Patent Publication Number: US-11649731-B2

Title: Airfoil having internal hybrid cooling cavities

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application is a Division of the legally related U.S. patent application Ser. No. 15/723,473, filed Oct. 3, 2017. The content of the priority application is hereby incorporated by reference in its entirety. 
    
    
     BACKGROUND 
     Illustrative embodiments pertain to the art of turbomachinery, and specifically to turbine rotor components. 
     Gas turbine engines are rotary-type combustion turbine engines built around a power core made up of a compressor, combustor and turbine, arranged in flow series with an upstream inlet and downstream exhaust. The compressor compresses air from the inlet, which is mixed with fuel in the combustor and ignited to generate hot combustion gas. The turbine extracts energy from the expanding combustion gas, and drives the compressor via a common shaft. Energy is delivered in the form of rotational energy in the shaft, reactive thrust from the exhaust, or both. 
     The individual compressor and turbine sections in each spool are subdivided into a number of stages, which are formed of alternating rows of rotor blade and stator vane airfoils. The airfoils are shaped to turn, accelerate and compress the working fluid flow, or to generate lift for conversion to rotational energy in the turbine. 
     Airfoils may incorporate various cooling cavities located adjacent external side walls. Such cooling cavities are subject to both hot material walls (exterior or external) and cold material walls (interior or internal). Although such cavities are designed for cooling portions of airfoil bodies, various cooling flow characteristics can cause hot sections where cooling may not be sufficient. Accordingly, improved means for providing cooling within an airfoil may be desirable. 
     BRIEF DESCRIPTION 
     According to some embodiments, airfoils for gas turbine engines are provided. The airfoils include an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge, a first core cavity within the airfoil body, and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall and at least one first cavity impingement hole is formed within the first surface, wherein a first impingement flow flows from the first core cavity through the at least one first cavity impingement hole and impinges upon the first exterior wall to form a first high momentum jet of impingement air thereon and a central ridge extending into the second core cavity from at least one of the first cavity wall and the second wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include that the central ridge is a forward central ridge extending into the second core cavity from the first cavity wall, the airfoil further comprising an aft central ridge extending into the second core cavity from the second cavity wall. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include at least one second cavity impingement hole formed within the second surface, wherein a second impingement flow flows from the first core cavity through the at least one second cavity impingement hole and impinges upon the second exterior wall to form a second high momentum jet thereon. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include that the first impingement flow separates into the first high momentum jet flowing along the first exterior wall and a first portion of a radial cooling flow within the second core cavity and the second impingement flow separates into the second high momentum jet flowing along the second exterior wall and a second portion of the radial cooling flow within the second core cavity, wherein the first and second portions of the radial cooling flow flow radially within the two-vortex chamber. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include a funneling feature extending the second core cavity along the first exterior wall to the at least one circuit exit. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include at least one heat transfer augmentation feature within the at least one circuit exit. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include at least one film exit in the first exterior wall, the at least one film exit arranged to expel air from the second core cavity through the first exterior wall. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include a funneling feature extending the second core cavity along the first exterior wall to the at least one circuit exit. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the airfoils may include that the at least one first cavity impingement hole has one of a radial orientation, an axial orientation, or an angular orientation within the first cavity wall. 
     According to some embodiments, core structures for manufacturing airfoils for gas turbine engines are provided. The core structures include a first core cavity core to form a first core cavity and a second core cavity core to form a second core cavity, the second core cavity core located adjacent the first core cavity core, wherein the second core cavity core is arranged to form a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall in a formed airfoil body such that the first cavity wall is located between the second core cavity core and the first core cavity and the first and second exterior walls are exterior walls of the formed airfoil body. A space between the first core cavity core and the second core cavity core that defines the first cavity wall includes a first portion to form a first surface of the first cavity wall that is angled toward the formed first exterior wall and a second portion to form a second surface of the first cavity wall that is angled toward the formed second exterior wall. At least one first cavity impingement stem extends between the first core cavity core and the second core cavity core, wherein at least one first cavity impingement hole is formed thereby in a formed airfoil body such that cooling flow can flow from the first core cavity through the at least one first cavity impingement hole and impinge upon the first exterior wall of the formed airfoil body to form a first high momentum jet of impingement air thereon. A central channel is formed in the second core cavity core extending into the second core cavity core to form a central ridge on at least one of the first cavity wall and the second cavity wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include at least one second cavity impingement stem extending between the first core cavity core and the second core cavity core, wherein at least one second cavity impingement hole is formed thereby in a formed airfoil body such that cooling flow can flow from the first core cavity through the at least one second cavity impingement hole and impinge upon the second exterior wall of the formed airfoil body to form a second high momentum jet thereon. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include at least one film exit stem attached to the second core cavity core to form at least one film exit in the first exterior wall, the at least one film exit arranged to expel air from the second core cavity through the first exterior wall in the formed airfoil body. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include that the at least one formed film exit is arranged to pull the impingement air from the at least one first cavity impingement hole along an interior surface of the first exterior wall within the second core cavity of the formed airfoil. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include at least one film exit core attached to the second core cavity core to form at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall in the formed airfoil body. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include that the at least one film exit core includes one or more heat transfer augmentation core features therein to form heat transfer augmentation features in the at least one circuit exit. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include that the central channel is a forward central channel extending into the second core cavity core to form a forward central ridge in a formed airfoil, the core structure further comprising an aft central channel extending into the second core cavity to form an aft central ridge in the formed airfoil. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include a funnel feature extension extending from the second core cavity core in an aftward direction to form a funneling feature in a formed airfoil. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the core structures may include that the at least one first cavity impingement stem is oblong in shape and has one of a radial orientation, an axial orientation, or an angular orientation. 
     According to some embodiments, gas turbine engines are provided. The gas turbine engines include an airfoil having an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge, a first core cavity within the airfoil body, and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface, wherein a first impingement flow flows from the first core cavity through the at least one first cavity impingement hole and impinges upon the first exterior wall to form a first high momentum jet of impingement air thereon. A central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber. 
     The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike: The subject matter is particularly pointed out and distinctly claimed at the conclusion of the specification. The foregoing and other features, and advantages of the present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which like elements may be numbered alike and: 
         FIG.  1    is a schematic cross-sectional illustration of a gas turbine engine; 
         FIG.  2    is a schematic illustration of a portion of a turbine section of the gas turbine engine of  FIG.  1   ; 
         FIG.  3    is a schematic illustration of a hybrid cavity configuration of an airfoil; 
         FIG.  4 A  is a schematic illustration of a cavity configuration of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  4 B  is a schematic illustration of airflow through the airfoil of  FIG.  4 A ; 
         FIG.  5 A  is a top down plan view cross-section illustration of internal cavities of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  5 B  is a side elevation cross-section illustrating the internal cavities of the airfoil of  FIG.  5 A  and illustrating air flow flowing therein; 
         FIG.  6    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  7    is a schematic illustration of a cross-section of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  8    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  9    is a schematic illustration of a cross-section of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  10    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  11    is a schematic illustration of a cross-section of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  12    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  13    is a schematic illustration of a portion of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  14    is a schematic illustration of a portion of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  15    is a schematic illustration of a cross-section of an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  16    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure; 
         FIG.  17    is an elevation view of a cavity wall in accordance with an embodiment of the present disclosure illustrating an impingement hole configuration; 
         FIG.  18    is an elevation view of a cavity wall in accordance with an embodiment of the present disclosure illustrating an impingement hole configuration; and 
         FIG.  19    is a schematic illustration of a portion of a core structure for forming an airfoil in accordance with an embodiment of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     Detailed descriptions of one or more embodiments of the disclosed apparatus and/or methods are presented herein by way of exemplification and not limitation with reference to the Figures. 
