Patent ID: 9739155
Date: 2017-08-22
CPC Classifications: F01D,F05D,Y02T

Claim:
1. A turbine blade comprising an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant, the turbine blade further comprising: a rib configuration that partitions the chamber of the airfoil into radially extending flow passages; wherein a first flow passage includes a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration; wherein the canted configuration comprises each of the turbulators being canted relative to a reference line on the first side that has a constant radial height; wherein the canted configuration of the turbulators comprises an acute angle of at least 20 degrees being formed between each of the turbulators and one of the reference lines; wherein the first flow passage is defined by radially extending sides that include: a second side that is opposite the first side, and two additional sides, a third side and a fourth side, that flank the first side and extend adjacent thereto; wherein each of the turbulators comprises an elongated, steep-sided protrusion; wherein the first side comprises a traverse rib; and wherein the traverse rib and the turbulators are configured to extend through a camber line of the airfoil.