Turbine blade with platform cooling

• US 6,210,111 B1
• Filed: 12/21/1998
• Issued: 04/03/2001
• Est. Priority Date: 12/21/1998
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Liang, George P.
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): WOO, RICHARD SUKYOON
• Application Number:
  US09/217,144
• Time in Patent Office: 834 Days
• Field of Search: 415/115, 415/116, 416/97 R, 416/97 A, 416/95, 416/96 R, 416/96 A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A cooled turbine blade for a gas turbine engine having a platform cooling supply channel that supplies cooling air to a plurality of cooling holes in the surface of the blade platform adjacent the trailing edge of the blade.

Claims

1. A blade for use in a gas turbine engine, said blade comprising:

a blade root;

an airfoil having a first end, a second end opposite said first end and in spaced relation thereto, a leading edge, and a trailing edge in spaced relation to said leading edge, said leading and trailing edges extending from said first end to said second end;

a blade platform having a first surface, a second surface, a first side and a second side opposite and in spaced relation to said first side, a platform cooling supply channel, a plurality of cooling holes in the second surface, and a plurality of cooling passages, said second surface opposite said first surface and in spaced relation thereto, said sides extending from said first surface to said second surface, said blade root connected to said first surface, said first end of said airfoil connected to said second surface, said platform cooling supply channel extending from said first side to said second side through said blade platform, and each of said cooling holes communicates with said platform cooling supply channel through one of said cooling passages;

wherein said platform cooling supply channel is substantially parallel to said second surface.

2. The blade of claim 1 wherein said cooling holes are located immediately adjacent said trailing edge.

3. The blade of claim 2 wherein said trailing edge is located immediately adjacent said first side.

4. The blade of claim 3 wherein said first and second sides each include a slot for receiving a feather seal, and said platform cooling supply channel communicates with said slots.