Turbine vane assembly

Patent metadata

Field	Value
Publication number	US-10428666-B2
Application number	US-201615375827-A
Country	US
Kind code	B2
Filing date	Dec 12, 2016
Priority date	Dec 12, 2016
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

First claim

What is claimed is:

1. A turbine vane for a gas turbine engine, comprising:
an engine centerline; and
an inner platform and an outer platform joined together by an airfoil, the airfoil including a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side,
the inner platform defines a plurality of inner cooling holes at geometric coordinates in conformance with Cartesian coordinate values of Xi, Yi, and Zi as set forth in Table 1, wherein each of the geometric coordinates is measured from the engine centerline, the Cartesian coordinate values of Table 1 are expressed in inches, the cooling holes have a diametrical surface tolerance relative to the coordinates of at least 0.017 inches (0.431 mm).

2. The turbine vane of claim 1 , wherein the plurality of inner cooling holes includes a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage, the plurality of first inner cooling holes being disposed proximate the leading edge and extending towards the suction side and the plurality of second inner cooling holes being disposed proximate the trailing edge and the suction side and extending towards the leading edge.

3. The turbine vane of claim 2 , wherein the plurality of inner cooling holes further includes a plurality of third inner cooling holes that are fluidly connected to the inner cooling passage and are disposed proximate the trailing edge and the pressure side and extend towards the leading edge.

4. The turbine vane of claim 3 , wherein the plurality of first inner cooling holes has a first diameter and the plurality of second inner cooling holes has a second diameter that is less than the first diameter.

5. The turbine vane of claim 1 , wherein the outer platform defines a plurality of outer cooling holes at geometric coordinates in substantial conformance with Cartesian coordinate values of Xo, Yo, Zo as set forth in Table 2, wherein each of the geometric coordinates is measured from the engine centerline, the Cartesian coordinate values of Table 2 are expressed in inches, the cooling holes have a diametrical surface tolerance relative to the coordinates of at least 0.017 inches (0.431 mm).

6. The turbine vane of claim 5 , wherein the plurality of outer cooling holes includes a plurality of first outer cooling holes and a plurality of second outer cooling holes that are fluidly connected to an outer cooling passage, the plurality of first outer cooling holes being disposed proximate the leading edge, and the plurality of second outer cooling holes being disposed proximate the trailing edge and the suction side extending towards the leading edge.

7. The turbine vane of claim 6 , wherein the plurality of outer cooling holes further includes a plurality of third outer cooling holes that are fluidly connected to the outer cooling passage, the plurality of third outer cooling holes are disposed proximate the pressure side and extend between the leading edge and the trailing edge.

8. The turbine vane of claim 7 , wherein a portion of the plurality of third outer cooling holes extend beyond the trailing edge and extend towards the suction side.

9. The turbine vane of claim 7 , wherein the plurality of first outer cooling holes has a first diameter and the plurality of second outer cooling holes has a second diameter that is less than the first diameter.

10. A turbine vane for a gas turbine engine, comprising:
an engine longitudinal axis;
an inner platform;
an outer platform spaced apart from the inner platform, the outer platform defines a plurality of outer cooling holes at geometric coordinates in conformance with Cartesian coordinate values of Xo, Yo, Zo as set forth in Table 2, wherein each of the geometric coordinates is measured from the engine longitudinal axis, the Cartesian coordinate values of Table 2 are expressed in inches, the cooling holes have a diametrical surface tolerance relative to the coordinates of at least 0.017 inches (0.431 mm); and
an airfoil having a chord length defined between a leading edge and a trailing edge, the airfoil joining the inner platform to the outer platform.

11. The turbine vane of claim 10 , wherein the inner platform defines a plurality of inner cooling holes at geometric coordinates in conformance with Cartesian coordinate values of Xi, Yi, and Zi as set forth in Table 1, wherein each of the geometric coordinates is measured from the engine longitudinal axis, the Cartesian coordinate values of Table 1 are expressed in inches, the cooling holes have a diametrical surface tolerance relative to the coordinates of at least 0.017 inches (0.431 mm).

12. The turbine vane of claim 11 , wherein the plurality of inner cooling holes includes a plurality of first inner cooling holes that extend circumferentially across the inner platform and are disposed proximate the leading edge.

13. The turbine vane of claim 12 , wherein the plurality of inner cooling holes includes a plurality of second inner cooling holes that extend between 60% and 100% of the chord length.

14. The turbine vane of claim 13 , wherein the plurality of inner cooling holes includes a plurality of third inner cooling holes that extend between 50% and 100% of the chord length.

15. The turbine vane of claim 10 , wherein the plurality of outer cooling holes includes a plurality of first outer cooling holes that extend circumferentially across the inner platform and are disposed proximate the leading edge.

16. The turbine vane of claim 15 , wherein the plurality of outer cooling holes includes a plurality of second outer cooling holes that extend between 50% and 100% of the chord length.

17. The turbine vane of claim 16 , wherein the plurality of outer cooling holes includes a plurality of third outer cooling holes that extend between 0% and 100% of the chord length.

18. A gas turbine engine, comprising:
a turbine section disposed adjacent to a combustor section, the turbine section including:
a turbine vane having an inner platform and an outer platform joined together by an airfoil having a pressure side and a suction side each extending between a leading edge and a trailing edge to define a chord length,
the inner platform defines a plurality of first inner cooling holes, a plurality of second inner cooling holes and a plurality of third inner cooling holes,
the plurality of first inner cooling holes being disposed proximate the leading edge and extend across the inner platform in a circumferentially oriented array from a point circumferentially spaced from the pressure side and towards the suction side,
the plurality of second inner cooling holes being disposed proximate the trailing edge and the suction side to extend between 60% and 100% of the chord length with a density exceeding that of the plurality of first inner cooling holes, and
the plurality of third inner cooling holes being disposed proximate the trailing edge and the pressure side to extend between 50% and 100% of the chord length with a density equaling that of the plurality of second inner cooling holes.

19. The gas turbine engine of claim 18 , wherein:
the outer platform defines a plurality of first outer cooling holes, a plurality of second outer cooling holes and a plurality of third outer cooling holes,
the plurality of first outer cooling holes being disposed proximate the leading edge with a density equaling that of the plurality of first inner cooling holes,
the plurality of second outer cooling holes being dispose

Assignees

• United Technologies Corp

Inventors

• Forbes John David
• Anselmi Gregory
• Botnick Christina E
• Kaufman Eleanor D
• Leon Jeffrey
• Levine Jeffrey R
• Mace Gerald M
• Nadeau Daniel C
• Kashyap Tania Bhatia
• Allen Richard N

Classifications

• F05D2240/81

  Cooled platforms · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F05D2260/202

  by film cooling · CPC title