Crossover cooled airfoil trailing edge
AssigneeGeneral Electric Company
InventorsRobert Francis Manning, Mohammad Esmail Taslim
Life of this patent
Estimating the term…
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.
Claims22
A turbine airfoil comprising:
- opposite pressure and suction sidewalls joined together at longitudinally extending leading and trailing edges, and spaced apart to define first and second flow channels separated by a bridge;
- a row of inlet holes extending through said bridge;
- a row of outlet holes extending from said second channel between said sidewalls toward said trailing edge;
- and
- a row of turbulator ribs disposed inside said second channel along said pressure sidewall and spaced from said suction sidewall, said ribs being longitudinally elongate and substantially colinear, and facing respective ones of said inlet holes for crossover impingement cooling said airfoil thereat by air channeled thereagainst.
A turbine airfoil comprising:
- opposite pressure and suction sidewalls joined together at longitudinally extending leading and trailing edges, and spaced apart to define first and second flow channels separated by a bridge;
- a row of inlet holes extending through said bridge;
- a row of outlet holes extending from said second channel between said sidewalls toward said trailing edge;
- a row of turbulator first ribs disposed inside said second channel along said pressure sidewall and spaced from said suction sidewall, said first ribs being longitudinally elongate and substantially colinear, and facing respective ones of said inlet holes for crossover impingement cooling said airfoil thereat by air channeled thereagainst;
- and
- a row of second turbulator ribs disposed inside said second channel along said pressure sidewall and spaced from said suction sidewall, and said second ribs being longitudinally elongate and substantially colinear, and spaced chordally from said row of first ribs.
Dependencies are inferred from the claim text.