Patent Publication Number: US-11639664-B2

Title: Turbine engine airfoil

Description:
CROSS-REFERENCE TO RELATED APPLICATION(S) 
     This application is a continuation of U.S. application Ser. No. 16/929,936, filed Jul. 15, 2020, currently allowed, which is a continuation of U.S. patent application Ser. No. 16/223,808, filed Dec. 18, 2018, now U.S. Pat. No. 10,767,492, each of which is incorporated herein by reference in its entirety. 
    
    
     BACKGROUND 
     Turbine engines, and particularly gas or combustion turbine engines, are rotary engines that extract energy from a flow of pressurized combusted gases passing through the engine onto rotating turbine blades. 
     Turbine engines are often designed to operate at high temperatures to improve engine efficiency. It can be beneficial to provide cooling measures for engine components such as airfoils in the high-temperature environment, where such cooling measures can reduce material wear on these components and provide for increased structural stability during engine operation. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       In the drawings: 
         FIG.  1    is a schematic cross-sectional diagram of a turbine engine for an aircraft. 
         FIG.  2    is a perspective view of a component that can be utilized in the turbine engine of  FIG.  1    in the form of an airfoil including a plexus of cooling passages according to various aspects described herein. 
         FIG.  3 A  is a cross-sectional view of the airfoil of  FIG.  2    along line illustrating an intersection in the plexus. 
         FIG.  3 B  is a schematic view of the intersection of  FIG.  3 A . 
         FIG.  4    is a perspective view of a portion of the airfoil of  FIG.  2    illustrating another intersection in the plexus. 
         FIG.  5    is a side cross-sectional view of a cooling passage in the airfoil of  FIG.  2    including an airflow modifier. 
         FIG.  6    is a side cross-sectional view of another cooling passage in the airfoil of  FIG.  2    including another airflow modifier. 
         FIG.  7    is a side cross-sectional view of another cooling passage in the airfoil of  FIG.  2    including another airflow modifier. 
         FIG.  8 A  is a top cross-sectional view of the cooling passage and airflow modifier of  FIG.  7    in a first configuration. 
         FIG.  8 B  is a top cross-sectional view of the cooling passage and airflow modifier of  FIG.  7    in a second configuration. 
         FIG.  9    is a sectional view of another plexus of cooling passages that can be utilized in the airfoil of  FIG.  2   . 
         FIG.  10    is a sectional view of another plexus of cooling passages that can be utilized in the airfoil of  FIG.  2   . 
         FIG.  11    is a sectional view of another plexus of cooling passages that can be utilized in the airfoil of  FIG.  2   . 
         FIG.  12    is a perspective view of another component that can be utilized in the turbine engine of  FIG.  1    in the form of another airfoil including at least one plexus of cooling passages according to various aspects described herein. 
         FIG.  13    is another perspective view of the airfoil of  FIG.  12   . 
     
    
    
     DETAILED DESCRIPTION 
     Aspects of the present disclosure are directed to a cooled component. For the purposes of description, the cooled component will be described as a cooled turbine engine component, such as a cooled airfoil. It will be understood that the disclosure may have general applicability for any engine component, including turbines and compressors and non-airfoil engine components, as well as in non-aircraft applications, such as other mobile applications and non-mobile industrial, commercial, and residential applications. 
     As used herein, the term “forward” or “upstream” refers to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component. The term “aft” or “downstream” used in conjunction with “forward” or “upstream” refers to a direction toward the rear or outlet of the engine or being relatively closer to the engine outlet as compared to another component. 
     As used herein, “a set” can include any number of the respectively described elements, including only one element. Additionally, the terms “radial” or “radially” as used herein refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference. 
     All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader&#39;s understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosure. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate members between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to one another. The exemplary drawings are for purposes of illustration only and the dimensions, positions, order and relative sizes reflected in the drawings attached hereto can vary. 
       FIG.  1    is a schematic cross-sectional diagram of a gas turbine engine  10  for an aircraft. The engine  10  has a generally longitudinally extending axis or centerline  12  extending forward  14  to aft  16 . The engine  10  includes, in downstream serial flow relationship, a fan section  18  including a fan  20 , a compressor section  22  including a booster 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 a HP turbine  34 , and a LP turbine  36 , and an exhaust section  38 . 
     The fan section  18  includes a fan casing  40  surrounding the fan  20 . The fan  20  includes a plurality of fan blades  42  disposed radially about the centerline  12 . The HP compressor  26 , the combustor  30 , and the HP turbine  34  form a core  44  of the engine  10 , which generates combustion gases. The core  44  is surrounded by core casing  46 , which can be coupled with the fan casing  40 . 
     A HP shaft or spool  48  disposed coaxially about the centerline  12  of the engine  10  drivingly connects the HP turbine  34  to the HP compressor  26 . A LP shaft or spool  50 , which is disposed coaxially about the centerline  12  of the engine  10  within the larger diameter annular HP spool  48 , drivingly connects the LP turbine  36  to the LP compressor  24  and fan  20 . The spools  48 ,  50  are rotatable about the engine centerline and couple to a plurality of rotatable elements, which can collectively define a rotor  51 . 
     The LP compressor  24  and the HP compressor  26  respectively include a plurality of compressor stages  52 ,  54 , in which a set of compressor blades  56 ,  58  rotate relative to a corresponding set of static compressor vanes  60 ,  62  to compress or pressurize the stream of fluid passing through the stage. In a single compressor stage  52 ,  54 , multiple compressor blades  56 ,  58  can be provided in a ring and can extend radially outwardly relative to the centerline  12 , from a blade platform to a blade tip, while the corresponding static compressor vanes  60 ,  62  are positioned upstream of and adjacent to the rotating blades  56 ,  58 . It is noted that the number of blades, vanes, and compressor stages shown in  FIG.  1    were selected for illustrative purposes only, and that other numbers are possible. 
