or "behind" indicate what is behind something. For example, when used in relation to fluid flow, "front" or "in front" can indicate upstream, and "behind" or "behind" can indicate downstream.

[0024] Furthermore, 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 outer circumference of the engine. Additionally, as used herein, the term "group" or a "set" of elements can be any number of elements, including only one.

[0025] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are used for identification purposes only to aid the reader's understanding of this disclosure and should not be construed as limiting the embodiments, particularly regarding the location, orientation, or purpose of the aspects of this disclosure described herein. Connection references (e.g., attachment, coupling, connection, and engagement) are to be interpreted broadly and may include intermediate members between sets of elements and relative movement between elements, unless otherwise stated. Therefore, a connection reference does not necessarily imply that two elements are directly connected and have a fixed relationship with each other. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying drawings may vary.

[0026] Figure 1 This 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 centerline 12 that extends from the front 14 to the rear 16. The engine 10 includes, in downstream series 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.

[0027] Fan section 18 includes a fan housing 40 surrounding fan 20. Fan 20 includes a plurality of fan blades 42 arranged radially around centerline 12. HP compressor 26, combustor 30 and HP turbine 34 form the 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.

[0028] An HP shaft or spool 48, coaxially arranged around the 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 centerline 12 of the engine 10, drives the LP turbine 36 to the LP compressor 24 and the fan 20. The spools 48 and 50 are rotatable around the engine centerline and are connected to multiple rotatable elements that collectively define a rotor 51.

[0029] 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 centerline 12 to the blade tips, while the corresponding static compressor blades 60 and 62 are positioned upstream and near the rotating blades 56 and 58. It is worth noting that... Figure 1 The number of blades, impellers, and compressor stages shown is selected for illustrative purposes only; other numbers are also possible.

[0030] Blades 56 and 58 for the compressor stage can be mounted (or integrated) onto a disc 61, which is mounted onto a corresponding one of the HP spool 48 and the LP spool 50. Impeller blades 60 and 62 for the compressor stage can be mounted circumferentially onto the core housing 46.

[0031] HP turbine 34 and LP turbine 36 each comprise multiple turbine stages 64 and 66, 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, the multiple turbine blades 68 and 70 may be arranged in a ring and may extend radially outward relative to a centerline 12, while the corresponding static turbine blades 72 and 74 are positioned upstream and near the rotating blades 68 and 70. It is worth noting that... Figure 1 The number of blades, impellers, and turbine stages shown is selected for illustrative purposes only; other numbers are also possible.

[0032] Blades 68 and 70 for the turbine stage can be mounted on disk 71, which is mounted on a corresponding one of HP spool 48 and LP spool 50. Blades 72 and 74 for the compressor stage can be mounted circumferentially to the core housing 46.

[0033] As a complement 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 referred to individually or collectively as the stator 63. Therefore, the stator 63 can refer to the combination of non-rotating elements throughout the engine 10.

[0034] In operation, the airflow leaving fan section 18 is split, with a portion directed to LP compressor 24. LP compressor 24 then supplies pressurized air 76 to HP compressor 26, which further pressurizes the air. The pressurized air 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, causing fan 20 and LP compressor 24 to rotate.

[0035] A portion of the pressurized gas flow 76 can be extracted from the compressor section 22 as bleed air 77. Bleed air 77 can be extracted 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 increases significantly to above the bleed air temperature. Bleed air 77 can be used to reduce the temperature of core components downstream of the combustor.

[0036] The remainder of the airflow 78 bypasses the LP compressor 24 and engine core 44, and exits the engine assembly 10 via a fixed row of blades on the fan exhaust side 84, 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.

[0037] Some of the air supplied by fan 20 can bypass engine core 44 and be used to cool parts of engine 10, especially hot parts, and / or to cool other aspects of the aircraft or 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, especially 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.

[0038] Now for reference Figure 2 , display Figure 1The turbine blade 68 is an engine component in the form of one of the turbine blades 68 of the 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 utilize cooling passages. The turbine blade 68 includes a dovetail 90 and an airfoil 92. The dovetail 90 also includes at least one inlet passage 100, shown as two exemplary inlet passages 100, each inlet passage 100 extending through the dovetail 90 to provide internal fluid communication with the airfoil 92 at a passage outlet 102. It should be understood that the dovetail 90 is shown in cross-section such that the inlet passage 100 is received 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.

[0039] Airfoil 92 extends radially between tip 94 and root 96, defining a spanwise direction between the tip 94 and root 96. Airfoil 92 is mounted to dovetail 90 at platform 98 at root 96. Platform 98 helps to radially contain the mainstream airflow of the turbine engine. Furthermore, airfoil 92 includes an outer wall 104, which includes a first side 106 and a second side 108, and extends between leading edge 110 and trailing edge 112 to define a chordal direction between the leading edge 110 and trailing edge 112. As shown, first side 106 can be a pressure side, and second side 108 can be an intake side of a steering blade. It is also contemplated that airfoil 92 can be a non-steering blade, such as a non-limiting example of a frame fairing. It is also contemplated that neither first side 106 nor second side 108 is curved to form a pressure side and / or an intake side. The outer wall 104 may partially define and surround at least one cooling conduit 118, as shown in two exemplary cooling conduits 118 forming a cooling circuit 128.