       FIG.  1    schematically illustrates a gas turbine engine  20 . The gas turbine engine  20  is disclosed herein as a two-spool turbofan that generally incorporates a fan section  22 , a compressor section  24 , a combustor section  26  and a turbine section  28 . Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section  22  drives air along a bypass flow path B in a bypass duct, while the compressor section  24  drives air along a core flow path C for compression and communication into the combustor section  26  then expansion through the turbine section  28 . Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. 
     The exemplary engine  20  generally includes a low speed spool  30  and a high speed spool  32  mounted for rotation about an engine central longitudinal axis A relative to an engine static structure  36  via several bearing systems  38 . It should be understood that various bearing systems  38  at various locations may alternatively or additionally be provided, and the location of bearing systems  38  may be varied as appropriate to the application. 
     The low speed spool  30  generally includes an inner shaft  40  that interconnects a fan  42 , a low pressure compressor  44  and a low pressure turbine  46 . The inner shaft  40  is connected to the fan  42  through a speed change mechanism, which in exemplary gas turbine engine  20  is illustrated as a geared architecture  48  to drive the fan  42  at a lower speed than the low speed spool  30 . The high speed spool  32  includes an outer shaft  50  that interconnects a high pressure compressor  52  and high pressure turbine  54 . A combustor  56  is arranged in exemplary gas turbine  20  between the high pressure compressor  52  and the high pressure turbine  54 . An engine static structure  36  is arranged generally between the high pressure turbine  54  and the low pressure turbine  46 . The engine static structure  36  further supports bearing systems  38  in the turbine section  28 . The inner shaft  40  and the outer shaft  50  are concentric and rotate via bearing systems  38  about the engine central longitudinal axis A which is collinear with their longitudinal axes. 
     The core airflow is compressed by the low pressure compressor  44  then the high pressure compressor  52 , mixed and burned with fuel in the combustor  56 , then expanded over the high pressure turbine  54  and low pressure turbine  46 . The turbines  46 ,  54  rotationally drive the respective low speed spool  30  and high speed spool  32  in response to the expansion. It will be appreciated that each of the positions of the fan section  22 , compressor section  24 , combustor section  26 , turbine section  28 , and fan drive gear system  48  may be varied. For example, gear system  48  may be located aft of combustor section  26  or even aft of turbine section  28 , and fan section  22  may be positioned forward or aft of the location of gear system  48 . 
     The engine  20  in one example is a high-bypass geared aircraft engine. In a further example, the engine  20  bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), the geared architecture  48  is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine  46  has a pressure ratio that is greater than about five. In one disclosed embodiment, the engine  20  bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor  44 , and the low pressure turbine  46  has a pressure ratio that is greater than about five 5:1. Low pressure turbine  46  pressure ratio is pressure measured prior to inlet of low pressure turbine  46  as related to the pressure at the outlet of the low pressure turbine  46  prior to an exhaust nozzle. The geared architecture  48  may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans. 
     A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section  22  of the engine  20  is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,688 meters). The flight condition of 0.8 Mach and 35,000 ft (10,688 meters), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(514.7° R)]0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 m/sec). 
     Although the gas turbine engine  20  is depicted as a turbofan, it should be understood that the concepts described herein are not limited to use with the described configuration, as the teachings may be applied to other types of engines such as, but not limited to, turbojets, turboshafts, and three-spool (plus fan) turbofans wherein an intermediate spool includes an intermediate pressure compressor (“IPC”) between a low pressure compressor (“LPC”) and a high pressure compressor (“HPC”), and an intermediate pressure turbine (“IPT”) between the high pressure turbine (“HPT”) and the low pressure turbine (“LPT”). 
       FIG.  2    is a schematic view of a portion of the turbine section  28  that may employ various embodiments disclosed herein. Turbine section  28  includes a plurality of airfoils  60 ,  62  including, for example, one or more blades and vanes. The airfoils  60 ,  62  may be hollow bodies with internal cavities defining a number of channels or cores, hereinafter airfoil cores, formed therein and extending from an inner diameter  66  to an outer diameter  68 , or vice-versa. The airfoil cores may be separated by partitions within the airfoils  60 ,  62  that may extend either from the inner diameter  66  or the outer diameter  68  of the airfoil  60 ,  62 . The partitions may extend for a portion of the length of the airfoil  60 ,  62 , but may stop or end prior to forming a complete wall within the airfoil  60 ,  62 . Thus, each of the airfoil cores may be fluidly connected and form a fluid path within the respective airfoil  60 ,  62 . The airfoils  60 ,  62  may include platforms  70  located proximal to the inner diameter  66  thereof. Located below the platforms  70  (e.g., radially inward with respect to the engine axis) may be airflow ports and/or bleed orifices that enable air to bleed from the internal cavities of the airfoils  60 ,  62 . A root of the airfoil may connect to or be part of the platform  70 . 
     The turbine section  28  is housed within a case  80 , which may have multiple parts (e.g., turbine case, diffuser case, etc.). In various locations, components, such as seals, may be positioned between airfoils  60 ,  62  and the case  80 . For example, as shown in  FIG.  2   , blade outer air seals  82  (hereafter “BOAS”) are located radially outward from the blade  60 . As will be appreciated by those of skill in the art, the BOAS  82  may include BOAS supports that are configured to fixedly connect or attach the BOAS  82  to the case  80  (e.g., the BOAS supports may be located between the BOAS  82  and the case  80 ). As shown in  FIG.  2   , the case  80  includes a plurality of case hooks  84  that engage with BOAS hooks  86  to secure the BOAS  82  between the case  80  and a tip of the airfoil  60 . 
     As shown and labeled in  FIG.  2   , a radial direction is upward on the page (e.g., radial with respect to an engine axis) and an axial direction is to the right on the page (e.g., along an engine axis). Thus, radial cooling flows will travel up or down on the page and axial flows will travel left-to-right (or vice versa). 
     Turning to  FIG.  3   , an airfoil  300  having internal hybrid cavities is shown. As used herein, a “hybrid cavity” is an internal cavity of an airfoil that has one wall that is a hot wall (e.g., exterior surface of an airfoil body and exposed to hot, gaspath air) and another wall that is a cold wall (e.g., a wall that is not exposed to the hot gaspath air, and may be an internal or interior wall structure of the airfoil). For example, as shown in  FIG.  3   , the airfoil  300  has a two leading edge hybrid cavities  302 , a pressure side hybrid cavity  304 , and a suction side hybrid cavity  306 . 
     The hybrid cavities  302 ,  304 ,  306  are defined in the airfoil  300  with a first wall of the hybrid cavity defined by an exterior surface wall  310  of the airfoil  300 . The exterior surface wall  310  is a “hot” wall of the airfoil  300  that is exposed to hot, gaspath air. A second wall of the hybrid cavity is defined by an interior wall  312 , with the interior wall  312  being a “cold” wall of the airfoil  300 . A cold wall is one that is not exposed to the hot gaspath air, and thus remains relatively cool in comparison to the hot, exterior surface walls. For example, the interior walls  312  can be adjacent to or part of defining walls of internal, cold core cavities  308 . 
