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1. (WO2019005425) TURBINE AIRFOIL WITH TRAILING EDGE FEATURES AND CASTING CORE
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CLAIMS

1. A turbine airfoil (10) comprising:

an outer wall (12) delimiting an airfoil interior (11), the outer wall (12) extending span-wise along a radial direction of a turbine engine and being formed of a pressure sidewall (14) and a suction sidewall (16) joined at a leading edge (18) and at a trailing edge (20);

a trailing edge coolant cavity (40f) located in the airfoil interior (11) between the pressure sidewall (14) and the suction sidewall (16), the trailing edge coolant cavity (40f) being positioned adjacent to and extending out to the trailing edge (20) and in fluid communication with a plurality of coolant exit slots (28) positioned along the trailing edge (20); and

an internal arrangement (48) comprising an array of discrete fins (22) located aft of the trailing edge coolant cavity (40f) and along of the trailing edge (20), the array of discrete fins (22) configured to extend out into the interior (11) of the airfoil (10) without reaching the opposite interior sidewall, the discrete fins (22) extending out into the interior (11) of the turbine airfoil (10) alternating from the pressure sidewall (14) and the suction sidewall (16), the discrete fins (22) form a zigzaging cooling flow passage (50) axially along a chord-wise direction for a cooling fluid (Cf) between the pressure sidewall (14) and the suction sidewall (16).

2. The turbine airfoil (10) according to claim 1, wherein each discrete fin (22) is elongated in the radial direction.

3. The turbine airfoil (10) according to claims 1 or 2, wherein the internal arrangement (48) further comprises at least one axially running shelf (42) along the trailing edge of the turbine airfoil (10), wherein the at least one axially running shelf (42) provides structural support between the pressure sidewall (14) and the suction sidewall (16).

4. The turbine airfoil (10) according to claims 1, 2, or 3, wherein the internal arrangement (48) further comprising at least one row of radially running pins (44) along the trailing edge of the airfoil (12).

5. The turbine airfoil (10) according to claim 4, wherein the at least one row of radially running pins (44) is positioned within the internal arrangement (48) so that a row of the at least one row of radially running pins (44) is the last row of features along the trailing edge (20).

6. A casting core (140) for forming a turbine airfoil (10), comprising: a casting core element (140a) forming a trailing edge coolant cavity (40f) of the turbine airfoil (10), the core element (140) comprising a core pressure side (114) and a core suction side (116) extending in a span-wise direction, and further extending chord-wise from a core leading edge (118) toward a core trailing edge (120); and a plurality of discrete non-perforated indentations (122) are provided on the surface of the core pressure side (114) and the surface of the core suction side (116) along the core trailing edge (120), the discrete non-perforated indentations (122) forming discrete fins (22) along the interior (11) of the turbine airfoil (10) trailing edge portion aft of the trailing edge coolant cavity (40f) along the trialing edge (20) of the turbine airfoil (10), with the discrete non-perforated indentations (122) being interspaced radially by interstitial core elements (124) that form axial coolant passages (24) in the turbine airfoil (10) and interspaced axially by interstitial core elements (125) that form radial coolant passages (25) in the turbine airfoil (10).

7. The casting core according to claim 6, wherein each discrete non-perforated indentation (122) is elongated in the radial direction.

8. The casting core according to claims 6 or 7, wherein the discrete non-perforated indentations (122) on the core pressure side (114) and the core suction side (116) are spaced in a chord-wise direction and span-wise direction.

9. The casting core according to one of claims 6 through 8, wherein the discrete non-perforated indentations (122) on the core pressure side (114) and the discrete non-perforated indentations (122) on the core suction side (116) are alternately positioned in the chord-wise direction forming a zigzagging cross-section in the casting core and zigzagging flow passages in the turbine airfoil (10) casting.

10. The casting core according to one of claims 6 through 9, further comprising at least one row of radially running through hole perforations (144) through the core element (140a) located between span-wise ends of the core element (140a), the through hole perforations (144) forming a portion of an internal arrangement (48) in the trailing edge interior portion of the turbine airfoil (10), each radially running through hole perforation (144) extending from the core pressure side (114) to the core suction side (116).

11. The casting core according to claim 10, wherein the radially running through-hole perforations (144) is positioned within the internal arrangement (48) so that a row of the at least one row of radially running through hole perforation (144) is the last row of features along the core trailing edge (120).

12. The casting core according to one of claims 6 through 11, further comprising at least one axially running through-hole perforation (142) through the core element (140a) located between span-wise ends of the core element (140a), the at least one axially running through hole perforation (142) forming a portion of an internal arrangement (48) aft of the trailing edge coolant cavity (40f) and along the trailing edge (20) of the turbine airfoil (10), each axially running through hole perforation (142) extending from the core pressure side (114) to the core suction side (116), with each axially running through hole perforation (142) dividing the core trailing edge (120) into multiple radial cooling zones forming at least one axially running shelf (42) in the turbine airfoil (10) casting providing structural support between the pressure sidewall (14) and the suction sidewall (16) in the turbine airfoil (10).