[0040] A set of cooling channels 114 exits on a first side 106 near the trailing edge 112 and is arranged in a spanwise configuration. Optionally, another set of cooling channels may be provided on a second side 108, but is... Figure 2 The three-dimensional view is obscured. Furthermore, it is conceivable that the cooling channel 114 may have an outlet on the trailing edge 112.

[0041] During operation, a hot gas flow (H), such as a burner flow, can pass along the exterior of the outer wall 104 of the airfoil 92. A cooling fluid flow (C) can be supplied to the inlet passage 100 and enter the airfoil 92 at the passage outlet 102, entering the cooling duct 118. The cooling fluid flow (C) can be supplied throughout the airfoil 92 and discharged as a cooling film from the cooling passage 114.

[0042] Now for reference Figure 3A ,show Figure 2Section III-III, airfoil 92 includes an interior 120 defined by an outer wall 104. The outer wall 104 may also include an inner surface 122 and an outer surface 124, wherein the inner surface 122 defines the interior 120. Ribs 126 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 120 into individual cooling conduits 118, including the rearmost cooling conduit 118 as shown. Figure 2 The cooling duct 118 may form at least a portion of the cooling circuit 128 within the interior 120 of the airfoil 92. It should be understood that the rib 126, cooling duct 118, and cooling circuit 128 shown are exemplary, and numerous different cooling circuits 128 may be formed within the airfoil 92, including but not limited to cooling ducts, channels, passages, pipes, cooling inlets, full-length or partial-length ribs in the spanwise or chordal plane, near-wall cooling channels, turbulence generators, pins, fins, or one or more of any other structures forming the airfoil 92.

[0043] A set of cooling channels 114 fluidly connects the interior 120 to the exterior of the airfoil 92 at the outer surface 124 and provides for the discharge of cooling fluid along the outer surface 124 near the trailing edge 112. The set of cooling channels 114 may include a main cooling channel 130, which is positioned adjacent to the trailing edge 112 and discharges from a cooling duct 118 located substantially toward the trailing edge 112. The outer wall 104 may have a thickness (T) near the trailing edge 112. It can be seen more clearly that the trailing edge 112 is the furthest point of the airfoil 92 in the chord. The thickness (T) may be defined as the dimension of the outer wall 104 upstream of the trailing edge 112, between the first side 106 and the second side 108, at the significant change in curvature along the outer wall 104 from each of the first side 106 and the second side 108 to the trailing edge 112. A significant change in curvature can be defined as the first tangent point (P1) where the first side 106 meets the first trailing edge fillet (F1) and the second tangent point (P2) where the second side 108 meets the second trailing edge fillet (F2). Alternatively, the first tangent point (P1) and the second tangent point (P2) can be defined as at least a 5% change (ΔC) between either the first side 106 or the second side 108 and the corresponding fillet (F1, F2). In other words, the thickness (T) is the straight-line distance between points (P1) and (P2).

[0044] The main cooling channel 130 may include at least one inlet 132 at the cooling duct 118 and a main outlet 134, referred to herein as outlet 134, at the outer surface 124. The main cooling channel 130 may be two-part, having a first portion 136 including a supply channel 138 and a second portion 140 including an outlet channel 142. An intermediate opening 144 may fluidly connect the supply channel 138 to the outlet channel 142.

[0045] A supply channel 138 extends between a cooling conduit 118 and an outlet channel 142, fluidly connecting the cooling conduit 118 to the outlet channel 142. The supply channel 138 may be curved or arcuate, curving in any direction, such as radial, axial, spanwise, or chordwise directions in a non-limiting example. As used herein, curvature may mean that the centerline is non-linear. Alternatively, curvature may mean that at least a portion of the supply channel 138 is arcuate or includes an arcuate outer wall defining a curvature. The supply channel 138 may define a curved centerline (CCL) extending between at least one inlet 132 and an intermediate opening 144. As a non-limiting example, the curved centerline (CCL) may define a first turn 146 toward a first side 106. The first turn 146 may define an angle greater than 90 degrees. Alternatively, it is contemplated that the supply channel 138 is linear. Furthermore, it is contemplated that one or both of the supply channel 138 and the outlet channel 142 are curved.

[0046] The second part 140 may further include an impact zone 148. The impact zone 148 may include a first deflection 146, an intermediate opening 144, and an impact surface 149 defined by a portion of the outlet channel 142 opposite to the intermediate opening 144, at which the cooling fluid flow (C) from the supply channel 138 impacts, or impinges, the impact surface 149. As shown, the first deflection 146 may be directed toward the first side 106 such that the impact occurs along the outer wall 104 of the first side 106, resulting in cooling of the first side 106.

[0047] The second portion 140 may further include a pocket 150. The pocket 150 may be defined by one end of the outlet passage 142 opposite to the outlet 134. The pocket 150 may be located near the impact zone 148. The pocket 150 may trap particles to clean the cooling fluid (C) before it flows through the remainder of the outlet passage 142. Although illustrated with a pocket 150, the set of cooling passages 114 does not necessarily need to include the pocket 150.

