Patent ID: 7217088
Filing Date: 2007-05-15
Classification: F01D,F05D

Abstract:
1. A turbine airfoil, comprising: a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first platform at first end of the generally elongated airfoil, an inner core positioned internally in the generally elongated airfoil between the pressure and suction sides, a laminate layer joined to the inner core and forming the leading edge, trailing edge, pressure and suction sides, and a cooling system in the elongated airfoil formed from at least one internal cooling channel; and a cooling fluid preheating system in the first platform formed from at least one cooling channel in the first platform in communication with the cooling system in the elongated airfoil for preheating cooling fluids before the cooling fluids enter the cooling system in the elongated airfoil; wherein the at least one cooling fluid preheating system in the platform and the cooling system in the airfoil form a continuous cooling system uninterrupted with additional cooling fluids along the cooling system from a first end of the cooling system to an exhaust of the cooling system in a trailing edae of the airfoil; a shroud proximate to the first platform and comprising at least one cooling fluid supply hole, wherein the shroud forms a cooling supply manifold between the first platform that extends for a spanwise width of the generally elongated airfoil and wherein the cooling supply manifold is in fluid communication with a leading edge cooling fluid supply chamber in the cooling channel; wherein the cooling channel is formed from the leading edge cooling fluid supply chamber positioned proximate to the leading edge of the generally elongated airfoil extending generally spanwise within the airfoil, a trailing edge supply channel extending generally spanwise within the airfoil proximate to the trailing edge, a plurality of pressure side channels extending generally chordwise within the inner core of the airfoil proximate to the pressure side and from the leading edge cooling fluid supply chamber to the trailing edge supply channel, a plurality of suction side channels extending generally chordwise within the inner core of the airfoil proximate to the suction side and from the leading edge cooling fluid supply chamber to the trailing edge supply channel, and a plurality of trailing edge cooling channels extending generally chordwise within the airfoil and in fluid communication with the trailing edge supply channel and between the trailing edge supply channel and the trailing edge.