US 12,228,048 B2
Turbine engine airfoil
Thomas William Vandeputte, Scotia, NY (US); Paul Hadley Vitt, Liberty Township, OH (US); Daniel Endecott Osgood, Loveland, OH (US); and Brian David Keith, Cincinnati, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Oct. 16, 2023, as Appl. No. 18/487,495.
Application 18/487,495 is a continuation of application No. 17/894,307, filed on Aug. 24, 2022, granted, now 11,952,912.
Prior Publication US 2024/0167385 A1, May 23, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/18 (2006.01); F02C 7/12 (2006.01)
CPC F01D 5/18 (2013.01) [F02C 7/12 (2013.01); F05D 2260/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil for a turbine engine, comprising:
an outer wall having an exterior surface and bounding an interior, the outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line extending between the leading edge and the trailing edge;
a cooling hole extending through the outer wall between an inlet fluidly coupled to the interior and an outlet on the exterior surface;
a first thickness (T1) defined between the pressure side and the suction side in a first direction perpendicular to the mean camber line at a first location (L1) along the mean camber line, wherein the first thickness T1 is between 0.147 cm and 0.269 cm (0.147 cm≤T1≤0.269 cm);
a second thickness (T2) defined between the pressure side and the suction side in a second direction perpendicular to the mean camber line at a second location (L2) along the mean camber line, wherein the second thickness T2 is between 0.353 cm and 0.693 cm (0.353 cm ≤T2≤0.693 cm); wherein the second location L2 positioned farther from the trailing edge than the first location L1; and
a distance (dT) defined along the mean camber line between the first location L1 and the second location L2, wherein the distance dT is between 0.559 cm and 1.313 cm (0.559 cm≤dT≤1.313 cm);
wherein the first thickness T1 and the distance dT define a first ratio (R1) as R1=dT/T1, wherein the first ratio R1 is between 2.5 and 6.5 (2.5≤R1≤6.5);
wherein the cooling hole defines a cooling hole distance (dH) along the mean camber line between an aft edge of the cooling hole and the first location L1, wherein the cooling hole distance dH is between 0.048 cm and 0.533 cm (0.048 cm≤dH≤0.533 cm); and
wherein the cooling hole distance dH and the first thickness T1 define a second ratio (R2) as R2=dH/T1, wherein the second ratio R2 is between 0.3 and 3.0 (0.3≤R2≤3.0).