Cooled turbine blade

• US 6,328,531 B1
• Filed: 10/05/1999
• Issued: 12/11/2001
• Est. Priority Date: 08/05/1998
• Status: Expired due to Term

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Bariaud, Christian Bernard, Bil, Eric Stéphan
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/412,759
• Time in Patent Office: 798 Days
• Field of Search: 415/115, 416/95, 416/96.R, 416/96.A, 416/97.R, 416/248
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A cooled turbine blade comprising a platform and an aerofoil portion has a rebate formed in the aerofoil portion near the trailing edge on the pressure face side. This rebate extends from the platform to the blade tip, and slots for the escape of cooling air from an internal cavity of the aerofoil portion open into the rebate.

Claims

1. A cooled turbine blade comprising a platform and an airfoil portion extending from said platform, said airfoil portion having at least one internal cavity for the flow of cooling air, a leading edge, a trailing edge, first and second walls between said leading and trailing edges, and an outer edge remote from said platform and defining a tip of said blade, said first and second walls having external surfaces respectively defining a suction face and a pressure face of said airfoil portion, and said first and second walls having internal surfaces bounding said at least one internal cavity, said second wall terminating short of said trailing edge and defining an end surface which is substantially perpendicular to said pressure face defined by said second wall, said end surface and said internal surface of said first wall defining a rebate in said airfoil portion adjacent said trailing edge and extending from said platform to said tip of said blade, and said airfoil portion including means defining a plurality of slots opening in said end surface for the escape of cooling air from said at least one internal cavity to said trailing edge on the pressure face side of said airfoil portion, the slot nearest said platform opening partly in the platform, and said rebate extending into said platform facing said slot.

2. A cooled turbine blade according to claim 1, wherein said slots are separated by small bridges extending between said first and second walls.

3. A cooled turbine blade according to claim 1, wherein said means defining a plurality of slots opening in said end surface provides for the escape of cooling air directly from said at least one internal cavity to said trailing edge on the pressure face side of said airfoil portion.