     Embodiments described herein are directed to eliminating the need for the interior wall to define the hybrid cavities. For example, in some embodiments, the elimination of the interior cold wall(s) is achieved by connecting a first core cavity to a second core cavity with a double impingement rib along the edges of the second core cavity. The double impingement rib directs air from the first core cavity to the second core cavity along an external hot wall of the second core cavity. Further, one or more sets of film holes are arranged along the external hot wall of the second core cavity to directionally pull the air along the external hot wall, thus generating a high momentum jet along an interior surface of the external hot wall within the second core cavity. The high momentum jet within the second core cavity creates a flow field that rides along the external hot wall and creates a “dead zone” in the middle of the second core cavity. The “dead zone” is an area or region of the second core cavity that is not directly influenced by the impingement cooling from the first core cavity and enables a radial cooling flow to pass through the middle of the second core cavity. Advantageously, embodiments provided herein enable the benefits of a hybrid cavity without the added weight of a conventional hybrid cavity geometry (e.g., employing the interior cold wall). 
     For example, turning to  FIGS.  4 A- 4 B , schematic illustrations of an airfoil  400  in accordance with an embodiment of the present disclosure shown.  FIG.  4 A  illustrates the structure of the airfoil  400  and  FIG.  4 B  illustrates a portion of an airflow through the airfoil  400 . In this embodiment, a leading edge  402  of the airfoil  400  is arranged with two leading edge hybrid cavities  404 . The cold walls of the leading edge hybrid cavities  404  is defined by a first core cavity  406 . As shown, the first core cavity  406  is a typical cold, internal cavity, similar to that shown in  FIG.  3   . Aft of the first core cavity  406  is a second core cavity  408 . The second core cavity  408 , as shown, is not a hybrid cavity, but rather has two opposing exterior walls  410 ,  412 . A first exterior wall  410  of the second core cavity  408  is a hot wall on a pressure side of the airfoil  400  and a second exterior wall  412  of the second core cavity  408  is a hot wall on a suction side of the airfoil  400 . The first core cavity  406  and the second core cavity  408  are divided or separated by an impingement rib  414 . 
     The impingement rib  414  includes a first set of impingement holes  416  and a second set of impingement holes  418 . The first and second sets of impingement holes  416 ,  418  are arranged to fluidly connect the first core cavity  406  to the second core cavity  408  and to direct impingement air from the first core cavity  406  into the second core cavity  408  along the exterior walls  410 ,  412 . The impinging air from the first core cavity  406  into the second core cavity  408  is achieved due to a pressure differential between the first and second core cavities  406 ,  408 . The first core cavity  408  has relatively high air pressure therein. The high air pressure is due to a fed of cooling air supplied into the first core cavity  406 , such as from a platform, inner diameter source, outer diameter source, etc. as will be appreciated by those of skill in the art. The second core cavity  408  has relatively low air pressure, which may be a result of a restricted cooling flow, or an absence of a supplied cooling flow directly into the second core cavity  408 . The difference in pressure causes the air from the first core cavity  406  to flow into the second core cavity  408  through the impingement holes  416 ,  418 . In a blade configuration, for example, the first core cavity  406  may be sourced from a root region and the second core  408  may be closed off from being sourced from the root region (e.g., completely sealed, blocked by a metering plate or other structure, etc.), thus resulting in a differential pressure between the first and second core cavities  406 ,  408 . In embodiments where the second core cavity  408  is completely sealed, all cooling air within the second core cavity  408  can be sourced from the first cooling cavity  406 . In a vane configuration, for example, the first and second core cavities  406 ,  408  could have two different sources with two different air pressures to achieve a desired differential pressure to achieve the impingement from the first core cavity  406  into the second core cavity  408 . 
     As shown in  FIGS.  4 A- 4 B , the first set of impingement holes  416  are angled to direct impingement air from the first core cavity  406  at the first exterior wall  410  within the second core cavity  408 . Similarly, the second set of impingement holes  418  are angled to direct impingement air from the first core cavity  406  at the second exterior wall  412  within the second core cavity  408 . The impinging air forms a high momentum jet of air along the interior surfaces of the exterior walls  410 ,  412  thus isolating an internal dead zone  424 , as shown and described herein. The second core cavity  408  has a first film exit  420  on the first exterior wall  410  that enables a portion of a flow to pass from the second core cavity  408  to the exterior of the airfoil  400 , such as out along a pressure side wall exterior surface of the airfoil  400 . The second core cavity  408 , as shown, also includes a second film exit  422  on the second exterior wall  412  that enables a portion of a flow to pass from the second core cavity  408  to the exterior of the airfoil  400 , such as out along a suction side wall exterior surface of the airfoil  400 . 
     With reference to  FIG.  4 B , a schematic illustration of an airflow through the airfoil  400  is shown. A first side cooling flow  426  originates within the first core cavity  406 , flows through the first set of impingement holes  416  in the impingement rib  414  into the second core cavity  408  along the first exterior wall  410 . Similarly, a second side cooling flow  428  originates within the first core cavity  406 , flows through the second set of impingement holes  418  in the impingement rib  414  into the second core cavity  408  along the second exterior wall  412 . The first side cooling flow  426  is drawn through the second core cavity  408  along the first exterior wall  410  by the pull of airflow through the first film exit  420 . Similarly, the second side cooling flow  428  is drawn through the second core cavity  408  along the second exterior wall  412  by the pull of airflow through the second film exit  422 . 
     As shown in  FIG.  4 B , the first and second side cooling flows  426 ,  428  create a dead zone  424  within the second core cavity  408 . The first and second sets of impingement holes  416 ,  418  include impingement holes that are configured to enable high velocity, high momentum side cooling flows  426 ,  428  to be formed as a high momentum jet along the interior surfaces of the first and second exterior side walls  410 ,  412  of the second core cavity  408 . The high velocity, high momentum jet flow of the side cooling flows  426 ,  428  can isolate the dead zone  424  from the hot surfaces of the exterior side walls  410 ,  412 , thus preventing high thermal transfer from the material of the airfoil  400  into the dead zone  424 . 
     As shown, a radial cooling flow  430  passes through the second core cavity  408  along the interior surface of the exterior side walls  410 ,  412 . The radial cooling flow  430  may be a typical cooling flow passing from one end of an airfoil (or cavity) to another end of the airfoil (or cavity). The radial cooling flow  430  can flow in either direction, e.g., radially outward toward an outer diameter or radially inward toward an inner diameter. For example, in some embodiments, the radial cooling flow  430  can flow from a root or first end of the airfoil  400  to a tip or second end of the airfoil  400 . In some embodiments, the radial cooling flow  430  is entirely formed from a portion of the air flowing through the first and second sets of impingement holes  416 ,  418  (e.g., from the first core cavity  406 ). In other embodiments, a portion of the radial cooling flow  430  can be sourced from a root or tip region and/or from other internal cavities of the airfoil (although the pressure within the second cavity core  408  will still be less than that within the first cavity core  408 ). 
     The radial cooling flow  430  may have low MACH numbers, slow flow, and low momentum. As illustratively shown, a portion of the radial cooling flow  430  may be rotated or swirled by the flow of the side cooling flows  426 ,  428 . For example, in some arrangements, the side cooling flows  426 ,  428  can cause dynamic vortices to be generated within the second core cavity  408 , with the dynamic vortices operating to contain the side cooling flows  426 ,  428  against the exterior walls  410 ,  412  (e.g., compress/push the high momentum jet air of the side cooling flows  426 ,  428  against the exterior walls  410 ,  412 ) and/or to contain and channel the radial cooling flow  430  within the dead zone  424  of the second core cavity  408 . 
     Turning now to  FIGS.  5 A- 5 B , schematic illustrations of an airfoil  500  in accordance with an embodiment of the present disclosure are shown.  FIG.  5 A  is a top down plan view cross-section illustrating the internal cavities of the airfoil  500  and  FIG.  5 B  is a side elevation cross-section illustrating the internal cavities of the airfoil  500  illustrating air flow flowing therein. The airfoil  500  includes a first core cavity  502  and a second core cavity  504  having an arrangement similar to that described above, wherein side cooling flows are generated by airflow that flows from the first core cavity  502  along interior side walls of the second core cavity  504  and then is expelled out of the airfoil  500 . 
