TURBINE BLADE

摘要

An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

主权项

1. An airfoil for a gas turbine engine, the airfoil comprising:
an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a root and a tip; and a cooling circuit located within the airfoil and comprising:
a supply passage extending from the root toward the tip and fluidly coupled to the cooling air inlet passage at the root,a pin bank passage in fluid communication with the supply passage and extending between the root and the tip, with a plurality of pins located within the pin bank passage and functionally dividing the pin bank passage into at least first and second sub-circuits, andat least first and second cooling passages fluidly coupled to a corresponding one of the first and second sub-circuits and arranged on opposite sides of the pin bank passage; wherein cooling air from the cooling air inlet passage travels through the supply passage in a first radial direction, returns through the sub-circuits in a second radial direction, opposite the first radial direction, and then flows through the first and second cooling passages in the first radial direction.