[0048] The outlet channel 142 may define at least one centerline, and multiple centerlines are illustrated. A first centerline (CL1) may extend from the bag 150 toward the trailing edge 112 in a first direction. The first centerline (CL1) may be generally parallel to the first side 106. Although illustrated as generally parallel, the first centerline (CL1) may be parallel to either the first side 106 or the second side 108, or extend in any direction toward the trailing edge 112. A second centerline (CL2) may extend from the outlet 134 toward the second side 108 in a second direction different from the first direction. A second deflection 152 may be defined by the intersection of the first centerline (CL1) and the second centerline (CL2). The second deflection 152 may define an angle of less than 90 degrees. Although the outlet channel 142 is shown as generally linear, it is conceivable that the outlet channel 142 may be curved or arcuate in any direction, similar to that described for the supply channel 138.

[0049] The main cooling channel does not need to exit precisely at the trailing edge 112. The outlet 134 of the outlet channel 142 can be located on the outer surface 124, downstream of the rearmost cooling conduit 118, but upstream of the trailing edge 112. The outlet 134 of the outlet channel 142 can be located within a predetermined distance of the trailing edge 112. The outlet 134 can define an opening extending along the outer surface 124 between the downstream edge 160 and the upstream edge 162. A first dimension measured from a point at the downstream edge 160 to the trailing edge 112 defines a first distance (D1). A second dimension measured from a point at the upstream edge 162 to the trailing edge 112 defines a second distance (D2). The first distance (D1) and the second distance (D2) are each defined as a straight-line distance from the trailing edge to each of the corresponding upstream edge 160 and downstream edge 162. As shown, the measuring lines extending from the trailing edge 112, the corresponding upstream edge 160, and the downstream edge 162 should be parallel to each other.

[0050] In the first example, see Equation 1 below, the thickness (T) is greater than or equal to the difference between the first distance (D1) and the second distance (D2).

[0051] Equation 1: (T≥(D2-D1))

[0052] In the second example, see Equation 2 below, the first distance (D1) is greater than or equal to half the thickness.

[0053] Equation 2: (D1≥(T / 2))

[0054] In the third example, see Equation 3 below, the second distance (D2) is greater than or equal to the thickness (T). Furthermore, the second distance (D2) is less than or equal to five times the thickness.

[0055] Equation 3: (T≤D2≤5*T)

[0056] A secondary cooling channel 170, which is geometrically similar to the main cooling channel 130, may be located upstream of the main cooling channel 130. The secondary cooling channel 170 may extend between a second inlet 172 and a second outlet 174 located upstream of the outlet 134 along the first side 106.

[0057] Although the illustrated set of cooling channels 114 includes a primary cooling channel 130 and a secondary cooling channel 170, any number of cooling channels is conceivable, and there may be one or more. Furthermore, the set of cooling channels 114 may be arranged in the spanwise direction. Additionally, each cooling channel shown may be part of a set of cooling channels 114 arranged spanwise. Furthermore, it should be understood that the supply channel 138 of the primary cooling channel 130 is longer than the supply channel 178 of the secondary cooling channel, allowing partial overlap between the cooling channels 114 defined along the chord of the airfoil 92. This overlap can be used to tailor localized cooling of the portions of the airfoil 92 that require the most localized cooling from the cooling channels 114; for example, solid-state analysis can be used to identify these portions.

[0058] Figure 3B This is an enlarged view of a variant of a set of cooling channels 114 at outlet 134. It is envisioned that, during production, outlet 134 may terminate at at least one fillet, shown herein as the third and fourth fillets (F3, F4). If fillets are formed at outlet 134, the difference between the second distance (D2) and the first distance (D1) is the minimum dimension of outlet 134 measured along outer surface 124. In other words, the points at downstream edge 160 and upstream edge 162 are now points 160a, 162a in this variant, separated from the third and fourth fillets (F3, F4). Each point 160a, 162a is located at the intersection of a dashed line extending through outer surface 124 of outlet 134 and a dashed line extending from the tangent of a point (P3, P4) in the main cooling channel 130, where the third and / or fourth fillets (F3, F4) begin at points (P3, P4), respectively. It should be understood that, in all aspects described herein, the dimension (D2-D1) is the minimum dimension of the outlet 134 at the outer surface 124.

[0059] Figure 4 This is a schematic diagram of a portion of one of a set of cooling channels 114, specifically a schematic diagram of the main cooling channel 130 as a non-limiting example. The schematic diagram includes a central opening, an impact zone 148, and a bag 150. The supply channel 138 may be the minimum cross-sectional area (CA) defining the main cooling channel 130. m The metering section. It should be understood that more than one metering section can be formed in a set of cooling channels 114. The metering section can be formed from the inlet 132 ( Figure 3AIt extends to the intermediate opening 144. Further, it is envisioned that the measuring section has no length and can define either the intermediate opening 144 or the inlet 132. Cross-sectional area (CA) m It can be circular, but any cross-sectional shape can be conceived.

[0060] Go to Figure 5 The illustration shows Figure 4 A top view along line VV. In one example, the central opening 144 may have a racetrack shape 144a extending in the spanwise direction. The exit passage 142 may be a diffusion section, such that the cross-sectional area (CA) of the exit passage 142 is... d The cross-sectional area (CA) can be increased by extending downstream from the central opening 144. In one example, the cross-sectional area (CA) d The cross-sectional area (CA) is continuously increasing. In an alternative, non-limiting embodiment, the increased cross-sectional area (CA) d It can be a discontinuous or gradually increasing cross-sectional region.

