Patent Number: 6,241,466

Title: Turbine airfoil breakout cooling

Abstract: A turbine airfoil includes pressure and suction sides extending between leading and trailing edges and defining an internal cooling air passage. A row of trailing edge holes is disposed in flow communication with the air passage behind the trailing edge. The airfoil is sized in conjunction with an adjacent airfoil for accelerating combustion gases along the pressure side at the trailing edge holes to a velocity at least as high as the velocity of the cooling air discharged from the holes.

Inventors: Tung; Stephen K. (Andover, MA), Weldon; Donald C. (Boxford, MA)

Assignee: General Electric Company

International Classification: F01D 5/18 (20060101); F01D 005/14 ()

Expiration Date: 06/05/2018