     An interior of the airfoil  500 , at a leading edge  506 , is divided into multiple leading edge hybrid cavities  508 . Although shown with two leading edge hybrid cavities  508 , various embodiments may have any number of leading edge hybrid or non-hybrid, core cavities, including a single leading edge cavity (hybrid or core cavity). The leading edge hybrid cavities  508  are arranged as leading-edge impingement cavities that are supplied with impingement air from the first core cavity  502  through one or more forward impingement holes  510 . The impinging air from the first core cavity  502  into the leading edge hybrid cavities  508  allows for changes in pressure distribution across the leading edge  506  of the airfoil  500  without causing back flow margin issues. The leading edge hybrid cavities  508  are fed from the first core cavity  502 , which may be a leading edge feed cavity which also feeds the second core cavity  504 , in a manner similar to that described above. 
     The second core cavity  504  is defined in an axial direction between a first cavity wall  512  and a second cavity wall  514 . In a circumferential direction, the second core cavity  504  is defined by a first exterior wall  516  and an opposing second exterior wall  518 . As discussed above, the exterior walls  516 ,  518  of the second core cavity  504  are “hot” walls that are exposed to hot gaspath air. In this embodiment, the first cavity wall  512  and the second cavity wall  514  are “cold” walls that are not exposed to the hot gaspath air (i.e., they are internal walls). The first cavity wall  512  includes one or more cavity impingement holes  520 ,  522 . In this embodiment, a first set of cavity impingement holes  520  is positioned and oriented within the first cavity wall  512  to direct an aft-flowing impingement flow from the first core cavity  502  into the second core cavity  504  and at the first exterior side wall  516 . Similarly, a second set of cavity impingement holes  522  is positioned and oriented within the first cavity wall  512  to direct an aft-flowing impingement flow from the first core cavity  502  into the second core cavity  504  and at the second exterior side wall  518 . 
     As shown, part of the directing of the impinging flow from the first core cavity  502  to the second core cavity  504  is achieved by the first cavity wall  512  being contoured or shaped. In the present embodiment, the first cavity wall  512  has a first surface  524  that is angled or faces the first exterior wall  516 . Similarly, the first cavity wall  512  has a second surface  526  that is angled or faces the second exterior wall  518 . Although the first cavity wall  512  has a specific geometric shape (e.g., shown as a chevron shape extending into the second core cavity  504 ) the geometry, shape, orientation, etc. of the first cavity wall  512  can be varied without departing from the scope of the present disclosure. For example, in some alternative arrangements, the first cavity wall may be arcuate or curved in a smooth transition from one side of the airfoil to the other, with angled surfaces facing the respective exterior walls. 
     In addition to the first cavity wall  512  having angled surfaces  524 ,  526 , in some embodiments, the cavity impingement holes  520 ,  522  may be angled such that the air is forced to imping upon the exterior walls  516 ,  518  of the second core cavity  508 . After the air from the first core cavity  502  impinges upon the exterior walls  516 ,  518  at least a portion of the air will form a high momentum jet along the exterior walls  516 ,  518  and flow out of the second core cavity  504  through film exits  528 ,  530 . For example, air flowing through the first cavity impingement hole  520  will contact the interior surface of the first exterior wall  516  and run along the first exterior wall  516  to one or more first film exits  528 , where the air will exit the interior of the airfoil  500  and flow along and exterior surface of the airfoil  500  (e.g., along a pressure side exterior surface). Similarly, air flowing through the second cavity impingement hole  522  will contact the interior surface of the second exterior wall  518  and run along the second exterior wall  518  to one or more second film exits  530 , where the air will exit the interior of the airfoil  500  and flow along and exterior surface of the airfoil  500  (e.g., along a suction side exterior surface). The flow of the impingement air along the exterior walls  516 ,  518  causes a dead zone to form within the middle of the second core cavity  504 , as shown and described above. 
     As shown in  FIG.  5 B , impingement air  534  flows from the first core cavity  502  into the second core cavity  504  through the cavity impingement holes  520 ,  522 . The impingement air  534  divides into high momentum jet air  536  that flows along the exterior walls  516 ,  518  and a radial cooling flow  538  within the second core cavity  504 . The high momentum jet air  536  is a film that flows along the exterior walls  516 ,  518  and out through the film exits  528 ,  530  as film air  540  that will flow along an exterior surface of the airfoil  500  (e.g., within a hot gaspath). The radial cooling flow  538  will have a low momentum and/or velocity within and around the dead zone (e.g., as shown in  FIG.  4 B ) that is within the second core cavity  504 . The radial cooling flow  538  can form into a dynamic vortex within the second core cavity  504 . That is, the radial cooling flow  538  portion of the impingement air  534  may rotate within the dead zone of the cavity due to, in part, the high momentum jet air  536 . The dynamic vortex structure of the radially cooling flow  538  may push the high momentum jet air  536  against the exterior walls  516 ,  518  and thus increase turbulence and, therefore, heat transfer within the second core cavity  504 . 
     As shown in  FIGS.  5 A- 5 B , the airfoil  500  can include additional cooling cavities  532  located throughout the interior of the airfoil  500 . The additional cooling cavities  532  can be parts of serpentine cavities, trailing edge cavities, flag tip cavities, or other cooling cavities (hybrid or non-hybrid (e.g., core) cavities). 
     Turning now to  FIG.  6   , a schematic illustration of a portion of an airfoil core structure  600  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  600  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  600  includes a plurality of core bodies that are arranged to form cavities within an airfoil body (e.g., as shown and described above). For example, the airfoil core structure  600  includes two leading edge hybrid cavity cores  602 , a first core cavity core  604 , and a second core cavity core  606 . The leading edge hybrid cavity cores  602  are connected to the forward core cavity core  604  by one or more forward impingement stems  608  that are arranged to form impingement holes between a formed first core cavity (from the first core cavity core  604 ) and formed leading edge hybrid cavities (from the leading edge hybrid cavity cores  602 ). Similarly, one or more cavity impingement stems  610  connect the first core cavity core  604  with the second core cavity core  606  to form impingement holes between a formed first core cavity and a formed second core cavity, as shown and described above. 
     The first core cavity core  604  is arranged with a geometry to form a first cavity wall of a formed second core cavity with a first surface and a second surface, as shown and described above. The first and second surfaces are arranged with the cavity impingement stems  610  to connect with the second core cavity core  606 . Extending from or attached to the second core cavity core  606  are one or more film exit stems  612  that are arranged to form the film exits as shown and described above. In some embodiments, rather than using stems  612 , the film exits can be drilled holes. 
     Although the airfoil core structure  600  is shown with a specific arrangement and geometry, those of skill in the art will appreciate that alternative arrangements are possible without departing from the scope of the present disclosure. For example, in some embodiments, the film exits can be formed using refractory metal core structures that are integrally formed with or attached to the second core cavity core  606 . Further, in some embodiments, manufacturing can be achieved using additive manufacturing techniques. 
     Turning now to  FIG.  7   , a schematic illustration of an airfoil  700  in accordance with an embodiment of the present disclosure is shown. The airfoil  700  includes a first core cavity  702  and a second core cavity  704  having an arrangement similar to that described above, wherein side cooling flows are generated by airflow that flows from the first core cavity  702  along interior side walls of the second core cavity  704  and then is expelled out of the airfoil  700 . 
