Abstract: A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row of inlet holes, and a row of outlet holes extends from the second channel toward the trailing edge of the airfoil. A row of turbulator ribs is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.

Abstract: A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row of inlet holes, and a row of outlet holes extends from the second channel toward the trailing edge of the airfoil. A row of turbulator ribs is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.

Abstract: A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.