COOLED TURBINE BLADE WITH LEADING EDGE FLOW REDIRECTION AND DIFFUSION

摘要

A cooled turbine blade (440) having a base (442) and an airfoil (441), the base (442) including cooling air inlet (481) and an internal cooling air passageway (482), and the airfoil (441) including an internal heat exchange path (470) beginning at the base (442) and ending at a cooling air outlet (471) at the trailing edge (447) of the airfoil (441). The airfoil (441) also includes a "skin" (460) that encompasses a tip wall (461), an inner spar (462), a leading edge rib (472), and a leading edge air deflector (475). The leading edge rib (472) is configured to form a leading edge chamber (463) in conjunction with the leading edge (446) of the skin (460). The leading edge air deflector (475) is shaped and positioned such that cooling air leaving the leading edge chamber (463) is both turned and diffused.