Cooled turbine airfoil structures

• US 9,267,381 B2
• Filed: 09/28/2012
• Issued: 02/23/2016
• Est. Priority Date: 09/28/2012
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Morris, Mark C., Kettinger, Jon, Krmpotich, Deane, Harman, Stuart Andrew, Malak, Malak Fouad
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Brockman, Eldon
• Application Number:
  US13/631,126
• Publication Number:
  US 20140093389A1
• Time in Patent Office: 1,243 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/183 Blade walls being porous
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/234 of the generator by compressor inlet air
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

In accordance with an exemplary embodiment, disclosed is an air-cooled turbine blade having an airfoil shape, including a convex suction side wall, a concave pressure side wall, the walls including an interior surface that defines an interior with the blade, a suction side flow circuit formed within the blade interior, a pressure side flow circuit formed within the blade interior; and a trailing edge pin bank positioned aft of the suction side and pressure side flow circuits. The turbine blade includes a wishbone-shaped architecture at a transition point between the suction side flow circuit and the pressure side flow circuit and the trailing edge pin bank.

Claims

1. An air-cooled turbine blade having an airfoil shape, comprising:

a multi-walled convex suction side wall comprising a convex-side outer wall and a convex-side inner wall, wherein a space between the convex-side outer wall and the convex-side inner wall defines a convex-side cooling air passage;

a multi-walled concave pressure side wall comprising a concave-side outer wall and a concave-side inner wall, wherein a space between the concave-side outer wall and the concave-side inner wall defines a concave-side cooling air passage, each of the convex-side and concave side inner walls including an interior surface that defines an interior with the blade;

a suction side flow circuit formed within the convex-side cooling air passage;

a pressure side flow circuit formed within the concave-side cooling air passage; and

a plurality of pins at a trailing edge of the blade and positioned aft of the suction side and pressure side flow circuits,

wherein the turbine blade comprises, in a mid-section extending from the suction side flow circuit and the pressure side flow circuit to the plurality of pins at the trailing edge, a generally Y-shaped cross-section defined with a first end of the Y-shape extending from the suction side flow circuit to the plurality of pins and a second end of the Y-shape extending from the pressure side flow circuit to the plurality of pins, an open space being present between the first and second ends of the Y-shape in the mid-section, and wherein the pressure side flow circuit comprises a plurality of pins positioned on the concave side outer wall of the pressure side flow circuit extending towards, but not in contact with, the concave side inner wall of the pressure side flow circuit.

2. The turbine blade of claim 1, further comprising a variable wall thickness between inner and outer walls of one or both of the suction side flow circuit and the pressure side flow circuit.

3. The turbine blade of claim 1, comprising a plurality of multi-angle forward swept cooling holes.

4. The turbine blade of claim 1, further comprising a platform comprising a first external airfoil fillet on the suction side and a second external airfoil fillet on the pressure side, wherein the external airfoil fillet on the suction side is at least 10% greater in size than the external airfoil fillet on the pressure side.

5. The turbine blade of claim 4, wherein the platform is tapered at an aft end thereof.