     As shown, the interior of the airfoil  700 , at a leading edge  706 , is divided into multiple leading edge hybrid cavities  708 . The leading edge hybrid cavities  708  are arranged as leading-edge impingement cavities that are supplied with impingement air from the first core cavity  702  through one or more forward impingement holes  710 . The leading edge hybrid cavities  708  are fed from the first core cavity  702 , which may be a leading edge feed cavity which also feeds the second core cavity  704 , in a manner similar to that described above. 
     The second core cavity  704  is defined in an axial direction between a first cavity wall  712  and a second cavity wall  714 . In a circumferential direction, the second core cavity  704  is defined by a first exterior wall  716  and an opposing second exterior wall  718 . As discussed above, the exterior walls  716 ,  718  of the second core cavity  704  are “hot” walls that are exposed to hot gaspath air, and the first cavity wall  712  and the second cavity wall  714  are “cold” walls that are not exposed to the hot gaspath air (i.e., they are internal walls). The first cavity wall  712  includes one or more cavity impingement holes  720 ,  722 . A first set of cavity impingement holes  720  is positioned and oriented within the first cavity wall  712  to direct an aft-flowing impingement flow from the first core cavity  702  into the second core cavity  704  and at the first exterior side wall  716 . A second set of cavity impingement holes  722  is positioned and oriented within the first cavity wall  712  to direct an aft-flowing impingement flow from the first core cavity  702  into the second core cavity  704  and at the second exterior side wall  718 . 
     As shown, part of the directing of the impinging flow from the first core cavity  702  to the second core cavity  704  is achieved by the first cavity wall  712  being contoured or shaped. In the present embodiment, the first cavity wall  712  has a first surface  724  that is angled or faces the first exterior wall  716 . Similarly, the first cavity wall  712  has a second surface  726  that is angled or faces the second exterior wall  718 . In addition to the first cavity wall  712  having angled surfaces  724 ,  726 , in some embodiments, the cavity impingement holes  720 ,  722  may be angled such that the air is forced to imping upon the exterior walls  716 ,  718  of the second core cavity  708 . After the air from the first core cavity  702  impinges upon the exterior walls  716 ,  718  at least a portion of the air will form a high momentum jet along the exterior walls  716 ,  718  and flow out of the second core cavity  704  through film exits  728 ,  730 . For example, air flowing through the first cavity impingement hole  720  will contact the interior surface of the first exterior wall  716  and run along the first exterior wall  716  to one or more first film exits  728 , where the air will exit the interior of the airfoil  700  and flow along and exterior surface of the airfoil  700  (e.g., along a pressure side exterior surface). Similarly, air flowing through the second cavity impingement hole  722  will contact the interior surface of the second exterior wall  718  and run along the second exterior wall  718  to one or more second film exits  730 , where the air will exit the interior of the airfoil  700  and flow along and exterior surface of the airfoil  700  (e.g., along a suction side exterior surface). The flow of the impingement air along the exterior walls  716 ,  718  causes a dead zone to form within the middle of the second core cavity  704 , as shown and described above. 
     In the airfoil  700  shown in  FIG.  7   , the first cavity wall  712  and the second cavity wall  714  each include a central ridge. For example, as shown, a forward central ridge  742  is formed as part of or integral with the first cavity wall  712 . The forward central ridge extends aftward into the second core cavity  704  toward the second cavity wall  714 . Similarly, an aft central ridge  744  is formed as part of or integral with the second cavity wall  714 . The aft central ridge  744  extends forward into the second core cavity  704  toward the first cavity wall  712 . The central ridges  742 ,  744  do not extend entirely across the second core cavity  704 , but rather are arranged to partially define a two-vortex chamber within the second core cavity  704 . That is, the central ridges  742 ,  744  are arranged to aid in the formation of the dynamic vortices within the radial cooling flow that passes or flows within the second core cavity. Further, the addition of the central ridges  742 ,  744  enables separation of two separate dynamic vortices within the second core cavity. 
     Turning now to  FIG.  8   , a schematic illustration of a portion of an airfoil core structure  800  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  8  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  800  includes two leading edge hybrid cavity cores  802 , a first core cavity core  804 , and a second core cavity core  806 . The leading edge hybrid cavity cores  802  are connected to the forward core cavity core  804  by one or more forward impingement stems  808  that are arranged to form impingement holes between a formed first core cavity (from the first core cavity core  804 ) and formed leading edge hybrid cavities (from the leading edge hybrid cavity cores  802 ). Similarly, one or more cavity impingement stems  810  connect the first core cavity core  804  with the second core cavity core  806  to form impingement holes between a formed first core cavity and a formed second core cavity, as shown and described above. 
     The first core cavity core  804  is arranged with a geometry to form a first cavity wall of a formed second core cavity with a first surface and a second surface, as shown and described above. The first and second surfaces are arranged with the cavity impingement stems  810  to connect with the second core cavity core  806 . Extending from or attached to the second core cavity core  806  are one or more film exit stems  812  that are arranged to form the film exits as shown and described above. As shown, the second core cavity core  806  includes a forward central channel  814  and an aft central channel  816  that are arranged to form forward and aft ridges, respectively, as shown and described with respect to  FIG.  7   . 
     Although  FIGS.  7 - 8    are illustrated with two central ridges (or associated central channels in a core body), various embodiment may be formed alternatively. For example, in some embodiment, only one of the forward and second cavity walls may include the central ridge, rather than both of the forward and second cavity walls. 
     Turning now to  FIG.  9   , a schematic illustration of an airfoil  900  in accordance with an embodiment of the present disclosure is shown. The airfoil  900  includes a first core cavity  902  and a second core cavity  904  having an arrangement similar to that described above, wherein side cooling flows are generated by airflow that flows from the first core cavity  902  along interior side walls of the second core cavity  904  and then is expelled out of the airfoil  900 . 
     As shown, the interior of the airfoil  900 , at a leading edge  906 , is divided into multiple leading edge hybrid cavities  908 . The leading edge hybrid cavities  908  are arranged as leading-edge impingement cavities that are supplied with impingement air from the first core cavity  902  through one or more forward impingement holes  910 . The leading edge hybrid cavities  908  are fed from the first core cavity  902 , which may be a leading edge feed cavity which also feeds the second core cavity  904 , in a manner similar to that described above. 
     The second core cavity  904  is defined in an axial direction between a first cavity wall  912  and a second cavity wall  914 . In a circumferential direction, the second core cavity  904  is defined by a first exterior wall  916  and an opposing second exterior wall  918 . As discussed above, the exterior walls  916 ,  918  of the second core cavity  904  are “hot” walls that are exposed to hot gaspath air, and the first cavity wall  912  and the second cavity wall  914  are “cold” walls that are not exposed to the hot gaspath air (i.e., they are internal walls). The first cavity wall  912  includes one or more cavity impingement holes  920 ,  922 . A first set of cavity impingement holes  920  is positioned and oriented within the first cavity wall  912  to direct an aft-flowing impingement flow from the first core cavity  902  into the second core cavity  904  and at the first exterior side wall  916 . A second set of cavity impingement holes  922  is positioned and oriented within the first cavity wall  912  to direct an aft-flowing impingement flow from the first core cavity  902  into the second core cavity  904  and at the second exterior side wall  918 . 