[0061] The distance (A) measured along the centerline (CL) of the intermediate opening 144 defines the width of the outlet channel 142. The distance (B) measured along the centerline of the intermediate opening defines the width of the intermediate opening 144. The ratio of A to B can be less than 3 (A / B < 3). It is further envisioned that the ratio of A to B can be less than 2 (A / B < 2).

[0062] Go to Figure 6 The illustration shows Figure 4 Another exemplary top view along line VV. In another example, the intermediate opening 144 can be multiple openings, illustrated as a pair of openings (N=2), each opening having a substantially circular shape 144b with a diameter (D). It should be understood that when the intermediate opening 144 is not circular, the diameter (D) as described herein can be a hydraulic diameter (DH). The letter “N” can indicate the number of openings. The distance (A) measured along the centerline (CL) of the intermediate opening 144 defines the width of the outlet channel 142. The ratio of A:(D*N) can be less than 4 ((A / (D*N)<4). The distance (B) measured along the centerline of the intermediate opening defines the width of the intermediate opening 144. The ratio of A:B can be less than 3 (A / B<3). It is further envisioned that the ratio of A:B can be less than 2 (A / B<2).

[0063] Turning Figure 7 The illustration shows Figure 4Another exemplary top view along line VV. In yet another example, the central opening 144 can be multiple openings, illustrated as a pair of openings (N=2), each opening having a generally runway shape 144c extending in the chordal direction and defining a hydraulic diameter (DH). The number of openings can be represented by the letter "N". The runway shape, also known as the stadium shape, is a two-dimensional geometry consisting of rectangles with semicircles on a pair of opposite sides. The distance (A) measured along the centerline (CL) of the central opening 144 defines the width of the exit passage 142. The ratio of A:(DH*N) can be less than 4 ((A / (DH*N)<4). A and B are distances measured as described above. The ratio of A:B can be less than 3 (A / B<3). Further envisioned, the ratio of A:B can be less than 2 (A / B<2).

[0064] Figure 8 A set of cooling channels 214 is shown according to another aspect of the disclosure discussed herein. The set of cooling channels 214 is substantially similar to the set of cooling channels 114; therefore, identical portions will be identified by the same number incremented by 100. It should be understood that the description of the identical portions of the set of cooling channels 114 applies to the set of cooling channels 214 unless otherwise stated.

[0065] A set of cooling channels 214 includes a main cooling channel 230 extending between at least one inlet 232 at the cooling duct 118 and an outlet 234 at the outer surface 124. The main cooling channel 230 may be two-part, having a first portion 236 including a supply channel 238 and a second portion 240 including an outlet channel 242. An intermediate opening 244 fluidly connects the supply channel 238 to the outlet channel 242.

[0066] The supply channel 238 may be defined by a curved centerline (CCL) extending between at least one inlet 232 and an intermediate opening 244. The curved centerline (CCL) may define a first deflection 246 toward the second side 108. The first deflection 246 may define an angle greater than 90 degrees. The first deflection 246 may be an angle close to 180 degrees. For example, when considering the bag 250 as part of the first deflection 246, the cooling fluid flow (C) may deflect 180 degrees.

[0067] The second part 240 may also include an impact zone 248. As shown, the first deflection 246 may be directed toward the second side 108, causing an impact along the second side 108 at the outer wall 104, resulting in cooling of the second side 108.

[0068] Although the set of cooling channels 214 shown includes the main cooling channel 230, any number of cooling channels is conceivable, and there may be one or more. Furthermore, the set of cooling channels 214 can be arranged in a spanwise group, such that each cooling channel shown is part of a spanwise arranged set of cooling channels 214.

[0069] Figure 9 A set of cooling channels 314 is shown according to another aspect of the disclosure discussed herein. The set of cooling channels 314 is substantially similar to the set of cooling channels 114; therefore, identical portions will be identified by the same number incremented by 200. It should be understood that the description of the identical portions of the set of cooling channels 114 applies to the set of cooling channels 314 unless otherwise stated.

[0070] A set of cooling channels 314 is a pair of nested cooling channels, comprising a main cooling channel 330 and secondary cooling channels 370 with a geometry similar to the main cooling channel 330. The main cooling channel 330 may include at least one inlet 332 at the cooling duct 118 and an outlet 334 at the outer surface 124. The main cooling channel 330 may be two-part, having a first portion 336 including a main supply channel 338 and a second portion 340 including an outlet channel 342. An intermediate opening 344 fluidly connects the main supply channel 338 to the outlet channel 342.

[0071] The secondary cooling passage 370 may extend between a second inlet 372 near the cooling duct at inlet 332 and a second outlet 374 located upstream of outlet 334 along the first side 106. The secondary cooling passage 370 may also be two-part, having a first portion 376 including a supply passage 378 and a second portion 380 including an outlet passage 382. An intermediate opening 384 may fluidly connect the supply passage 378 to the outlet passage 382.

[0072] The second portion 340 of the main cooling channel 330 extends from the cooling duct 118 near the second side 108 toward the trailing edge 112. The outlet channel 342 may define a first centerline (CL1) that is generally parallel to the second side 108.

[0073] The second portion 380 of the secondary cooling passage 370 is spaced apart from the second portion 340 of the main cooling passage 330 to define an intermediate wall 386. The outlet passage 382 may define a third centerline (CL3) extending substantially parallel to the first centerline (CL1). In some embodiments, the sum of the lengths of the first and second centerlines (CL1+CL2) is greater than (CL3) shown.

