Robert T Simmons

US Patent:

55119468, Apr 30, 1996

Filed:

Dec 8, 1994

Appl. No.:

8/361242

Inventors:

Gary E. Wheat - Madisonville KY
Barry T. Malone - Dawson Springs KY
Nicholas C. Palmer - Loveland OH
Robert C. Simmons - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A gas turbine engine airfoil includes a tip corner disposed at the juncture of the airfoil tip and trailing edge, and a cooling hole extends therethrough in direct flow communication with an internal cooling passage thereof. A cross-hole extends perpendicularly into the tip corner and into the cooling hole for discharging from the airfoil a portion of cooling air channeled into the cooling hole. The airfoil tip corner is therefore cooled by the air channeled through the cross-hole received from the intersecting cooling hole.

US Patent:

52617890, Nov 16, 1993

Filed:

Aug 25, 1992

Appl. No.:

7/935065

Inventors:

Don Butts - Swampscott MA
John G. Nourse - Gansevoort NY
Robert C. Simmons - Springdale OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 96R

Abstract:

A gas turbine engine blade includes an airfoil having first and second sides and a dovetail extending from the airfoil root. The airfoil includes a tip having a tip floor with first and second tip walls extending from the floor and spaced apart to define therebetween a tip pienum. The first tip wall is recessed at least in part from the airfoil first side to define an outwardly facing tip shelf, with the tip shelf and the first tip wall defining therebetween a trough. A plurality of cooling holes extend through the tip floor at the tip shelf for channeling cooling air from a flow channel inside the airfoil into the trough for cooling the blade tip.