     As shown, part of the directing of the impinging flow from the first core cavity  902  to the second core cavity  904  is achieved by the first cavity wall  912  being contoured or shaped. In the present embodiment, the first cavity wall  912  has a first surface  924  that is angled or faces the first exterior wall  916 . Similarly, the first cavity wall  912  has a second surface  926  that is angled or faces the second exterior wall  918 . In addition to the first cavity wall  912  having angled surfaces  924 ,  926 , in some embodiments, the cavity impingement holes  920 ,  922  may be angled such that the air is forced to imping upon the exterior walls  916 ,  918  of the second core cavity  908 . After the air from the first core cavity  902  impinges upon the exterior walls  916 ,  918  at least a portion of the air will form a high momentum jet along the exterior walls  916 ,  918  and flow out of the second core cavity  904  through film exits  928 ,  930 . For example, air flowing through the first cavity impingement hole  920  will contact the interior surface of the first exterior wall  916  and run along the first exterior wall  916  to one or more first film exits  928 , where the air will exit the interior of the airfoil  900  and flow along and exterior surface of the airfoil  900  (e.g., along a pressure side exterior surface). Similarly, air flowing through the second cavity impingement hole  922  will contact the interior surface of the second exterior wall  918  and run along the second exterior wall  918  to one or more second film exits  930 , where the air will exit the interior of the airfoil  900  and flow along and exterior surface of the airfoil  900  (e.g., along a suction side exterior surface). The flow of the impingement air along the exterior walls  916 ,  918  causes a dead zone to form within the middle of the second core cavity  904 , as shown and described above. 
     In the airfoil  900  shown in  FIG.  9   , the first and second film exits  928 ,  930  are formed as circuit exits  946 ,  948 , respectively. That is, in prior embodiments, as illustratively shown, the film exits have been formed as film holes (e.g., discrete exits). However, in this embodiment, an exit gap or channel can be formed, and in some embodiments, heat transfer augmentation features  946   a,    946   b,    948   a,    948   b  can be provided along the length of the film exits  928 ,  930  prior to exiting the airfoil. The heat transfer augmentation features  946   a,    946   b,    948   a,    948   b  can be pedestals, tear drops, racetracks, or other types of heat transfer augmentation features as appreciated by those of skill in the art. Further, such increased size film exits  928 ,  930  can allow for more of the impinged air (e.g., side cooling flows) to flow directly along the side walls and provided cooling thereto, while reducing an amount of cold air in the vortexes within the second core cavity  904 . 
     Turning now to  FIG.  10   , a schematic illustration of a portion of an airfoil core structure  1000  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  1000  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  1000  includes two leading edge hybrid cavity cores  1002 , a first core cavity core  1004 , and a second core cavity core  1006 . The leading edge hybrid cavity cores  1002  are connected to the forward core cavity core  1004  by one or more forward impingement stems  1008  that are arranged to form impingement holes between a formed first core cavity (from the first core cavity core  1004 ) and formed leading edge hybrid cavities (from the leading edge hybrid cavity cores  1002 ). Similarly, one or more cavity impingement stems  1010  connect the first core cavity core  1004  with the second core cavity core  1006  to form impingement holes between a formed first core cavity and a formed second core cavity, as shown and described above. 
     The first core cavity core  1004  is arranged with a geometry to form a first cavity wall of a formed second core cavity with a first surface and a second surface, as shown and described above. The first and second surfaces are arranged with the cavity impingement stems  1010  to connect with the second core cavity core  1006 . Extending from or attached to the second core cavity core  1006  are one or more film exit cores  1016  that are arranged to form the film exits as shown and described above with respect to  FIG.  9   . For example, as shown, the film exit core  1016  includes first and second heat transfer augmentation core features  1016   a,    1016   b  to form various heat transfer augmentation features within a film exit (e.g., film exits  928 ,  930  shown in  FIG.  9   ). The film exit core  1016 , as shown, also defines a continuous structure for forming an exit line or gap that will be formed on an exterior surface of a formed airfoil. 
     Turning now to  FIG.  11   , a schematic illustration of an airfoil  1100  in accordance with an embodiment of the present disclosure is shown. The airfoil  1100  includes a first core cavity  1102  and a second core cavity  1104  having an arrangement similar to that described above, wherein side cooling flows are generated by airflow that flows from the first core cavity  1102  along interior side walls of the second core cavity  1104  and then is expelled out of the airfoil  1100 . 
     As shown, the interior of the airfoil  1100 , at a leading edge  1106 , is divided into multiple leading edge hybrid cavities  1108 . The leading edge hybrid cavities  1108  are arranged as leading-edge impingement cavities that are supplied with impingement air from the first core cavity  1102  through one or more forward impingement holes  1110 . The leading edge hybrid cavities  1108  are fed from the first core cavity  1102 , which may be a leading edge feed cavity which also feeds the second core cavity  1104 , in a manner similar to that described above. 
     The second core cavity  1104  is defined in an axial direction between a first cavity wall  1112  and a second cavity wall  1114 . In a circumferential direction, the second core cavity  1104  is defined by a first exterior wall  1116  and an opposing second exterior wall  1118 . As discussed above, the exterior walls  1116 ,  1118  of the second core cavity  1104  are “hot” walls that are exposed to hot gaspath air, and the first cavity wall  1112  and the second cavity wall  1114  are “cold” walls that are not exposed to the hot gaspath air (i.e., they are internal walls). The first cavity wall  1112  includes one or more cavity impingement holes  1120 ,  1122 . A first set of cavity impingement holes  1120  is positioned and oriented within the first cavity wall  1112  to direct an aft-flowing impingement flow from the first core cavity  1102  into the second core cavity  1104  and at the first exterior side wall  1116 . A second set of cavity impingement holes  1122  is positioned and oriented within the first cavity wall  1112  to direct an aft-flowing impingement flow from the first core cavity  1102  into the second core cavity  1104  and at the second exterior side wall  1118 . 
     As shown, part of the directing of the impinging flow from the first core cavity  1102  to the second core cavity  1104  is achieved by the first cavity wall  1112  being contoured or shaped. In the present embodiment, the first cavity wall  1112  has a first surface  1124  that is angled or faces the first exterior wall  1116 . Similarly, the first cavity wall  1112  has a second surface  1126  that is angled or faces the second exterior wall  1118 . In addition to the first cavity wall  1112  having angled surfaces  1124 ,  1126 , in some embodiments, the cavity impingement holes  1120 ,  1122  may be angled such that the air is forced to imping upon the exterior walls  1116 ,  1118  of the second core cavity  1108 . After the air from the first core cavity  1102  impinges upon the exterior walls  1116 ,  1118  at least a portion of the air will form a high momentum jet along the exterior walls  1116 ,  1118  and flow out of the second core cavity  1104  through film exits  1128 ,  1130 . For example, air flowing through the first cavity impingement hole  1120  will contact the interior surface of the first exterior wall  1116  and run along the first exterior wall  1116  to one or more first film exits  1128 , where the air will exit the interior of the airfoil  1100  and flow along and exterior surface of the airfoil  1100  (e.g., along a pressure side exterior surface). Similarly, air flowing through the second cavity impingement hole  1122  will contact the interior surface of the second exterior wall  1118  and run along the second exterior wall  1118  to one or more second film exits  1130 , where the air will exit the interior of the airfoil  1100  and flow along and exterior surface of the airfoil  1100  (e.g., along a suction side exterior surface). The flow of the impingement air along the exterior walls  1116 ,  1118  causes a dead zone to form within the middle of the second core cavity  1104 , as shown and described above. 
     In the airfoil  1100  shown in  FIG.  11   , the first and second film exits  1128 ,  1130  include funneling features  1150 ,  1152  formed in the second cavity wall  1114  and along the side walls  1116 ,  1118 . The funneling features  1150 ,  1152  are axial extensions of the second core cavity  1104  that extend along the side walls  1116 ,  1118 . The funneling features  1150 ,  1152  enable funneling of more air to the film exits  1128 ,  1130 , respectively, as compared to embodiments without such features, and can reduce the size of the dynamic vortices within the second core cavity  1104 . 
