Turbine blade cooling hole arrangement
AssigneeRtx Corporation
InventorsEmma J. Place, Dominic J. Mongillo, Jr., Jeremy B Fredette
Life of this patent
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Abstract
Disclosed is a turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes being located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.
Claims20
A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.
A turbine rotor assembly for a gas turbine engine, comprising:
- a rotor disk;
- a plurality of turbine blades secured to the rotor disk, each turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in an airfoil of each turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on each turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of each turbine blade.
A method of cooling an airfoil of a turbine blade of a gas turbine engine, comprising:
- forming a plurality of cooling holes in an airfoil of the turbine blade, wherein the plurality of cooling holes are located in the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.
Dependencies are inferred from the claim text.