US 11,885,235 B2
Internally cooled turbine blade
Carlos Calixtro, Atlanta, GA (US); Alex D. Wong, South Windsor, CT (US); and Yanhu Guo, Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Feb. 15, 2022, as Appl. No. 17/651,179.
Prior Publication US 2023/0258090 A1, Aug. 17, 2023
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/186 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/30 (2013.01); F05D 2240/303 (2013.01); F05D 2240/304 (2013.01); F05D 2250/185 (2013.01); F05D 2260/202 (2013.01); F05D 2260/22141 (2013.01)] 6 Claims
OG exemplary drawing
 
1. An internally cooled turbine blade for use in a gas turbine engine, the internally cooled turbine blade comprising:
an airfoil with a concave sidewall and a convex sidewall extending spanwise between a platform and a blade tip, and chordwise between a leading edge and a trailing edge;
wherein internal surfaces of the airfoil define an internal cooling passage within the airfoil extending between a cooling air inlet and a plurality of air outlets, the internal cooling passage comprising:
a serpentine channel comprising a leading edge channel, an intermediate channel,
a trailing edge channel, and a plurality of turbulators;
wherein two adjacent rows of the plurality of turbulators are positioned within the trailing edge channel;
wherein:
the leading edge channel is positioned adjacent the leading edge of the airfoil;
the trailing edge channel is positioned adjacent the trailing edge of the airfoil; and
the intermediate channel is positioned between the leading edge channel and the trailing edge channel;
wherein the leading edge channel and the intermediate channel are separated by a first dividing wall that extends from a blade base toward the blade tip and wherein the first dividing wall includes a first radially outer end configured to turn cooling air flowing in the leading edge channel from a platform towards the blade tip into the intermediate channel such that the cooling air flows in the intermediate channel from the blade tip towards the platform, and
wherein the trailing edge channel and the intermediate channel are separated by a second dividing wall that extends from the platform toward the blade tip and wherein the second dividing wall includes a second radially inner end configured to direct cooling air flowing in the intermediate channel from the blade tip to the platform into the trailing edge channel such that the cooling air flows in the trailing edge channel from the platform towards the blade tip.