     Turning now to  FIG.  12   , a schematic illustration of a portion of an airfoil core structure  1200  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  1200  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  1200  includes two leading edge hybrid cavity cores  1202 , a first core cavity core  1204 , and a second core cavity core  1206 . The leading edge hybrid cavity cores  1202  are connected to the forward core cavity core  1204  by one or more forward impingement stems  1208  that are arranged to form impingement holes between a formed first core cavity (from the first core cavity core  1204 ) and formed leading edge hybrid cavities (from the leading edge hybrid cavity cores  1202 ). Similarly, one or more cavity impingement stems  1210  connect the first core cavity core  1204  with the second core cavity core  1206  to form impingement holes between a formed first core cavity and a formed second core cavity, as shown and described above. 
     The first core cavity core  1204  is arranged with a geometry to form a first cavity wall of a formed second core cavity with a first surface and a second surface, as shown and described above. The first and second surfaces are arranged with the cavity impingement stems  1210  to connect with the second core cavity core  1206 . Extending from and integral with the second core cavity core  1206  are funnel feature extensions  1218  that are arranged to form funneling features as shown and described with respect to  FIG.  11   . To core structure  1200  further includes one or more film exit stems  1212  that are arranged to form the film exits as shown and described above. The film exit stems  1212  extend from the funnel feature extensions  1218 . 
     Turning now to  FIG.  13   , a schematic illustration of a portion of an airfoil  1300 . The portion shown in  FIG.  13    is of an exterior wall  1318  with a first cavity wall  1312  extending therefrom into an interior of the airfoil. The first cavity wall  1312  is substantially similar to that shown and described above and is arranged to separate a first core cavity from a second core cavity. As shown, the first cavity wall  1312  includes a plurality of cavity impingement holes  1322 , with the first cavity wall  1312  having a surface  1326  that is angled toward an interior surface  1354  of the exterior side wall  1318 . Although in some embodiments, the cavity impingement holes may be circular “holes” other geometries for such impingement passages are possible. For example, in this embodiment, the cavity impingement holes  1322  have radially extending, oblong orientations. This geometry can result in the impingement air being distributed radially along the interior surface  1354  of the exterior side wall  1318 . This arrangement can provide for a substantial portion (or all) of the interior surface  1354  to receive impingement air from a first core cavity. As shown, to achieve the orientation shown in  FIG.  13   , the cavity impingement holes  1322  have an axis  1356  that runs parallel to the radial direction of the airfoil  1300 . 
     Turning now to  FIG.  14   , a schematic illustration of a portion of an airfoil  1400 . The portion shown in  FIG.  14    is of an exterior wall  1418  with a first cavity wall  1412  extending therefrom into an interior of the airfoil. The first cavity wall  1412  is substantially similar to that shown and described above and is arranged to separate a first core cavity from a second core cavity. As shown, the first cavity wall  1412  includes a plurality of cavity impingement holes  1422 , with the first cavity wall  1412  having a surface  1426  that is angled toward an interior surface  1454  of the exterior side wall  1418 . In this embodiment, the cavity impingement holes  1422  have axially extending, oblong orientations along the first cavity wall  1412 . In this embodiment, the cavity impingement holes  1422  are axially lengthened such that the impinged air on the interior surface  1454  of the exterior side wall  1418  remains on the interior surface  1454  longer (e.g., in time) regardless of augmentation features such as trip strips or small pin fins formed in or on the interior surface  1454  of the exterior side wall  1418 . As shown, to achieve the orientation shown in  FIG.  14   , the cavity impingement holes  1422  have an axis  1456  that runs perpendicular to the radial direction of the airfoil  1400 . 
     Although  FIGS.  13 - 14    illustrate specific orientations of oblong cavity impingement holes, various other orientations are possible without departing from the scope of the present disclosure. The orientation of  FIG.  13    can represent a zero degree angling of the cavity impingement holes relative to the exterior side wall and the orientation of  FIG.  14    can represent a 90° angling of the cavity impingement holes relative to the exterior side wall. A 180° angling would appear as the arrangement shown in  FIG.  13    (i.e., 0° and 180° appear the same due to the oblong geometry and shape of the cavity impingement holes). In various embodiments, the cavity impingement holes can take any degree of angling relative to the exterior side wall from 0° to 180°. That is, the cavity impingement holes have oblong shapes with a long axis oriented between 0° and 180° relative to the first exterior side wall. 
     Turning now to  FIG.  15   , a schematic illustration of an airfoil  1500  in accordance with an embodiment of the present disclosure is shown. The airfoil  1500  includes a first core cavity  1502  and a second core cavity  1504  having an arrangement different from the above described embodiments. In this embodiment, the first core cavity  1502  is located aft of the second core cavity  1504 . However, similar to the above described embodiments, side cooling flows are generated by airflow that flows from the first core cavity  1502  along interior side walls of the second core cavity  1504  and then is expelled out of the airfoil  1500 . 
     As shown, the interior of the airfoil  1500 , at a leading edge  1506 , is divided into multiple leading edge hybrid cavities  1508 . The leading edge hybrid cavities  1508  are arranged as leading-edge impingement cavities that are supplied with impingement air from a leading edge feed cavity  1558  through one or more forward impingement holes  1510 . In this embodiment, unlike that described above, the leading edge feed cavity  1558  is not fluidly connected to either of the first or second core cavities  1502 ,  1504 . 
     The first core cavity  1502 , in this embodiment, is a conventional cavity that can be sourced with cooling air from other cavities within the airfoil  1500  and/or from a cooling source that is located at an end of the airfoil body (e.g., at platform ends of a vane or at a root of a blade, depending on the configuration of the airfoil). The second core cavity  1504  is defined in an axial direction between a first cavity wall  1512  and a second cavity wall  1514 . In a circumferential direction, the second core cavity  1504  is defined by a first exterior wall  1516  and an opposing second exterior wall  1518 . Similar to that described above, the exterior walls  1516 ,  1518  of the second core cavity  1504  are “hot” walls that are exposed to hot gaspath air, and the first cavity wall  1512  and the second cavity wall  1514  are “cold” walls that are not exposed to the hot gaspath air (i.e., they are internal walls). 
     The first cavity wall  1512  includes one or more cavity impingement holes  1520 ,  1522 . A first set of cavity impingement holes  1520  is positioned and oriented within the first cavity wall  1512  to direct an aft-flowing impingement flow from the first core cavity  1502  into the second core cavity  1504  and at the first exterior side wall  1516 . A second set of cavity impingement holes  1522  is positioned and oriented within the first cavity wall  1512  to direct an aft-flowing impingement flow from the first core cavity  1502  into the second core cavity  1504  and at the second exterior side wall  1518 . 
     As shown, part of the directing of the impinging flow from the first core cavity  1502  to the second core cavity  1504  is achieved by the first cavity wall  1512  being contoured or shaped. In the present embodiment, the first cavity wall  1512  has a first surface  1524  that is angled or faces the first exterior wall  1516 . Similarly, the first cavity wall  1512  has a second surface  1526  that is angled or faces the second exterior wall  1518 . In addition to the first cavity wall  1512  having angled surfaces  1524 ,  1526 , in some embodiments, the cavity impingement holes  1520 ,  1522  may be angled such that the air is forced to imping upon the exterior walls  1516 ,  1518  of the second core cavity  1508 . After the air from the first core cavity  1502  impinges upon the exterior walls  1516 ,  1518  at least a portion of the air will form a high momentum jet along the exterior walls  1516 ,  1518  and flow out of the second core cavity  1504  through film exits  1528 ,  1530 . 