     The blades  56 ,  58  for a stage of the compressor can be mounted to (or integral to) a disk  61 , which is mounted to the corresponding one of the HP and LP spools  48 ,  50 . The vanes  60 ,  62  for a stage of the compressor can be mounted to the core casing  46  in a circumferential arrangement. 
     The HP turbine  34  and the LP turbine  36  respectively include a plurality of turbine stages  64 ,  66 , in which a set of turbine blades  68 ,  70  are rotated relative to a corresponding set of static turbine vanes  72 ,  74  (also called a nozzle) to extract energy from the stream of fluid passing through the stage. In a single turbine stage  64 ,  66 , multiple turbine blades  68 ,  70  can be provided in a ring and can extend radially outwardly relative to the centerline  12  while the corresponding static turbine vanes  72 ,  74  are positioned upstream of and adjacent to the rotating blades  68 ,  70 . It is noted that the number of blades, vanes, and turbine stages shown in  FIG.  1    were selected for illustrative purposes only, and that other numbers are possible. 
     The blades  68 ,  70  for a stage of the turbine can be mounted to a disk  71 , which is mounted to the corresponding one of the HP and LP spools  48 ,  50 . The vanes  72 ,  74  for a stage of the compressor can be mounted to the core casing  46  in a circumferential arrangement. 
     Complementary to the rotor portion, the stationary portions of the engine  10 , such as the static vanes  60 ,  62 ,  72 ,  74  among the compressor and turbine section  22 ,  32  are also referred to individually or collectively as a stator  63 . As such, the stator  63  can refer to the combination of non-rotating elements throughout the engine  10 . 
     In operation, the airflow exiting the fan section  18  is split such that a portion of the airflow is channeled into the LP compressor  24 , which then supplies pressurized air  76  to the HP compressor  26 , which further pressurizes the air. The pressurized air  76  from the HP compressor  26  is mixed with fuel in the combustor  30  and ignited, thereby generating combustion gases. Some work is extracted from these gases by the HP turbine  34 , which drives the HP compressor  26 . The combustion gases are discharged into the LP turbine  36 , which extracts additional work to drive the LP compressor  24 , and the exhaust gas is ultimately discharged from the engine  10  via the exhaust section  38 . The driving of the LP turbine  36  drives the LP spool  50  to rotate the fan  20  and the LP compressor  24 . 
     A portion of the pressurized airflow  76  can be drawn from the compressor section  22  as bleed air  77 . The bleed air  77  can be drawn from the pressurized airflow  76  and provided to engine components requiring cooling. The temperature of pressurized airflow  76  entering the combustor  30  is significantly increased. As such, cooling provided by the bleed air  77  is necessary for operating of such engine components in the heightened temperature environments. 
     A remaining portion of the airflow  78  bypasses the LP compressor  24  and engine core  44  and exits the engine assembly  10  through a stationary vane row, and more particularly an outlet guide vane assembly  80 , comprising a plurality of airfoil guide vanes  82 , at the fan exhaust side  84 . More specifically, a circumferential row of radially extending airfoil guide vanes  82  are utilized adjacent the fan section  18  to exert some directional control of the airflow  78 . 
     Some of the air supplied by the fan  20  can bypass the engine core  44  and be used for cooling of portions, especially hot portions, of the engine  10 , and/or used to cool or power other aspects of the aircraft. In the context of a turbine engine, the hot portions of the engine are normally downstream of the combustor  30 , especially the turbine section  32 , with the HP turbine  34  being the hottest portion as it is directly downstream of the combustion section  28 . Other sources of cooling fluid can be, but are not limited to, fluid discharged from the LP compressor  24  or the HP compressor  26 . 
     Referring now to  FIG.  2   , a cooled component in the form of an airfoil assembly  95  is shown that can be utilized in the turbine engine  10  of  FIG.  1   . The airfoil assembly  95  includes an airfoil  100  that can be any airfoil such as a blade or vane in the fan section  18 , compressor section  22  or turbine section  32  as desired. It will be understood that the cooled component can also be in the form of any suitable component within the turbine engine, including a shroud, hanger, strut, platform, inner band, or outer band, in non-limiting examples. 
     The airfoil  100  includes an outer wall  102  (shown in phantom line) defining an exterior surface  103  and bounding an interior  104 . The outer wall  102  defines a pressure side  106  and a suction side  108 , and a cross-wise direction R can be defined therebetween. The outer wall  102  also extends axially between a leading edge  110  and a trailing edge  112  to define a chord-wise direction C, and also extends radially between a root  114  and a tip  116  to define a span-wise direction S. 
     The airfoil assembly  95  can also include a platform  118  (shown in phantom line) coupled to the airfoil  100  at the root  114 . In one example the airfoil  100  is in the form of a blade, such as the HP turbine blade  68  of  FIG.  1   , extending from a dovetail  117  (in phantom line). In such a case, the platform  118  can form at least a portion of the dovetail  117 . In another example, the airfoil  100  can be in the form of a vane, such as the LP turbine vane  72 , and the platform  118  can form at least a portion of an inner band or an outer band (not shown) coupled to the root  114 . 
     The dovetail  117  can be configured to mount to the turbine rotor disk  71  on the engine  10 . The dovetail  117  can comprise at least one inlet passage  119 , exemplarily shown as three inlet passages  119 , each extending through the dovetail  117  to provide internal fluid communication with the airfoil  100 . It should be appreciated that the dovetail  117  is shown in cross-section, such that the inlet passages  119  are housed within the body of the dovetail  117 . 