[0074] The second portions 340 and 380 may each include impact zones 348 and 388. The impact zone 348 may be defined by the flow (C) of cooling fluid from the supply channels 338 and 378 impacting a portion of the outlet channels 342 and 382 opposite to the intermediate openings 344 and 384. Further, it is envisioned that the flow enhancer 392 may be located within both second portions 340 and 380.

[0075] Supply channels 338 and 378 may each define a curve centerline (CCL) extending between their respective inlets 332 and 372 and intermediate openings 344 and 384. The curve centerline (CCL) of the main supply channel 338 may define a first deflection 346 toward the second side 108. The first deflection 346 may define an angle greater than 90 degrees. The secondary supply channel 378 may be longer than the main supply channel 338 to include a secondary deflection 390 mirroring the first deflection 346. The secondary deflection 390 is located rearward relative to the first deflection 346 and toward the first side 106. As shown, deflections 346 and 390 may be toward the second side 108. Therefore, impact may occur along the outer wall 104 and intermediate wall 386 of the second side 108, resulting in cooling of the second side 108 and intermediate wall 386.

[0076] The primary cooling channel 330 and the secondary cooling channel 370 are nested. Nesting means that the primary cooling channel 330 and the secondary cooling channel 370 are formed to fit tightly together, such that the secondary cooling channel 370 at least partially mirrors the primary cooling channel 330. In other words, the secondary cooling channel 370 can have a smaller footprint and fit within the space between the primary cooling channel 330 and the first side 106.

[0077] Furthermore, the outlet 334 of the main cooling channel 330 is shown as having a downstream edge 360 ​​with a rounded corner (F3), while the upstream edge 362 has no rounded corner. Therefore, in the variant as previously described herein, the point 360a located upstream of the downstream edge 360 ​​is where a first distance (D1) is measured from it to the trailing edge 112.

[0078] Although the set of cooling channels 314 shown includes a main cooling channel 330 and a secondary cooling channel 370, any number of cooling channels is conceivable, and there may be one or more. Furthermore, the set of cooling channels 314 can be arranged in a spanwise group, such that each cooling channel shown is part of a spanwise arranged set of cooling channels 314.

[0079] Figure 10 It is along Figure 9A schematic diagram of the main cooling channel 330, taken by line XX. The flow enhancer 392 may be a pin 394 formed in a teardrop shape. Although illustrated as a teardrop shape, the flow enhancer 392 and / or pin 394 may be of any shape, including but not limited to square, circular, and rhomboid, or any combination of shapes. The pins 394 may be evenly distributed in the second portion of the main cooling channel 330. Although illustrated as evenly distributed pins, it should be understood that any placement of the pins 394 is conceivable. The outlet 334 of the main cooling channel 330 may have an aspect ratio less than 1. More specifically, the ratio of the axial (A) to radial (R) direction of the outlet 334 may be between 1:3 and 1:15. It should be understood that the aspect ratio depicted for the outlet 334 may also be applied to all outlets described herein.

[0080] Figure 11 A set of cooling channels 414 is shown according to another aspect of the disclosure discussed herein. The set of cooling channels 414 is substantially similar to the set of cooling channels 114; therefore, identical portions will be indicated by the same numeral increment of 300. It should be understood that the description of the identical portions of the set of cooling channels 114 applies to the set of cooling channels 414 unless otherwise stated. For clarity, dimensions (T), (D1), and (D2) have been removed.

[0081] A set of cooling channels 414 includes a main cooling channel 430 extending between at least one inlet 432 at the cooling duct 118 and an outlet 434 at the outer surface 124. The main cooling channel 430 may be two-part, having a first portion 436 including a supply channel 438 and a second portion 440 including an outlet channel 442. The outlet channel 442 may be straight. An intermediate opening 444 may fluidly connect the supply channel 438 to the outlet channel 442.

[0082] The supply channel 438 may be defined by a curved centerline (CCL) extending between at least one inlet 432 and an intermediate opening 444. In one example, the curved centerline (CCL) may be "S"-shaped and include multiple curves. The curved centerline (CCL) may further include inflection points 496 and may have complex curvatures, such as having different bends, curves, or inflection points extending in three dimensions, for example in the chordal direction, spanwise direction, axial direction, radial direction, circumferential direction, or any combination thereof.

[0083] The second part 440 may also include an impact zone 448. As shown, an impact occurs along the second side 108 at the outer wall 104, causing the second side 108 to cool.

[0084] A set of cooling passages 414 may further include a secondary cooling passage 470. The secondary cooling passage 470 may be a straight cooling passage that discharges to the first side 106. Cooling passages 430 and 470 discharge to the first side 106, but contemplated they may discharge to the second side 108, or both the pressure side 106 and the intake side 108.

[0085] It should be understood that the cooling channels described herein can be located in any part of the airfoil or engine component, such as the trailing edge of the airfoil as described herein. 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. Moreover, the cooling hole geometry can be adapted to other engine components besides the airfoil, such as blades, impellers, struts, shields, or combustor liners in the non-limiting examples.

