Patent ID: 8840363
Filing Date: 2014-09-23
Classification: F01D,F05D

Abstract:
1. An airfoil in a gas turbine engine comprising: an outer wall including a leading edge, a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading edge and the trailing edge; a cooling fluid cavity defined in the outer wall and extending generally radially between the inner end and the outer end of the outer wall, the cooling fluid cavity receiving cooling fluid for cooling the outer wall; and a plurality of cooling fluid passages in fluid communication with the cooling fluid cavity, the cooling fluid passages comprising zigzagged passages that include alternating angled sections, each section having both a radial component and a chordal component, the cooling fluid passages extending from the cooling fluid cavity toward the trailing edge of the outer wall and receiving cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge, wherein the cooling fluid passages are gradually tapered in a circumferential direction as the cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall, the circumferential direction defined between the pressure side and the suction side of the outer wall, and wherein radial heights of the cooling fluid passages are greater than radial spaces between radially adjacent cooling fluid passages.