     The airfoil  100  further includes at least one cooling air supply conduit  125  (also referred to herein as a “conduit  125 ”). The conduit  125  includes at least one three-dimensional plexus  120  (also referred to herein as “plexus  120 ”) of fluidly interconnected cooling passages  122 . The plexus  120  is illustrated schematically in solid line with “flat” passages and regions. It should be understood that the plexus  120  represents three-dimensional open spaces or voids inside of the airfoil  100 . The plexus  120  can extend between at least one inlet  124  fluidly coupled to a source of cooling air within the airfoil interior  104 , such as the at least one inlet passage  119 , and at least one outlet  126  fluidly coupled to the plexus  120 . The outlets  126  can be located at any or all of the leading edge  110 , trailing edge  112 , root  114 , tip  116 , or platform  118 . The inlet  124  can include a slot, hole, or combination as desired. It is contemplated that the inlet  124  can receive cooling fluid from any desired location within the airfoil assembly  95 , such as an interior passage of the platform  118 , or a central supply passage (not shown) within the airfoil interior  104 . In addition, while the plexus  120  is illustrated proximate the trailing edge  112  of the airfoil  100 , the plexus  120  can extend to any portion of the airfoil  100  including the leading edge  110 , root  114 , tip  116 , or elsewhere along the pressure side  106  or suction side  108 . Multiple plexuses can also be provided within the airfoil  100 . 
     It is contemplated that the cooling passages  122  of the plexus  120  can furcate, including recursively furcating, at least twice in the downstream direction indicated by the arrow  123 . For example, the recursively-furcated plexus  120  can define a fractal pattern. In addition, the conduit  125  can further include a non-furcated passage or non-furcated portion  121  upstream of the plexus  120 . In the illustrated example, a plurality of outlets  126  are located on the exterior surface  103  extending along the trailing edge  112 . The outlets  126  can be located along the leading edge  110 , trailing edge  112 , pressure side  106 , or suction side  108 . The outlets  126  can also be fluidly coupled to the plexus  120 . It should be understood that the outlets  126  can include in-line diffusers, diffusing slots, film holes, ejection holes, channels, and the like, or combinations thereof. The outlets  126  can be located at any suitable location including the leading edge  110 , root  114 , tip  116 , or elsewhere along the pressure side  106  or suction side  108 . Outlets  126  can also be formed in other portions of the airfoil assembly  95 , such as the platform  118 , and fluidly coupled to the plexus  120 . 
     The three-dimensional plexus  120  of cooling passages  122  can be formed using a variety of methods, including additive manufacturing, casting, electroforming, or direct metal laser melting, in non-limiting examples. It is contemplated that the airfoil  100  having the plexus  120  can be an additively manufactured component. As used herein, an “additively manufactured” component will refer to a component formed by an additive manufacturing (AM) process, wherein the component is built layer-by-layer by successive deposition of material. AM is an appropriate name to describe the technologies that build 3D objects by adding layer-upon-layer of material, whether the material is plastic or metal. AM technologies can utilize a computer, 3D modeling software (Computer Aided Design or CAD), machine equipment, and layering material. Once a CAD sketch is produced, the AM equipment can read in data from the CAD file and lay down or add successive layers of liquid, powder, sheet material or other material, in a layer-upon-layer fashion to fabricate a 3D object. It should be understood that the term “additive manufacturing” encompasses many technologies including subsets like 3D Printing, Rapid Prototyping (RP), Direct Digital Manufacturing (DDM), layered manufacturing and additive fabrication. Non-limiting examples of additive manufacturing that can be utilized to form an additively-manufactured component include powder bed fusion, vat photopolymerization, binder jetting, material extrusion, directed energy deposition, material jetting, or sheet lamination. In addition, the plexus  120  can include any desired geometric profile, including a fractal geometric profile, an axial serpentine profile, or a radial serpentine profile. 
       FIG.  3 A  illustrates the airfoil  100  in cross-section with the plexus  120  being shown in further detail. It is contemplated that the plexus  120  can extend in the span-wise direction S (as seen in  FIG.  2   ), and can also extend in the chord-wise direction C as well as the cross-wise direction R. For example, the plexus  120  can have an overall profile or form similar to that of a vein plexus or network in a body. The plexus  120  can include an in-wall cooling passage extending through the outer wall  102 , a near-wall cooling passage, or other cooling structures suitable for the airfoil  100 . With reference to  FIGS.  2  and  3 A , it should be understood that each line notated as a cooling passage  122  in  FIG.  3 A  represents a plurality of cooling passages  122  “stacked” in a radially inward or outward manner as seen in  FIG.  2   . 
     The plexus  120  can include multiple intersections between the fluidly interconnected cooling passages  122 . It should also be understood that in other cross-sectional views through the airfoil  100  radially inward or outward from the line the plexus  120  can have other appearances, branches, or intersections. It can be appreciated that the three-dimensional plexus  120  having multiple interconnected cooling passages  122  can be utilized for a tailored supply of cooling air to a variety of locations within the interior or exterior of the airfoil  100 . 
     In the illustrated example, the airfoil  100  includes a first planar set  131 , a second planar set  132 , and a third planar set  133  of cooling passages  122 . As used herein, a “planar set” of cooling passages can refer to any set of cooling passages that extends or branches in two dimensions that define a plane. In another example, a “planar set” of cooling passages can refer to any set of cooling passages that forms a three-dimensional structure that extends in two dimensions and includes a thickness in a third dimension. In still another example, a “planar set” of cooling passages can refer to any set of cooling passages having a first local region extending in two dimensions that define a first plane, and having a second local region that extending in two dimensions that define a second plane different from the first plane, such as an S-shaped planar set of cooling passages in one example. Put another way, “planar” as used herein can refer to a structure that is locally “flat” or two-dimensional over a given region but can include an overall curvature, such as a curved plane, including a curved plane structure with a three-dimensional thickness. The planar sets of cooling passage can include tip-wise-oriented passages, chord-wise-oriented passages, or span-wise-oriented passages, or any combination thereof. 
