Enhanced turbine airfoil cooling
First Claim
1. A turbine airfoil for a gas turbine engine said turbine airfoil having an end and including a plurality of generally radially extending cooling passages therein, at least one of said cooling passages terminating at said end of said airfoil and including turbulence promoters therewithin, said turbulence promoters extending substantially completely to said end of said airfoil and wherein said end includes an outer shroud and said at least one of said cooling passages and said turbulence promoters terminates at an outer surface of said shroud.
4 Assignments
0 Petitions
Accused Products
Abstract
The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.
36 Citations
29 Claims
- 1. A turbine airfoil for a gas turbine engine said turbine airfoil having an end and including a plurality of generally radially extending cooling passages therein, at least one of said cooling passages terminating at said end of said airfoil and including turbulence promoters therewithin, said turbulence promoters extending substantially completely to said end of said airfoil and wherein said end includes an outer shroud and said at least one of said cooling passages and said turbulence promoters terminates at an outer surface of said shroud.
- 15. A turbine blade comprising an airfoil portion terminating at a radially outer portion thereof at a tip shroud, said airfoil portion including at least one radially extending cooling passage, terminating at an outer surface of said tip shroud, said at least one radially extending cooling passage including turbulence promoters distributed along at least a portion of the length of said at least one passage and to said termination of said end thereof at said tip shroud.
-
23. A method of enhancing the internal convective cooling of an end portion of a turbine airfoil having a tip shroud and at least one internal cooling passage which terminates at said end portion of said turbine airfoil and said tip shroud and is provided with turbulence promoters therewithin along a medial portion to a tip portion thereof, said method comprising the steps of:
-
determining the location of the radially endmost of said turbulence promoters and said tip shroud; inserting a cutting tool into said at least one passage from end portion of said airfoil and said tip shroud and machining turbulence promoters into said at least one passage from said termination of said cooling passage to said radially endmost turbulence promoter. - View Dependent Claims (24, 25, 26, 27, 28, 29)
-
Specification