Turbine vane for gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsChristopher Cosher, Alex J. Schneider, Bret M. Teller
Life of this patent
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Abstract
A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1.
Claims18
A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates:
- HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of 0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.
A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes providing fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates:
- TCA, TCB, TDA, TDB, and TDC of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates, wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.
A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes providing fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates:
- TBA and TBE of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.
A turbine stator assembly for a gas turbine engine comprising a plurality of vanes, each vane having a plurality of cooling holes defined therein for providing fluid communication to a surface of each vane, the plurality of cooling holes including holes noted by the following coordinates:
- HDA, HDB, HEA, HEB, SAA, SAB and HCA of Table 1, wherein X, Y and Z coordinate values in Table 1 are distances given in inches from a point of origin O, which is a center point of a circular opening that is cast into a bottom surface of the vane and the coordinates of Table 1 have in average a tolerance of ±0.100 inches with respect to X, Y and Z axes of the coordinates wherein for each hole, surface breakout corresponds to an intersection of a central axis of the cooling hole with an outer surface of the vane.
Dependencies are inferred from the claim text.