     The first, second, and third planar sets  131 ,  132 ,  133  are illustrated as being fluidly coupled to one another at a first intersection  135 . In addition, a first set of outlets  126 A can fluidly couple to the first planar set  131 , and a second set of outlets  126 B can fluidly couple to the second planar set  132  as shown. The airfoil  100  can also include an in-wall cooling passage  137  extending through the outer wall  102 , as shown at the suction side  108 . The in-wall cooling passage  137  can fluidly couple the second planar set  132  to the second set of outlets  126 B. It is contemplated that the in-wall cooling passage  137  can be a non-furcating cooling passage. It should also be understood that the airfoil  100  can include other in-wall cooling passages (not shown) fluidly coupled to the plexus  120 . 
     In addition, a second intersection  145  illustrates that the second and third planar sets  132 ,  133  can fluidly couple to a fourth planar set  134  of cooling passages  122 . The fourth planar set  134  is illustrated along a plane partially extending along the camber line  107  of the airfoil  100 , and it is also contemplated that the fourth set  134  can be formed in any direction. 
     A source  150  of cooling air can be positioned within the airfoil  100 . The source  150  is illustrated as a radial cooling passage, and it should be understood that the source  150  of cooling air can have a variety of orientations or shapes, and can be positioned within the airfoil  100  or elsewhere in the airfoil assembly  95  including the platform  118  as desired. The plexus  120  can fluidly couple to the source  150  of cooling air via the at least one inlet  124  as shown. 
       FIG.  3 B  illustrates a zoomed view  140  of the plexus  120  with the first intersection  135  of the first, second, and third planar sets  131 ,  132 ,  133  of cooling passages  122 . The first planar set  131  can extend along a first plane  141 , which is seen in an edge-on view. The second planar set  132  can extend along a second plane  142  (seen edge-on) different from the first plane  141 , and the third planar set  133  extends along a third plane  143  (seen edge-on) unaligned with the first and second planes  141 ,  142 . In the illustrated example, the first plane  141  partially extends toward the chord-wise direction C, the second plane  142  partially extends in the cross-wise direction R toward the suction side  108 , and the third plane  143  partially extends in the cross-wise direction R toward the pressure side  106 . 
     Referring now to  FIG.  4   , a portion  128  ( FIG.  2   ) of the plexus  120  of cooling passages is shown along the trailing edge  112  and platform  118 , where the third intersection  152  is located at the root  114  of the airfoil  100 . The span-wise direction S and the chord-wise direction C are shown, as well as directions toward the pressure side  106  and suction side  108 . It should be understood that in the illustrated example wherein the airfoil  100  comprises a blade, the root  114  is adjacent the platform  118  coupled to the blade. In an alternate example wherein the airfoil  100  comprises a vane, the root  114  can be adjacent an inner or outer band (not shown) coupled to the vane. 
     In the illustrated example, a third intersection  152  fluidly couples a fourth planar set  154  of cooling passages along the span-wise direction to a fifth planar set  155  and a sixth planar set  156  of cooling passages. The fifth planar set  155  defines a fifth plane  157  and branches from the third intersection  152  toward the suction side  108  and platform  118 . The sixth planar set  156  defines a sixth plane  158  and branches from the third intersection  152  toward the pressure side  106  and platform  118 . Arrows illustrate cooling air flowing through the plexus  120  and exiting via the outlets  126 . Some of the outlets  126  can be located along the trailing edge  112 , and some of the outlets  126  can also be located within the platform  118 . In this manner, the three-dimensional plexus  120  of fluidly interconnected cooling passages  122  can extend in first, second, and third directions, such as the span-wise direction S, the chord-wise direction C, and the cross-wise direction R. 
     Turning to  FIG.  5   , an exemplary sectional view of the airfoil  100  is shown with the span-wise and chord-wise directions S, C illustrated. It is further contemplated that an airflow modifier  160  can be included within at least one cooling passage  122  of the plexus  120 . The airflow modifier  160  can be configured to redirect, speed up, slow down, turbulate, mix, or smooth an airflow (illustrated with arrows) within the at least one cooling passage  122 . One exemplary airflow modifier  160  can include a turbulator. As used herein, a “turbulator” will refer to any component that can generate a turbulent airflow, including dimples, pins, or impingement zones, in non-limiting examples. Other non-limiting examples of airflow modifiers  160  that can be utilized include surface roughness, variable passage width, or scalloped wall portions. 
     In one example, the airflow modifier  160  includes an impingement zone  161  in combination with surface roughness  162  at an intersection between fluidly coupled cooling passages  122 . Another airflow modifier  160  can be in the form of a narrowed portion  163  of a cooling passage  122 ; it can be appreciated that such narrowing of a cooling passage  122  can cause an airflow to increase in speed through the portion  163 . In still another example, the airflow modifier  160  can include a first width  164  in one cooling passage  122 , and a second width  165  larger than the first width  164  in another cooling passage  122 . 
       FIG.  6    illustrates another exemplary sectional view of the airfoil  100 , with the chord-wise direction C and cross-wise direction R shown. It should be understood that the sectional view of  FIG.  6    is in a direction perpendicular to that of  FIG.  5   . 
     The airflow modifier  160  can further include a scalloped portion  166 , where adjacent concave and convex surfaces can cause swirling or turbulence of a local airflow through the cooling passage  122 . In still another example, the airflow modifier  160  can also include a beveled portion  167  with a sharp corner. 
     Turning to  FIG.  7   , a top cross-sectional view of another cooling conduit  125 A within the airfoil  100  is shown. The cooling conduit  125 A also includes an impingement zone  161 A with an impingement chamber  161 C having at least one inlet passage  180  and at least one outlet passage  181  which is illustrated as being furcated into two outlet passages  181 . A common junction  186  can be defined at an intersection of the inlet passage  180  and outlet passages  181 . The cooling conduit  125 A can, in a non-limiting example, form part of the plexus  120  wherein the inlet passage  180  and outlet passages  180  can form cooling passages  122  within the plexus  120 . 
