CPC F01D 5/186 (2013.01) [F05D 2240/307 (2013.01); F05D 2250/74 (2013.01); F05D 2260/202 (2013.01)] | 16 Claims |
1. A turbine blade for use in a gas turbine engine, the turbine blade comprising:
a plurality of cooling holes positioned adjacent a tip of the turbine blade, wherein the plurality of cooling holes comprises six cooling holes, including a first cooling hole, a second cooling hole, a third cooling hole, a fourth cooling hole, a fifth cooling hole, and a sixth cooling hole;
wherein each of the plurality of cooling holes extend from an interior of the turbine blade through a turbine blade pressure-side sidewall toward a trailing edge of the turbine blade at an acute angle with respect to a vertical axis extending from a base of the turbine blade to the tip of the turbine blade;
wherein each of the plurality of cooling holes are offset from the tip of the turbine blade by less than 2.0% of a total span between the base of the turbine blade and the tip of the turbine blade; and
wherein:
the first cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 25 degrees and 30 degrees with respect to the vertical axis;
the second cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 25 degrees and 30 degrees with respect to the vertical axis;
the third cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 25 degrees and 30 degrees with respect to the vertical axis;
the fourth cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 25 degrees and 30 degrees with respect to the vertical axis;
the fifth cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 25 degrees and 30 degrees with respect to the vertical axis; and
the sixth cooling hole extends toward the trailing edge of the turbine blade at an angle ranging between 55 degrees and 60 degrees with respect to the vertical axis.
|