Cooling arrangement

• US 8,240,994 B2
• Filed: 04/28/2008
• Issued: 08/14/2012
• Est. Priority Date: 05/18/2007
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Ireland, Peter T., Rawlinson, Anthony J.
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US12/149,165
• Publication Number:
  US 20080286116A1
• Time in Patent Office: 1,569 Days
• Field of Search: 416/97.R, 415/115
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence

Abstract

An aerofoil for a gas turbine engine comprising a pressure wall and a suction wall and defining leading and trailing edges, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an exterior surface. The array of holes comprise two groups, the holes of each group are angled to intersect the holes of the other group and are characterized in that the holes of at least one of the groups comprises two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.

Claims

1. An aerofoil for a gas turbine engine comprising:

a pressure wall and a suction wall, together defining leading and trailing edges and a passage into which is supplied a cooling fluid, at least one wall of the pressure wall and suction wall having an interior surface and exterior surface, and defining an array of cooling holes to allow the cooling fluid to flow from the interior surface to the exterior surface, the array of holes defining a first group and a second group, the holes of the first group are angled to intersect the holes of the second group, wherein the holes of at least one of the groups include two or more holes positioned at different angles to one another to vary a porosity of the at least one wall dependent on a varying temperature profile.

2. The aerofoil of claim 1, wherein the array of cooling holes includes a first row of holes.

3. The aerofoil of claim 2, wherein the array of cooling holes includes two or more rows of holes, each additional row defining an additional group.

4. The aerofoil of claim 3, wherein the two or more rows of holes are divergent.

5. The aerofoil of claim 3, wherein the two or more rows of holes are convergent.

6. The aerofoil of claim 1, wherein the array of holes includes two or more rows of holes.

7. The aerofoil of claim 1, wherein the holes of at least one of the groups are at different angles to one another.

8. The aerofoil of claim 1, wherein at least one of the groups includes consecutive holes inclined at increasingly steep angles to one another.

9. The aerofoil of claim 1, wherein more than one of the holes of both groups are consecutive holes inclined at increasingly steep angles to one another and are positioned so that they increase the porosity of the region.

10. The aerofoil of claim 9, wherein the porosity of the wall is greater at its exterior surface than at its interior surface.

11. The aerofoil of claim 1, wherein the porosity of the wall varies through the thickness of the wall.