     A turbulator  168  can be positioned within the impingement chamber  161 C at the common junction  186 . The turbulator  168  can be positioned along a center streamline direction  189  of the inlet passage  180  as shown. For example, the turbulator  168  can be spaced from a rear wall  187  of the impingement chamber  161 C to define a rear portion  188  of the impingement chamber  161 C. 
     The turbulator  168  is illustrated as a pin in the example of  FIG.  7   . It should be understood that the turbulator  168  can have any suitable geometry or form, including a cylindrical pin, a flattened fin, a fin, an airfoil, a chevron, or an irregular geometric profile. The turbulator  168  can also define a surface area  168 S and first and second surfaces  169 A,  169 B. The impingement chamber  161 C can also define a chamber surface area  161 S that includes the surface area  168 S. In addition, the inlet passage  180  can define an inlet surface area  180 S. It is contemplated that the chamber surface area  161 S can be greater than the inlet surface area  180 S. For example, a surface area of the cooling conduit  125 A can increase when moving in the center streamline direction  189 , e.g. when moving from the inlet passage  180  to the impingement chamber  161 C. In another example, the chamber surface area  161 S can be greater than the inlet surface area  180 S or an outlet surface area  181 S defined by the at least one outlet passage  181 . 
     It is further contemplated that at least one of the turbulator  168  or the impingement chamber  161 C can form an airflow modifier  160  within the cooling conduit  125 A. Optionally, other airflow modifiers such as a turbulator, scalloped portion, narrowed portion, surface roughness, or beveled portion described above can also be included in the cooling conduit  125 A. 
       FIG.  8 A  illustrates a first configuration of the cooling conduit  125 A in a view perpendicular to that of  FIG.  7   . In the illustrated example, the turbulator  168  extends fully across the extent of the impingement chamber  161 C in a direction unaligned with, e.g. perpendicular to, the center streamline direction  189 . Cooling air flowing through the cooling conduit  125 A in this configuration can impinge the turbulator  168 , generate a turbulent airflow along the rear wall  187 , and transfer heat through the turbulator  168  to multiple walls of the impingement chamber  161 C to provide cooling. 
       FIG.  8 B  illustrates a second configuration of the cooling conduit  125 A in a view perpendicular to that of  FIG.  7   . In the illustrated example, the turbulator  168  can extend partially across the impingement chamber  161 C in a direction unaligned with, e.g. perpendicular to, the center streamline direction  189  as shown. Cooling air flowing through the cooling conduit  125 A in this configuration can impinge the turbulator  168  as well as flow multiple surfaces such as the first and second surfaces  169 A,  169 B of the turbulator  168 , thereby transferring heat through the turbulator  168  to one wall of the impingement chamber  161 C. 
     In operation, air flowing through the cooling conduit  125 ,  125 A, including the plexus  120  and cooling passage  122 , can encounter or impinge the airflow modifier  160 . The airflow modifier  160  can causing swirling or other turbulence of a local airflow, such as the scalloped portion  166  or impingement zones  161 ,  161 A with surface roughness  162  or impingement chamber  161 C. The airflow modifier  160  can also be utilized to redirect a local airflow, such as via the beveled portion  167  or rear portion  188  of the impingement chamber  161 C. The airflow modifier  160  can also alter a local airflow speed such as via the narrowed portion  163 . It can also be appreciated that any of the exemplary airflow modifiers can modify one or more airflow characteristics such as speed, velocity, swirl, or turbulence, and that a given airflow modifier may also modify multiple airflow characteristics within the cooling conduit or passage. 
     It will be understood that aspects of the airflow modifiers  160  described above can be combined or tailored to any desired portion of the three-dimensional plexus  120 , as well as in any desired direction within the airfoil  100 . The airflow modifiers  160  can be oriented to direct or modify airflows moving in the span-wise direction S, chord-wise direction C, cross-wise direction R, or any combination thereof, including in cooling passages not having a three-dimensional plexus. In one non-limiting example, the impingement chamber  161 C can be located within a portion of the plexus  120  forming a near-wall cooling structure, such as in a portion of the plexus  120  located adjacent the pressure side  106  or suction side  108  as shown in the view of  FIG.  3 A . 
     Referring now to  FIG.  9   , another three-dimensional plexus  220  of cooling passages is illustrated that can be utilized in the airfoil  100 . The plexus  220  is similar to the plexus  120 ; therefore, like parts will be identified with like numerals increased by 100, with it being understood that the description of the like parts of the plexus  120  applies to the plexus  220 , unless otherwise noted. 
     For clarity, the plexus  220  is shown without the surrounding airfoil. It should be understood that the plexus  220  can be positioned within an interior of the airfoil, such as that shown for the plexus  120  within the airfoil  100  (see  FIG.  2   ). In addition, it should be understood that although illustrated with “flat” passages and regions, the plexus  220  represents three-dimensional open spaces or voids within the airfoil  100 . The span-wise and chord-wise directions S, C are illustrated for reference. It should be understood that the plexus  220  can be oriented in any suitable direction within the airfoil  100 , including along any combination of the span-wise direction S, chord-wise direction C, or cross-wise direction R. 
     The plexus  220  of cooling passages  222  can include at least one inlet  224  wherein cooling air can be supplied to the plexus  220 . The inlet  224  is illustrated with a combination of a slot and inlet holes. The plexus  220  also includes a plurality of outlets  226  that can be positioned along a trailing edge of the airfoil. 
