Patent ID: 7270519
Filing Date: 2007-09-18
Classification: F01D,F04D,F05D,Y10T

Abstract:
1. A method for fabricating a rotor blade for a gas turbine engine, said method comprising: forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge; forming a first rib that extends from the trailing edge to the leading edge and extends a first distance outward from the airfoil first side wall, such that the first rib is positioned between the airfoil tip and the airfoil root at a first radial distance from the tip, and such that the first rib facilitates reducing airflow spillage from flowing from a pressure side of the airfoil to a suction side of the airfoil past the airfoil tip wherein the first distance is substantially uniform across the full length of the first rib, and wherein the first radial distance from the tip is substantially uniform across the full length of the first rib; and forming a second rib that extends from the trailing edge to the leading edge and extends outwardly a second distance from the airfoil second side wall, such that the second rib is positioned between the airfoil tip and the airfoil root at a second radial distance from the tip, wherein the second radial distance is approximately equal to the first radial distance and the second distance from the airfoil second side wall is substantially uniform across the full length of the second rib and the second distance is approximately equal to the first distance from the airfoil first side wall; wherein the first rib comprises a leading end that is adjacent the leading edge and a trailing end that is adjacent to the trailing edge, and the second rib comprises a leading end that is adjacent the airfoil leading edge and a trailing end that is adjacent to the airfoil trailing edge.