Patent ID: 7080971
Filing Date: 2006-07-25
Classification: F01D,Y10T

Abstract:
1. A blade for a rotor of a gas turbine engine, said blade having a longitudinal axis and a spanwise axis, said blade including a spar having a wall being generally elliptically shaped extending along said longitudinal axis and said spanwise axis and defining a central cavity, an attachment having a central bore disposed at the bottom portion of said spar, a depending portion extending longitudinally and downwardly from said wall fitting into said central bore, an attachment member extending laterally through openings formed in said attachment and said depending portion securing said spar to said attachment, a relatively thin aerodynamically shaped shell extending over said spar defining an airfoil and laterally spaced from said spar defining another longitudinal cavity, said shell having an upper edge attached to the upper end of said spar and a lower edge attached to said attachment, and support means on said shell and said spar supporting said shell to said spar and defining a load transmitting path for transmitting loads on said shell through said spar to said attachment, and a coolant flowing from the end of said spar through the central cavity and through holes in said spar to said another longitudinal cavity between said shell and said spar.