     The plexus  220  can include a fractal geometric profile. As used herein, “fractal” will refer to a recursive or self-similar pattern or arrangement of cooling passages. More specifically, a first group  280  of linear cooling passages  222  along a first chord-wise position  281  can have a first passage size  282 . A second group  283  of linear cooling passages  222  along a second chord-wise position  284  downstream of the first chord-wise position  281 , have a second passage size  285  that can be smaller than the first passage size  282 . It is contemplated that a passage size of the linear cooling passages  222 , or of groups of linear cooling passages  222 , can decrease between the first chord-wise position  281  and the second chord-wise position  284 . Further, it can be appreciated that the second group  283  has a similar appearance or pattern to the first group  280  on a differing size scale. It should be understood that the plexus  220  can also extend in a direction between a pressure and suction side of the airfoil, including groups of linear cooling passages having variable passage sizes as desired. In this manner, the plexus  220  can continually recursively furcate in a downstream direction until fluidly connecting to the outlets  226  and can also define a fractal pattern as described above. The plexus  220  can also include a non-expanding cross section that is at least one of constant or reducing in the flow direction, such as the second passage size  285  being smaller than the first passage size  282 . 
     Referring now to  FIG.  10   , another plexus  320  of cooling passages is illustrated that can be utilized in the airfoil  100 . The plexus  320  is similar to the plexus  120 ,  220 ; therefore, like parts will be identified with like numerals further increased by 100, with it being understood that the description of the like parts of the plexus  120 ,  220  applies to the plexus  320 , unless otherwise noted. 
     For clarity, the plexus  320  is shown without the surrounding airfoil. It should be understood that the plexus  320  can be positioned within an interior of the airfoil, such as that shown for the plexus  120  within the airfoil  100  (see  FIG.  2   ). In addition, it should be understood that although illustrated with “flat” passages and regions, the plexus  320  represents three-dimensional open spaces or voids within the airfoil  100 . The span-wise and chord-wise directions S, C are illustrated for reference. It should be understood that the plexus  320  can be oriented in any suitable direction within the airfoil  100 , including along any combination of the span-wise direction S, chord-wise direction C, or cross-wise direction R. 
     The plexus  320  of cooling passages  322  can include at least one inlet  324 , illustrated as a plurality of inlet holes, wherein cooling air can be supplied to the plexus  320 . The plexus  320  also includes a plurality of outlets  326  that can be positioned along a trailing edge of the airfoil. 
     A cooling passage  322  is shown with an exemplary cooling airflow  390  flowing between the inlet  324  and outlet  326 . One difference is the plexus  320  can include a radial serpentine profile. More specifically, the cooling passage  322  can include a first portion  391  wherein the cooling airflow  390  moves in a downstream chord-wise direction, as well as a second portion  392  offset in the span-wise direction (e.g. radially offset) from the first portion  391  wherein the cooling airflow  390  moves in an upstream chord-wise direction as shown. The cooling passage  322  can further include a third portion  393  wherein the cooling airflow  390  moves in a downstream chord-wise direction and furcates, splits, or divides prior to flowing through multiple outlets  326 . In this manner, the first portion  391 , second portion  392 , and third portion  393  can at least partially define the radial serpentine profile of the plexus  320 . 
     Referring now to  FIG.  11   , another three-dimensional plexus  420  of cooling passages is illustrated that can be utilized in the airfoil  100 . The plexus  420  is similar to the plexus  120 ,  220 ,  320 ; therefore, like parts will be identified with like numerals further increased by 100, with it being understood that the description of the like parts of the plexus  120 ,  220 ,  320  applies to the plexus  420 , unless otherwise noted. 
     For clarity, the plexus  420  is shown without the surrounding airfoil. It should be understood that the plexus  420  can be positioned within an interior of the airfoil, such as that shown for the plexus  120  within the airfoil  100  (see  FIG.  2   ). In addition, it should be understood that although illustrated with “flat” passages and regions, the plexus  220  represents three-dimensional open spaces or voids within the airfoil  100 . The span-wise and chord-wise directions S, C are illustrated for reference. It should be understood that the plexus  420  can be oriented in any suitable direction within the airfoil  100 , including along any combination of the span-wise direction S, chord-wise direction C, or cross-wise direction R. 
     The plexus  420  of cooling passages  422  can include at least one inlet  424 , illustrated as a plurality of inlet holes, wherein cooling air can be supplied to the plexus  420 . The plexus  420  also includes a plurality of outlets  426  that can be positioned along a trailing edge of the airfoil. 
     A cooling passage  422  is shown with an exemplary cooling airflow  490  flowing between the inlet  424  and outlet  426 . One difference is the plexus  420  can include an axial serpentine profile. More specifically, the cooling passage  422  can include a first portion  491  wherein the cooling airflow  490  moves in a downstream chord-wise direction as well as moving radially outward in the span-wise direction. The cooling passage  422  also includes a second portion  492  wherein the cooling airflow  490  continues moving in the downstream chord-wise direction while moving radially inward in the span-wise direction. A third portion  493  fluidly coupled to the second portion  491  divides the cooling airflow  490  prior to flowing through multiple outlets  426 . In this manner, the first, second, and third portions  491 ,  492 ,  493  can at least partially define the axial serpentine profile of the plexus  420 . 
     Optionally, the cooling passage  422  can include a fourth portion  494  providing an additional fluid coupling between the first and second portions  491 ,  492 . Alternately, the fourth portion  494  can provide rigidity or support for the axial-serpentine shaped cooling passage  422  without providing an additional fluid coupling. 
     Turning to  FIG.  12   , another engine component in the form of an airfoil assembly  495  is shown that can be utilized in the turbine engine  10  of  FIG.  1   . The airfoil assembly  495  is similar to the airfoil assembly  95 ; therefore, like parts will be identified with like numerals increased by 400, with it being understood that the description of the like parts of the airfoil assembly  95  applies to the airfoil assembly  495 , except where noted. 
     The airfoil assembly  495  includes an airfoil  500  that can be any airfoil such as a blade or vane in any section of the turbine engine  10 , including the compressor section  22  or turbine section  32  as desired. 
     The airfoil  500  includes an outer wall  502  (shown in phantom line) defining an exterior surface  503  and bounding an interior  504 . The outer wall  502  defines a pressure side  506  and suction side  508  with a cross-wise direction R defined therebetween. The outer wall  502  also extends axially between a leading edge  510  and a trailing edge  512  to define a chord-wise direction C, and also extends radially between a root  514  and a tip  516  to define a span-wise direction S. In addition, the airfoil  500  can extend from a dovetail  517  having at least one inlet passage  519  as shown. 
