Film cooling of turbine airfoil wall using mesh cooling hole arrangement

• US 5,370,499 A
• Filed: 02/03/1992
• Issued: 12/06/1994
• Est. Priority Date: 02/03/1992
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lee, Ching-Pang
• Primary Examiner(s): Nelson, Peter A.
• Application Number:
  US07/830,144
• Time in Patent Office: 1,037 Days
• Field of Search: 476/97 R, 476/97 A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least at a pressure side and extending from an internal chamber to the airfoil exterior. The cooling holes of each plurality extend generally parallel to one another. The cooling holes of the first and second pluralities intersect so as to define a plurality of spaced apart internal solid nodes in the side wall having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes which extend between and along opposite sides of adjacent nodes and a plurality of flow intersections which interconnect the hole portions of the cooling holes and are disposed between the corners of adjacent nodes. The sides of the nodes have lengths which are greater than the widths of the hole portions between adjacent nodes such that, when cooling fluid is passed through the cooling holes, jet flow actions are created through the hole portions which in turn generate jet interactions at the flow intersections to cause restriction of air flow and produce a pressure drop. Also, the cooling holes have flow inlets at the internal surface and flow outlets at the external surface of the airfoil side wall. The area of the flow inlets is substantially less than the area of the flow outlets.

Claims

1. In a turbine airfoil having leading and trailing edges and opposite side walls defining pressure and suction sides and merging together at said leading and trailing edges, said side walls having internal surfaces defining a hollow interior chamber for communication of cooling air flow to said side walls, said side walls having external surfaces spaced from the internal surfaces and extending generally in the direction of gas flow past said airfoil from said leading edge to said trailing edge of said airfoil, a mesh cooling hole arrangement comprising:

(a) a first plurality of cooling holes extending generally parallel to one another between said internal and external surfaces of said side wall at least at said pressure side of said airfoil and from said internal chamber to the exterior of said airfoil; and

(b) a second plurality of cooling holes extending generally parallel to one another between said internal and external surfaces of said side wall at least at said pressure side of said airfoil and from said internal chamber to the exterior of said airfoil;

(c) said cooling holes of said second plurality intersecting said cooling holes of said first plurality so as to define a plurality of spaced apart internal solid nodes in said side wall having pairs of opposite sides interconnected by pairs of opposite corners, a multiplicity of hole portions extending between and along opposite sides of adjacent nodes and a plurality of the flow intersections interconnecting said hole portions and disposed between said corners of adjacent nodes;

(d) said sides of said nodes having lengths greater than the widths of said hole portions between said nodes such that when cooling fluid is passed through said first and second pluralities of cooling holes in said airfoil side wall a jet flow action is created in said hole portions between said sides of adjacent nodes which generates jet interactions at said flow intersections between said corners of adjacent nodes to cause restriction of air flow and produce a pressure drop.

2. The arrangement as recited in claim 1, wherein said cooling holes of said first and second pluralities have flow inlets at said internal surface of said airfoil side wall and flow outlets at said external surface of said airfoil side wall, the ones of said nodes being positioned adjacent said cooling hole inlets being substantially greater in size than said nodes positioned adjacent said cooling hole outlets such that the area of said cooling hole inlets is substantially less than the area of said cooling hole outlets.

3. The arrangement as recited in claim 2, wherein said flow outlets of said cooling holes are displaced downstream of said flow inlets of said cooling holes relative to the direction of gas flow past said external surface of said side wall of said airfoil.

4. The arrangement as recited in claim 1, wherein said cooling holes of said first and second pluralities extend in inclined relation relative to said external surface of said side wall of said airfoil and the direction of gas flow past said external surface of said side wall of said airfoil.

5. The arrangement as recited in claim 1, wherein said flow outlets of said cooling holes of said first and second pluralities are aligned in a row extending in generally transverse relation to the direction of gas flow past said external surface of said side wall of said airfoil.

6. The arrangement as recited in claim 1, wherein said cooling holes of said first and second pluralities are aligned with one another in a plane extending in inclined relation relative to said external surface of said side wall of said airfoil and the direction of gas flow past said external surface of said side wall of said airfoil.

7. The arrangement as recited in claim 1, wherein said cooling holes of said first and second pluralities are substantially straight and equal to one another in axial length.

8. The arrangement as recited in claim 1, wherein said cooling holes of said first and second pluralities are substantially uniform in cross-sectional size.

9. In a turbine airfoil having leading and trailing edges and opposite side walls defining pressure and suction sides and merging together at said leading and trailing edges, said side walls having internal surfaces defining a hollow interior chamber for communication of cooling air flow to said side walls, said side walls having external surfaces spaced from the internal surfaces and extending generally in the direction of gas flow past said airfoil from said leading edge to said trailing edge of said airfoil, a mesh cooling hole arrangement comprising:

(a) a first plurality of cooling holes extending generally parallel to one another between said internal and external surfaces of said side wall at least at said pressure side of said airfoil and from said internal chamber to the exterior of said airfoil; and

(b) a second plurality of cooling holes extending generally parallel to one another between said internal and external surfaces of said side wall at least at said pressure side of said airfoil and from said internal chamber to the exterior of said airfoil;

(c) said cooling holes of said second plurality intersecting said cooling holes of said first plurality so as to define a plurality of spaced apart internal solid nodes in said side wall having pairs of opposite sides interconnected by pairs of opposite corners;

(d) said cooling holes of said first and second pluralities having flow inlets at said internal surface of said airfoil side wall and flow outlets at said external surface of said airfoil side wall, ones of said nodes being positioned adjacent said cooling hole inlets being substantially greater in size than ones of said nodes being positioned adjacent said cooling hole outlets such that the area of said cooling hole inlets is substantially less than the area of said cooling hole outlets.

10. The arrangement as recited in claim 9, wherein said flow outlets of said cooling holes are displaced downstream of said flow inlets of said cooling holes relative to the direction of gas flow past said external surface of said side wall of said airfoil.