US 11,732,594 B2
Cooling assembly for a turbine assembly
Nicholas William Rathay, Rock City Falls, NY (US); Thomas Earl Dyson, Niskayuna, NY (US); and Brian Brzek, Niskayuna, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Nov. 27, 2019, as Appl. No. 16/697,242.
Prior Publication US 2021/0156265 A1, May 27, 2021
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/189 (2013.01) [F01D 5/186 (2013.01); F05D 2240/121 (2013.01); F05D 2240/304 (2013.01); F05D 2250/711 (2013.01); F05D 2260/202 (2013.01); F05D 2260/2212 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A cooling assembly comprising:
a coolant chamber disposed inside an airfoil of a turbine assembly, the coolant chamber configured to direct coolant inside the airfoil of the turbine assembly, the airfoil including a pressure side and a suction side and extending between a leading edge of the airfoil and a trailing edge of the airfoil along an axial length of the airfoil;
one or more inlet cooling channels extending from the coolant chamber to a passageway, the one or more inlet cooling channels fluidly coupled with the coolant chamber and configured to direct the coolant in a direction toward a trailing edge chamber of the airfoil, the trailing edge chamber disposed at the trailing edge of the airfoil and including an inner surface extending from the pressure side to the suction side, wherein the one or more inlet cooling channels are configured to direct at least a portion of the coolant to impinge on the inner surface of the trailing edge chamber; and
one or more outlet cooling channels extending from the passageway to the coolant chamber, the one or more outlet cooling channels configured to direct at least a portion of the coolant in one or more directions away from the trailing edge chamber of the airfoil, wherein at least one of the one or more inlet cooling channels is fluidly coupled with one of the one or more outlet cooling channels, and wherein the at least one of the one or more inlet cooling channels is fluidly separate from the trailing edge chamber.