Patent ID: 8177492
Filing Date: 2012-05-15
Classification: F01D,F05D,Y02T

Abstract:
1. A cooled gas turbine engine component comprising: an elongate cooling passage comprising: one or more cooling inlet apertures extending through the first major surface and being displaced from the first end to define a space between the one or more cooling inlet apertures and one of the plurality of minor surfaces defining the first end, the one or more cooling inlet apertures being in flow communication with a coolant supply and the first end of the cooling passage; a cooling exit aperture extending through one of the plurality of minor surfaces at the second end; and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and the second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage and into the space; wherein the coolant flow obstruction comprises a chevron arranged with an apex pointed toward the cooling exit aperture, wherein the coolant flow obstruction and the one or more cooling inlet apertures are centered axially between minor surfaces.