[0086] Cooling channels and other complex geometries described herein can be formed, for example, through additive manufacturing, while envisioning conventional manufacturing methods. Additive manufacturing (AM) processes build parts layer by layer by 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), machinery, and layered materials. Once a CAD sketch is generated, AM equipment can read data from the CAD file and place or add successive 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, many of which include 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 means to form complex geometries like those described in this article, where such formation by traditional manufacturing methods such as casting or drilling can be challenging, expensive, or time-consuming, and yields low. Further casting can also be achieved by producing the core through additive manufacturing, or by fabricating the core via RMC.

[0087] A method for cooling the airfoil 92 may include flowing cooling fluid through a cooling circuit 128. The method may include flowing cooling fluid (C) through a cooling conduit 118 and delivering the cooling fluid (C) to a set of cooling channels 114. Upon receiving the cooling fluid (C), the method may include flowing the cooling fluid (C) through a main cooling channel 130 and discharging the cooling fluid along the outer surface 124 near the trailing edge 112.

[0088] The method may further include allowing cooling fluid to flow through a first portion 136 including a supply passage 138 and then through a second portion 140 including an outlet passage 142, wherein the supply passage 138 is fluidly connected to the outlet passage 142 at an intermediate opening 144.

[0089] The method may further include directing the cooling fluid (C) along a curved channel and redirecting the cooling fluid (C) at a first deflection 146. The cooling fluid (C) may then impinge on a portion of the outlet channel 142 opposite to the intermediate opening 144. As described herein, this deflection may be directed toward a first side 106 or a second side 108. The method may include cooling the corresponding first side 106 or second side 108.

[0090] The method may include cleaning the cooling fluid (C) with a bag 150 before the remaining portion of the cooling fluid (C) flows through the outlet channel 142.

[0091] The method may further include redirecting the cooling fluid at a second turn 152 of less than 90 degrees. As described herein, discharge of the cooling fluid (C) may include discharging the cooling fluid (C) at a location upstream of the trailing edge 112.

[0092] Further, as described herein, the method includes allowing a portion of the cooling fluid (C) to flow through a secondary cooling channel 170.

[0093] The dimensions described in this paper minimize the outlet opening and the thickness near the trailing edge. A smaller outlet opening improves film cooling performance at the trailing edge. Minimal thickness increases aerodynamic efficiency associated with engine components. These adjustments together directly affect the stability of engine components, and more specifically, the stability of the airfoil at the trailing edge by increasing the strength of engine components near the trailing edge. This increases the lifespan and durability of engine components. Furthermore, overall engine efficiency is improved, which is beneficial to the environment.

[0094] Furthermore, the cooling channels and concepts described herein provide improved localized cooling, such as improved shock cooling. Additionally, the diffuser grooves in the outlet channel 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 may necessitate less bleed air. The reduced amount of cooling air required can improve engine efficiency and reduce specific fuel consumption. Improved film cooling can provide higher operating temperatures, which can improve engine efficiency, as well as extend component life and reduce maintenance.

[0095] 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.

[0096] Within the scope not yet described, different features and structures of the various aspects may be combined or substituted for each other as needed. The omission of a feature in all examples is not intended to imply that it cannot be described in this way, but rather is done for the sake of brevity. Therefore, various features of different aspects may be mixed and matched as needed to form new aspects, whether or not the new aspects are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure.

[0097] This written description uses examples to illustrate the aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice the disclosed aspects, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of the 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.

[0098] Further aspects of this disclosure are provided by the subject matter of the following provisions:

[0099] 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 over which the combustion airflow flows, the outer surface extending between a leading edge and a trailing edge to define a first side and a second side in a chordal direction, wherein the wall has a thickness “T” near the trailing edge; at least one cooling duct located in the interior and fluidly coupled to the cooling airflow; a main cooling channel having at least one inlet fluidly coupled to the cooling duct, a main outlet on the outer surface, and a channel connecting the inlet to the outlet, wherein the main outlet has a downstream point spaced from the trailing edge by a first distance D1 and an upstream point spaced from the trailing edge by a second distance D2, wherein the thickness T is greater than or equal to the difference between the first distance D1 and the second distance D2 (T≥(D2-D1)).

[0100] The engine component according to any one of the foregoing clauses, wherein the first distance is greater than or equal to half of the thickness (D1≥(T / 2)).

[0101] The engine component according to any one of the foregoing clauses, wherein the second distance is greater than or equal to the thickness, and the second distance is less than or equal to five times the thickness (T≤D2≤5*T).

[0102] The engine component according to any one of the foregoing clauses, wherein the main cooling passage includes a first portion extending between the inlet and the impact zone and a second portion extending between the impact zone and the main outlet.

[0103] The engine component according to any one of the foregoing clauses, wherein the first portion has a curved centerline.

[0104] The engine component according to any one of the foregoing clauses, wherein the center line of the curve defines a first steer of more than 90 degrees, the first steer terminating at the impact zone.

[0105] The engine component according to any one of the foregoing clauses, wherein the second portion has a first centerline extending from the impact zone toward the trailing edge and a second centerline extending from the main outlet toward the first centerline to define a second steering.

[0106] The engine component according to any one of the foregoing clauses, wherein the second steering angle is less than 90 degrees.

[0107] The engine component according to any one of the foregoing clauses further includes a second cooling passage nested with the main cooling passage near the trailing edge, and having a second outlet upstream of the main outlet.