     The airfoil  500  can include at least one cooling air supply conduit fluidly coupled to at least one passage within the interior  504 . In the illustrated example the airfoil  500  includes first, second, and third cooling air supply conduits  581 ,  582 ,  583 . A trailing edge passage  591  can extend along the trailing edge  512  and fluidly couple to the first supply conduit  581 . A leading edge passage  592  can extend along the leading edge  510  and fluidly couple to the second supply conduit  582 . A tip passage  593  can extend along the tip  516  of the airfoil  500  and fluidly couple to the third supply conduit  583 . 
     The airfoil can also include a plurality of outlets located in the exterior surface  503 . For example, a plurality of trailing edge outlets  596 , leading edge outlets  597 , and tip outlets  598  can be provided in the exterior surface  503  and be fluidly coupled to the trailing edge passage  591 , leading edge passage  592 , and tip passage  593 , respectively. It should be understood that the supply conduits  581 ,  582 ,  583  and passages  591 ,  592 ,  593  and outlets  596 ,  597 ,  598  are exemplary, and the airfoil  500  can include more or fewer supply conduits or passages than those shown. 
     At least one three-dimensional plexus can also be included in the airfoil  500 . In the illustrated example, a first plexus  520 A similar to the plexus  120 ,  220 ,  320 ,  420  is included in the first supply conduit  581  and fluidly coupled to the trailing edge passage  591  and trailing edge outlets  596 . A second plexus  520 B and a third plexus  520 C, both similar to the plexus  120 ,  220 ,  320 ,  420 , are included in the third supply conduit  583 . The second plexus  520 B can be fluidly coupled to the tip passage  593  and tip outlets  598 . The third plexus  520 C can be fluidly coupled to either or both of the first plexus  520 A or tip passage  593 . In addition, the first plexus  520 A can be positioned adjacent the second plexus  520 B in the chord-wise direction C, such as the second plexus  520 B being located upstream of the first plexus  520 A. For clarity, the third plexus  520 C is schematically illustrated in solid outline form. It should be understood that the third plexus  520 C also includes fluidly interconnected cooling passages not shown in this view. It will also be understood that other cooling passages, holes, or outlets not shown can nonetheless be provided in the airfoil  500 . 
     In another example, a surface channel  590  can be provided in the exterior surface  503  of the outer wall  502 , illustrated adjacent the tip  516  of the airfoil  500 . The surface channel  590  can be fluidly coupled to either or both of the second plexus  120 B and the tip outlets  598 . For example, at least some of the tip outlets  598  can be provided in the surface channel  590 . In another example where no tip channel is utilized, the tip outlets  598  can be provided directly in the exterior surface  503 . 
     It is also contemplated that at least one of the cooling air supply conduits can include at least one non-furcated passage  585 . For example, the second supply conduit  582  can include a non-furcated passage  585  which is fluidly coupled to the leading edge passage  592 . In another example, the first supply conduit  581  can include a non-furcated passage  585  which is fluidly coupled to, and located upstream of, the first plexus  520 A. 
     It is also contemplated that at least one of the cooling air supply conduits can be at least partially radially aligned with at least one three-dimensional plexus. In the illustrated example, the first cooling air supply conduit  581  is at least partially radially aligned with the first plexus  520 A, and the third cooling air supply conduit  583  is radially aligned with the second plexus  520 B and third plexus  520 C. 
       FIG.  13    illustrates the airfoil  500  facing the pressure side  506 . In this view, the second plexus  520 B is schematically illustrated in solid outline form, and it should be understood that the second plexus  520 B can include fluidly interconnected cooling passages as shown in  FIG.  13   . It is further contemplated that the second plexus  520 B and third plexus  520 C can be located adjacent one another in the cross-wise direction R, with the second plexus positioned adjacent the pressure side  506  and the third plexus positioned adjacent the suction side  508 . In addition, the second plexus  520 B and third plexus  520 C can be fluidly coupled and optionally supplied by a common inlet passage within the dovetail  517 . Additional tip outlets  598  can be fluidly coupled to the tip passage  593 ; in the illustrated example, the surface channel  590  can be provided on the pressure side  506  ( FIG.  12   ) while the tip outlets  598  can be provided directly on the exterior surface on the suction side  508  ( FIG.  13   ). 
     In operation, cooling air supplied from the dovetail  517  can flow radially outward (e.g. along the span-wise direction S) through the first supply conduit  581 , second supply conduit  582 , and third supply conduit  583 . Cooling air can flow in the span-wise direction S, chord-wise direction C, cross-wise direction R, or any combination thereof, while flowing through at least one three-dimensional plexus within the airfoil  500  before being emitted through at least one outlet on the leading edge  510 , trailing edge  512 , tip  516  or elsewhere on the exterior surface  503 . The cooling air can flow through at least one non-furcated passage  585  prior to flowing through a three-dimensional plexus as described above. 
     In still another example (not shown), multiple plexuses can be provided within the airfoil such that the cooling passages of a first plexus can be interwoven through cooling passages of a second plexus. The first plexus can optionally be fluidly coupled to the second plexus, or the first and second plexus can be supplied with independent sources of cooling air. For example, the first plexus can include a planar set of cooling passages in the span-wise direction and the second plexus can include a planar set of cooling passages in the chord-wise direction, where cooling passages of the first plexus are directed around cooling passages of the second plexus without being fluidly coupled to the second plexus. 
     In another non-limiting example (not shown), at least one plexus can be directly fluidly coupled to outlets in the exterior surface, such as tip outlets, without intervening ejection holes. In such a case, at least one plexus can extend fully to the tip of the airfoil and fluidly couple to the outlets. The lattice portion can also be directly fluidly coupled to other outlets located on the pressure side or suction side of the airfoil, including without intervening ejection holes; including by way of the elongated ejection holes or by directly fluidly coupling to the outlets without such ejection holes. 
