High pressure turbine vane cooling hole distrubution
First Claim
1. A turbine vane for a gas turbine engine comprising an airfoil portion defined by a perimeter wall surrounding an enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the enclosure and a gaspath of the gas turbine engine, the plurality of cooling holes including first, second, third and fourth rows of holes, the first and second rows of holes extending at least substantially radially adjacent a leading edge of the airfoil portion, the third now of holes extending at least substantially radially on one side of the airfoil in proximity of a trailing edge thereof, and the fourth row of holes extending at least substantially radially on the opposed side of the airfoil in proximity of the leading edge, the first, second, third and fourth rows of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
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Accused Products
Abstract
A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
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Citations
20 Claims
- 1. A turbine vane for a gas turbine engine comprising an airfoil portion defined by a perimeter wall surrounding an enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the enclosure and a gaspath of the gas turbine engine, the plurality of cooling holes including first, second, third and fourth rows of holes, the first and second rows of holes extending at least substantially radially adjacent a leading edge of the airfoil portion, the third now of holes extending at least substantially radially on one side of the airfoil in proximity of a trailing edge thereof, and the fourth row of holes extending at least substantially radially on the opposed side of the airfoil in proximity of the leading edge, the first, second, third and fourth rows of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
- 10. A turbine stator assembly for a gas turbine engine comprising a plurality of vanes, each vane having an airfoil portion defined by a perimeter wall enclosing a cooling cavity, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the cooling cavity and a gaspath of the gas turbine engine, the plurality of cooling holes including first, second, third and fourth sets of holes, the first and second sets of holes extending adjacent a leading edge of the airfoil portion, the third set of holes extending on one side of the airfoil in proximity of a trailing edge thereof, and the fourth set of holes extending on the opposed side of the airfoil in proximity of the leading edge, the first, second, third and fourth sets of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, each hole having a central axis extending through point 1 and point 2 located at least substantially in accordance with X, Y, Z Cartesian coordinate values set forth in Table 3.
- 17. A high pressure turbine vane comprising an airfoil having a perimeter wall surrounding a cooling cavity, the perimeter wall having an outer surface lying substantially on the points of Table 2, the airfoil extending between platforms defined generally by at least some of the coordinate values given in Table 1, wherein a fillet radius is applied around the airfoil between the airfoil and platforms, the perimeter wall having a plurality of cooling holes defined therethrough in fluid communication with the cooling cavity, the plurality of cooling holes including first, second, third and fourth sets of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
Specification