Abstract:
An airfoil (55;200) is provided. The airfoil (55;200) comprises a crossover (232) and an impingement cavity (102,106,110) in fluid communication with the crossover (232) and having an internal surface. At least a portion of the internal surface comprises an undulating internal surface (237). A plurality of trip strips (236) may be disposed on the at least a portion of the internal surface to define the undulating internal surface (237). A gas turbine engine (20) and an internally-cooled engine part (55;200,250,252) are also provided.
Abstract:
A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.