     In yet another non-limiting example (not shown), the plexus can further include multiple discrete groups of cooling passages each fluidly supplied by a separate cooling conduit. Each of the multiple discrete groups can include any or all of the impingement zone, lattice portion, or elongated ejection holes. The multiple discrete groups can be fluidly coupled, for example by a single connecting fluid passage, or they can be separated within the airfoil interior. In addition, the multiple discrete groups can form multiple impingement zones arranged radially within the airfoil, such that cooling air supplied from the cooling conduit can impinge a first zone, impinge a second zone, impinge a third zone, and so on, until exiting via a cooling hole outlet. 
     Aspects provide for a method of cooling a turbine engine airfoil, including supplying a cooling fluid through a three-dimensional plexus, such as the plexus  120 ,  220 ,  320 ,  420  of fluidly interconnected cooling passages within the airfoil, and emitting the cooling fluid through at least one outlet. The outlet can be located on any or all of the leading edge, trailing edge, tip, or surface channel as described above. Optionally, the method can include dividing the cooling fluid at an intersection, such as the first intersection  135  of the first planar set  131  of cooling passages extending in the first direction  141  and the second planar set  132  of cooling passages extending in the second direction  142 . Optionally, the method can include recombining the cooling fluid from the first and second planar sets  131 ,  132  at a second intersection  145 . The first direction  141  can be in the cross-wise direction R between the pressure side  106  and the suction side  108  of the airfoil  100 , and the second direction  142  can be along the span-wise direction S or the chord-wise direction C. It is contemplated that any of first, second, and third directions can be in any of the span-wise direction S, the chord-wise direction C, the cross-wise direction R, or any combination of the above. The method can further include impinging the cooling fluid on the impingement zone  161  within a cooling passage  122  of the three-dimensional plexus  120 . In addition, emitting the cooling fluid can further include emitting through multiple outlets, such as the outlets  126  at the trailing edge  112  disposed between multiple concave portions  170  in one of the pressure or suction sides  106 ,  108 . 
     The described structures, such as the various plexuses, provide for a method of cooling an airfoil in a turbine engine, including supplying a cooling fluid through a cooling conduit within an interior of the airfoil. The method also includes flowing the cooling fluid to an impingement chamber located within the cooling conduit, impinging the cooling fluid on a pin located within the impingement chamber, and flowing the cooling fluid from the impingement chamber to at least one outlet passage to cool the airfoil. The cooling fluid can flow to a rear portion of the impingement chamber behind and spaced from the pin as described above, and the cooling fluid can then flow from the impingement chamber to the at least one outlet passage. Optionally, the impingement chamber can be located within a plexus of fluidly interconnected cooling passages as described above. 
     The described structures and methods provide several benefits, including that the ability to split and tailor the three-dimensional plexus of cooling passages can provides specified cooling to multiple airfoil locations as desired. The three-dimensional structure provides for closely following multiple contours within the airfoil, enabling weight reductions, manufacturability improvements, and improved cooling to tailored locations. Tailored geometries such as serpentine or fractal portions, or combinations thereof, within the three-dimensional plexus also provide for localized increase in temperature capability, where stresses or temperature fields lead to higher cooling needs at specific locations on or within the airfoil. Such tailoring can be accomplished by varying a passage size, length, or cross-sectional width, or by branching off portions of the plexus at an intersection to redirect cooling air to needed portions of the airfoil. Improving the cooling performance results in less dedicated cooling flow from the engine, improving engine performance and efficiency. In addition, tailored cooling can reduce component stress and improve the working lifetime of a component, resulting in better engine durability. 
     One benefit of the fractal or furcated geometry is that the use of larger passages transitioning to smaller passages can accomplish the same or improved cooling performance with less supplied air. In addition, larger or upstream passages being radially or axially offset from downstream passages, such as in a serpentine geometric profile, can provide for increased working of the cooling air which can further improve cooling performance. Such fractal, furcated, lattice, or serpentine geometries can spread the cooling air over a greater region of the airfoil or expose a greater surface area of the airfoil interior to the cooling air during operation, which increasing high-temperature cooling performance compared to traditional cooling structures. 
     It can also be appreciated that the use of impingement zones, including the positioning of a pin in an impingement chamber, can provide for increased surface area for cooling of the airfoil. Airflow modifiers can provide for mixing, redirecting, working, or turbulating of the cooling air within the airfoil, including within the three-dimensional plexus, which can improve cooling performance compared to traditional methods of cooling. 
     It can be further appreciated that the use of concave portions at the trailing edge outlets, in combination with the plexus of cooling passages and airflow modifiers, can direct, tailor, and efficiently utilize the cooling air supplied as cooling airflows through and out of the airfoil  100 . The ability to tailor or customize an exit airflow direction through the outlets via the concave portions can improve producibility in a variety of manufacturing methods, including casting or additive manufacturing. The concave portions can effectively provide a thinner trailing edge compared to traditional airfoils, which improves bore cooling performance and reduces the weight of the airfoil, thereby improving durability and engine efficiency. It can also be appreciated that the use of concave portions or other indented surface features can improve or tailor flow streams around the airfoil, or enhance mixing and promote turbulence where desired. 
     It should be understood that application of the disclosed design is not limited to turbine engines with fan and booster sections, but is applicable to turbojets and turboshaft engines as well. 
     To the extent not already described, the different features and structures of the various embodiments can be used in combination, or in substitution with each other as desired. That one feature is not illustrated in all of the embodiments is not meant to be construed that it cannot be so illustrated, but is done for brevity of description. Thus, the various features of the different embodiments can be mixed and matched as desired to form new embodiments, whether or not the new embodiments are expressly described. All combinations or permutations of features described herein are covered by this disclosure. 
     This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.