Patent ID: 8961133
Filing Date: 2015-02-24
Classification: F01D,Y02T

Abstract:
1. An airfoil having a leading edge and a trailing edge for a gas turbine engine, comprising: an outer wall having a plurality of cooling air exit openings; an inner wall spaced apart from the outer wall, wherein the inner wall has a plurality of cooling air inlet openings; a plurality of flow migration dams, wherein the flow migration dams extend between the inner wall and the outer wall, the plurality of flow migration dams forming therebetween a plurality of cooling passages, wherein the cooling passages are in fluid communication with the cooling air inlet openings and with the cooling air exit openings; a cooling air supply passage in fluid communication with the cooling air inlet openings, wherein the cooling air supply passage is operative to supply cooling air to the cooling air inlet openings; and wherein each of the cooling passages formed by the flow migration dams includes a single cooling air inlet opening positioned proximate one of the leading edge and the trailing edge of the airfoil and a single cooling air exit opening positioned proximate the other of one of the leading edge and trailing edge of the airfoil opposite of the cooling air inlet opening and further includes one or more trip strips positioned between the cooling air inlet opening and the cooling air exit opening, each inlet and outlet opening oriented transverse to the cooling passage.