Patent ID: 6435813
Filing Date: 2002-08-20
Classification: F01D,F05D

Abstract:
An airfoil for use in a gas turbine engine comprising:a body having a leading edge and a trailing edge opposite said leading edge, the body having an interior surface defining a hollow cavity in the airfoil having an inlet in communication with a source of cooling air for admitting cooling air to the cavity and an outlet for exhausting cooling air from the cavity thereby permitting cooling air to pass through the cavity from the inlet to the outlet to cool the airfoil body by convective heat transfer; and a partition within the cavity extending entirely across the cavity and dividing the cavity into a first cooling passage and a second cooling passage, said first cooling passage communicating with the inlet for delivering cooling air to the first passage and said second cooling passage communicating with the outlet for exhausting cooling air from the second passage, the partition having a cooling hole therein extending between said first passage and said second passage and permitting cooling air to pass from said first passage to said second passage, said cooling hole being sized and positioned with respect to the interior surface of the airfoil body for directing cooling air toward a portion of the interior surface of the airfoil body so the cooling air impinges upon the portion thereby cooling the body by impingement cooling, wherein cooling air entering the inlet of the cavity travels through said first passage for cooling the body by convective heat transfer, through the cooling hole for impinging upon the portion of the interior surface of the body thereby cooling the body by impingement cooling, through said second passage to cool the body by convective heat transfer, and out the outlet of the cavity.