US 12,215,601 B2
Air foil with staggered cooling hole configuration
Jaime G. Ghigliotty Rosado, Cabo Rojo, PR (US); Brandon W. Spangler, Vernon, CT (US); and Tracy A. Propheter-Hinckley, Rocky Hill, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Feb. 17, 2023, as Appl. No. 18/170,810.
Prior Publication US 2024/0280025 A1, Aug. 22, 2024
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/186 (2013.01) [F05D 2240/301 (2013.01); F05D 2240/303 (2013.01); F05D 2260/201 (2013.01); F05D 2260/202 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbine blade for a gas turbine engine, comprising:
An airfoil, the airfoil having a leading edge, a pressure side, a suction side and a trailing edge;
a plurality of internal cooling cavities including a leading edge cavity, a leading edge feed passage, pressure side cooling passages, suction side cooling passages and main body cavities; the leading edge cavity extending towards the suction side;
a first crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage; and
a second crossover row of cooling passages providing fluid communication between the leading edge cavity and the leading edge feed passage, a centerline of the first crossover row of cooling passages is located closer to the pressure side than a centerline of the second crossover row of cooling passages and the centerline of the second crossover row of cooling passages is located closer to the suction side than the centerline of the first crossover row of cooling passages, and wherein the second crossover row of cooling passages are radially staggered relative to the first crossover row of cooling passages and the centerline of the first crossover row of cooling passages and the centerline of the second crossover row of cooling passages intersects the leading edge cavity at a point forward of a line parallel to a pull angle or edge of the leading edge feed passage and the centerline of the first crossover row of cooling passages and the centerline of the second crossover row of cooling passages intersects a vertex of the leading edge feed passage.