     For example, air flowing through the first cavity impingement hole  1520  will contact the interior surface of the first exterior wall  1516  and run in a forward direction along the first exterior wall  1516  to one or more first film exits  1528 , where the air will turn and exit the interior of the airfoil  1500  and flow along and exterior surface of the airfoil  1500  (e.g., along a pressure side exterior surface). Similarly, air flowing through the second cavity impingement hole  1522  will contact the interior surface of the second exterior wall  1518  and run in forward direction along the second exterior wall  1518  to one or more second film exits  1530 , where the air will exit the interior of the airfoil  1500  and flow along and exterior surface of the airfoil  1500  (e.g., along a suction side exterior surface). The flow of the impingement air along the interior surface of the exterior walls  1516 ,  1518  within the second core cavity  1504  causes a dead zone to form within the middle of the second core cavity  1504 . 
     Turning now to  FIG.  16   , a schematic illustration of a portion of an airfoil core structure  1600  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  1600  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  1600  includes two leading edge hybrid cavity cores  1602  and a leading edge feed cavity core  1603 . Further, the airfoil core structure  1600  includes a first core cavity core  1604  and a second core cavity core  1606 , arranged to form fluidly connected first and second core cavities. The leading edge hybrid cavity cores  1602  are connected to the leading edge feed cavity core  1604  by one or more forward impingement stems  1608  that are arranged to form impingement holes between a formed leading edge feed cavity and formed leading edge hybrid cavities. In contrast to the previously discussed embodiments, one or more cavity impingement stems  1610  connect the first core cavity core  1604  with the second core cavity core  1606  to form impingement holes between a formed first core cavity and a formed second core cavity. 
     The first core cavity core  1604  is arranged with a geometry to form a first cavity wall of a formed second core cavity with a first surface and a second surface, as shown and described above. The first and second surfaces are arranged with the cavity impingement stems  1610  to connect with the second core cavity core  1606 . Extending from and integral with the second core cavity core  1606  one or more film exit stems  1612  that are arranged to form the film exits as shown and described above. 
     In the above shown embodiments, the cavity impingement holes of the impingement wall are shown as misaligned in the radial direction. That is, the cavity impingement holes in one angled surface of the first cavity wall are located at a different radial position than the cavity impingement holes in the other angled surface of the first cavity wall. This arrangement is shown, for example, in the arrangement shown in the airfoil core structures of  FIGS.  6 ,  8 ,  10 ,  12 , and  16   . In these illustrations, the cavity impingement stems in one surface are not aligned in the radial direction with the cavity impingement stems of the other surface. In contrast, the cross-sectional illustrations of  FIGS.  5 A,  7 ,  9 ,  11 , and  15   , the cavity impingement holes are shown at the same radial position (i.e., shown in the cross-sectional slice of the respective airfoils) 
     Accordingly, in some embodiments, the cavity impingement holes of the impingement wall can be aligned between the two surfaces and in other embodiments, the cavity impingement holes may be misaligned in the radial direction. For example, when aligned, the impinging air flowing through a first cavity impingement hole in a first surface of the impingement wall can impact the first exterior wall at the same airfoil radial position (e.g., height within the airfoil) as the impinging air flowing through a second cavity impingement hole in a second surface of the impingement wall and impinging upon the second exterior wall. That is, the arrays of cavity impingement holes can have an aligned pattern. However, in other embodiments, radial staggering, misalignment, or offset of the impingement holes within the two surfaces of the impingement wall may be employed. The arrangement of the cavity impingement holes (e.g., staggered or aligned) may alter the nature of the dynamic vortices within the second core cavity. For example, an aligned configuration may result in a stable or relatively linear separation between the two vortices. In contrast, a staggered arrangement may result in a wavy or possibly turbulent interaction between neighboring dynamic vortices. Accordingly, vortex pressures may vary depending on the arrangement and configuration and/or angle of orientation and may result in different hot wall cooling stream behavior. 
     Turning to  FIG.  17   , a schematic illustration of a first cavity wall  1712  having a plurality of cavity impingement holes  1720 ,  1722  is shown. A first set of cavity impingement holes  1720  is shown formed in a first angled surface  1724  of the first cavity wall  1712  and a second set of cavity impingement holes  1722  is shown formed in a second angled surface  1726  of the first cavity wall  1712 . As illustratively shown, the impingement holes of the first set of cavity impingement holes  1720  are aligned in a radial direction with the impingement holes of the second set of cavity impingement holes  1722 . 
     Turning to  FIG.  18   , a schematic illustration of a first cavity wall  1812  having a plurality of cavity impingement holes  1820 ,  1822  is shown. A first set of cavity impingement holes  1820  is shown formed in a first angled surface  1824  of the first cavity wall  1812  and a second set of cavity impingement holes  1822  is shown formed in a second angled surface  1826  of the first cavity wall  1812 . As illustratively shown, the impingement holes of the first set of cavity impingement holes  1820  are offset in a radial direction from the impingement holes of the second set of cavity impingement holes  1822 . 
     Turning now to  FIG.  19   , a schematic illustration of an airfoil core structure  1900  in accordance with an embodiment of the present disclosure is shown. The airfoil core structure  1900  can be used to manufacture airfoils in accordance with the present disclosure. The airfoil core structure  1900  includes two leading edge hybrid cavity cores  1902 , a first core cavity core  1904  (forming, in part, a leading edge feed cavity core), and a second core cavity core  1906 , arranged to form fluidly connected first and second core cavities. The leading edge hybrid cavity cores  1902  are connected to the leading edge feed cavity core  1904  by one or more radially aligned forward impingement stems  1908   a,    1908   b  that are arranged to form aligned impingement holes in a radial direction between a formed leading edge feed cavity and formed leading edge hybrid cavities. The aligned forward impingement stems  1908   a,    1908   b  are arranged to form aligned impingement holes, e.g., impingement holes located at similar radial positions, for each of the leading edge hybrid cavities. Similarly, one or more aligned (in a radial direction) cavity impingement stems  1910   a,    1910   b  connect the first core cavity core  1904  with the second core cavity core  1906  to form radially aligned impingement holes between a formed first core cavity and a formed second core cavity that are aligned at radial positions in a formed airfoil. This arrangement is in contrast to the structures of the airfoil core structures of  FIGS.  6 ,  8 ,  10 , and  12   , which all shown unaligned or offset forward impingement stems and unaligned or offset cavity impingement stems. 
     Although the various above embodiments are shown as separate illustrations, those of skill in the art will appreciate that the various features can be combined, mix, and matched to form an airfoil having a desired cooling scheme that is enabled by one or more features described herein. Thus, the above described embodiments are not intended to be distinct arrangements and structures of airfoils and/or core structures, but rather are provided as separate embodiments for clarity and ease of explanation. 
     Advantageously, embodiments provided herein are directed to airfoil cooling cavity structures that combine the benefits of hybrid cavities and traditional core cavities. Further, advantageously, improved part life, improved cooling, and reduced weight can all be achieved from embodiments of the present disclosure. 
     As used herein, the term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application. For example, “about” may include a range of ±8%, or 5%, or 2% of a given value or other percentage change as will be appreciated by those of skill in the art for the particular measurement and/or dimensions referred to herein. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof. It should be appreciated that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” “radial,” “axial,” “circumferential,” and the like are with reference to normal operational attitude and should not be considered otherwise limiting. 
     While the present disclosure has been described with reference to an illustrative embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.