[0108] The engine component according to any one of the foregoing clauses, wherein the second cooling passage includes an outlet passage having a third centerline extending substantially parallel to the first centerline.

[0109] The engine component according to any one of the foregoing clauses, wherein the sum of the lengths of the first centerline and the second centerline is greater than the third centerline.

[0110] The engine component according to any one of the foregoing clauses, wherein the first portion terminates at the intermediate opening in the impact zone.

[0111] The engine component according to any one of the preceding clauses, wherein the second part includes an outlet passage defining a width (A), and the intermediate opening defining a width (B), wherein the ratio of A:B is less than 3 (A:B<3).

[0112] The engine component according to any one of the foregoing clauses, wherein the intermediate opening is a plurality of openings.

[0113] The engine component according to any one of the preceding clauses, wherein the second part includes an outlet passage with a defined width (A), each of the plurality of openings having a defined diameter (D), and the ratio of the width (A) to the number of the plurality of openings (N) multiplied by the diameter (D) is less than 4 (A:(N*D)<4).

[0114] The engine component according to any one of the foregoing clauses, wherein the second part includes at least one flow enhancer.

[0115] The engine component according to any one of the foregoing clauses, wherein the second part includes a diffusion section.

[0116] The engine component according to any one of the foregoing clauses further includes a second cooling passage, the second cooling passage being adjacent to the trailing edge and having a second outlet upstream of the main outlet.

[0117] The engine component according to any one of the foregoing clauses, wherein the second cooling passage comprises a straight cooling passage.

[0118] The engine component according to any one of the foregoing clauses, wherein the at least one inlet is a plurality of inlets.

[0119] An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising: a wall defining an interior and having an outer surface over which the combustion airflow flows, the outer surface extending between a leading edge and a trailing edge to define a pressure side and an intake side in a chordal direction, wherein the wall has a thickness “T” near the trailing edge; at least one cooling duct located in the interior and fluidly coupled to the cooling airflow; a main cooling channel having at least one inlet fluidly coupled to the cooling duct, a main outlet on the outer surface, a channel connecting the at least one inlet to the main outlet, and an impact zone located within the channel between the at least one inlet and the main outlet, wherein the impact zone separates the channel into a first portion and a second portion, the first portion having a curved centerline extending between the at least one inlet and the impact zone, and the second portion having a diffusion section extending between the impact zone and the main outlet.

[0120] According to any one of the preceding clauses, the airfoil wherein the centerline of the curve defines a first directional change of more than 90 degrees, the first directional change terminating at the impact zone.

[0121] According to any one of the preceding clauses, the airfoil has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, and the thickness T is greater than or equal to the difference between the first distance and the second distance (T≥(D2-D1)).

[0122] According to any one of the preceding clauses, the airfoil has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, and the first distance is greater than or equal to half of the thickness (D1≥(T / 2)).

[0123] According to any one of the foregoing clauses, the main outlet has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, and the second distance is greater than or equal to the thickness and less than or equal to five times the thickness (T≤D2≤5*T).

[0124] According to any one of the foregoing clauses, the second portion has a first centerline extending from the impact zone toward the trailing edge and a second centerline extending from the main exit toward the first centerline to define a second steer of less than 90 degrees.

[0125] The airfoil according to any one of the foregoing clauses further includes a second cooling channel extending between a secondary inlet fluidly connected to the at least one cooling duct and a second outlet on the outer surface at a location upstream of the main outlet.

[0126] A method for cooling an airfoil, the method comprising: flowing cooling fluid through a cooling circuit; flowing the cooling fluid through at least one cooling conduit and directing the cooling fluid to a set of cooling channels; receiving the cooling fluid in a main cooling channel; flowing the cooling fluid through the main cooling channel; and discharging the cooling fluid along an outer surface near the trailing edge of the airfoil.

[0127] The method according to any one of the foregoing clauses further includes causing the cooling fluid to flow through a first portion of the main cooling channel, the first portion including a supply channel.

[0128] The method according to any one of the foregoing clauses further includes causing the cooling fluid to flow through a second portion of the main cooling channel, the second portion including the outlet channel.

[0129] The method according to any one of the foregoing clauses further includes causing the cooling fluid to flow from the first portion to the second portion through an intermediate opening.

[0130] The method according to any one of the foregoing clauses further includes causing the cooling fluid to flow along a curved channel and turning the cooling fluid at a first turning point located in the first portion.

[0131] The method according to any one of the foregoing clauses further includes impinging the cooling fluid onto a portion of the outlet channel opposite the intermediate opening.

[0132] The method according to any one of the foregoing clauses further includes cooling the corresponding side near the main cooling channel.

[0133] The method according to any one of the foregoing clauses further includes cleaning the cooling fluid using a bag located in the main cooling channel before allowing the cooling fluid to flow through the remaining portion of the outlet channel.

[0134] The method according to any one of the foregoing clauses further includes discharging the cooling fluid at a location upstream of the trailing edge.

[0135] The method according to any one of the foregoing clauses further includes causing a portion of the cooling fluid to flow through a secondary cooling channel.

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: A wall defining an interior and having an outer surface over which the combustion gas flow is allowed to flow, the outer surface being defined between a leading edge and a trailing edge to define a first side and a second side in a chordal direction, wherein the wall has a thickness T near the trailing edge; At least one cooling duct is located inside the interior and fluidly connected to the cooling airflow; A main cooling channel having at least one inlet fluidly connected to the cooling conduit, a main outlet on the outer surface, and a channel connecting the inlet to the main outlet, the channel defining a first centerline extending in a first direction and a second centerline extending in a second direction different from the first direction, the intersection of the first centerline and the second centerline defining a second deflection, and an impact zone located within the channel upstream of the first deflection between the at least one inlet and the main outlet, wherein the main outlet has a downstream point spaced from the trailing edge by a first distance D1 and an upstream point spaced from the trailing edge by a second distance D2, wherein the thickness T is greater than or equal to the difference (T1) between the first distance D1 and the second distance D2. > (D2-D1)).

2. The engine component according to claim 1, characterized in that, Where the first distance is greater than or equal to half of the thickness (D1) > (T / 2)).

3. The engine component according to claim 1, characterized in that, Wherein the second distance is greater than or equal to the thickness, and the second distance is less than or equal to five times the thickness (T) < D2 < 5*T).

4. The engine component according to claim 1, characterized in that, The main cooling channel includes a first portion extending between the inlet and the impact zone, and a second portion extending between the impact zone and the main outlet.

5. The engine component according to claim 4, characterized in that, The first part has a curve centerline.

6. The engine component according to claim 5, characterized in that, The centerline of the curve defines the first turn of direction at a degree greater than 90 degrees, and the first turn of direction terminates in the impact zone.

7. The engine component according to claim 4, characterized in that, The second steering is downstream of the first steering.

8. The engine component according to claim 7, characterized in that, The second turning angle is less than 90 degrees.

9. The engine component according to any one of claims 1-7, characterized in that, It further includes a second cooling channel nested with the main cooling channel near the trailing edge, and has a second outlet upstream of the main outlet.

10. The engine component according to claim 9, characterized in that, The second cooling channel includes an outlet channel having a third centerline extending substantially parallel to the first centerline.

11. The engine component according to claim 10, characterized in that, The sum of the lengths of the first centerline and the second centerline is greater than that of the third centerline.

12. The engine component according to claim 4, characterized in that, The first part terminates at the middle opening in the impact zone.

13. The engine component according to claim 12, characterized in that, The second part includes an outlet channel with a defined width A, and the intermediate opening has a defined width B, wherein the ratio of A to B is less than 3 (A:B<3).

14. The engine component according to claim 12, characterized in that, The intermediate opening is a plurality of openings.

15. The engine component according to claim 14, characterized in that, The second part includes an outlet channel with a defined width (A), each of the plurality of openings having a defined diameter (D), and the ratio of the width (A) to the number of the plurality of openings (N) multiplied by the diameter (D) is less than 4 (A:(N*D)<4).

16. The engine component according to claim 4, characterized in that, The second part includes at least one flow enhancer.

17. The engine component according to claim 4, characterized in that, The second part includes a diffusion section.

18. The engine component according to any one of claims 12-17, characterized in that, It further includes a second cooling channel, which is located near the trailing edge and has a second outlet upstream of the main outlet.

19. The engine component according to claim 18, characterized in that, The second cooling channel includes a straight cooling channel.

20. The engine component according to any one of claims 1-8, 10-17, characterized in that, The at least one inlet is multiple inlets.

21. An airfoil for a turbine engine, the turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, characterized in that, The airfoil includes: A wall defining an interior and having an outer surface over which the combustion gas flow passes, the outer surface being defined to extend between a leading edge and a trailing edge to define a first side and a second side in a tangential direction, wherein the wall has a thickness "T" near the trailing edge; At least one cooling duct is located inside the interior and fluidly connected to the cooling airflow; A main cooling channel having at least one inlet fluidly connected to the cooling duct, a main outlet on the outer surface, a channel connecting the at least one inlet to the main outlet, and an impact zone within the channel between the at least one inlet and the main outlet, wherein the impact zone divides the channel into a first portion and a second portion, the first portion having a curved centerline extending between the at least one inlet and the impact zone, and the second portion having a diffusion section extending between the impact zone and the main outlet.

22. The airfoil according to claim 21, characterized in that, The centerline of the curve defines a first turn of more than 90 degrees, which terminates at the impact zone.

23. The airfoil according to claim 21, characterized in that, The main outlet has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, and the thickness T is greater than or equal to the difference between the first distance and the second distance (T0). > (D2-D1)).

24. The airfoil according to claim 21, characterized in that, The main outlet has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, wherein the first distance is greater than or equal to half the thickness (D1). > (T / 2)).

25. The airfoil according to claim 21, characterized in that, The main outlet has a downstream point separated from the trailing edge by a first distance D1 and an upstream point separated from the trailing edge by a second distance D2, wherein the second distance is greater than or equal to the thickness and less than or equal to five times the thickness (T). < D2 < 5*T).

26. The airfoil according to claim 21, characterized in that, The second portion has a first centerline extending from the impact zone toward the trailing edge and a second centerline extending from the main outlet toward the first centerline to define a second velocity of less than 90 degrees.

27. The airfoil according to any one of claims 21-26, characterized in that, It further includes a second cooling channel that extends between a secondary inlet fluidly connected to the at least one cooling duct and a second outlet on the outer surface located upstream of the main outlet.

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