Gas turbine aerofoil

• US 7,056,093 B2
• Filed: 05/19/2004
• Issued: 06/06/2006
• Est. Priority Date: 06/10/2003
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Self, Kevin P, Bennett, Paul N
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US10/848,013
• Publication Number:
  US 20040253106A1
• Time in Patent Office: 748 Days
• Field of Search: 415/115, 415/116, 416/97.R, 416/97.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 2230/12 by spark erosion methods
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine aerofoil with at least one internal cavity for conveying cooling fluid through the aerofoil has at least one internal cavity adjacent the aerofoil leading edge, at least one impingement cooling passage extending from, and in flow communication with the cavity, and at least one film cooling hole extending from, and in flow communication with, the cooling passage. The impingement passage extends into the aerofoil wall in the region of the leading edge and opens into the film cooling hole. The cooling hole extends through the aerofoil wall to an external surface of the aerofoil at a position downstream of the leading edge such that, in use, cooling fluid from the cavity exits the cooling passage into the cooling hole as an impingement jet against the internal surface of the cooling hole in the region of the leading edge.

Claims

1. A gas turbine aerofoil of the type having at least one internal cavity for conveying cooling fluid through the aerofoil for cooling the aerofoil in use, the aerofoil comprising:

at least one internal cavity adjacent the aerofoil leading edge;

at least one impingement cooling passage extending from, and in flow communication with, the least one internal cavity; and

at least one film cooling hole extending from, and in flow communication with, the at least one impingement cooling passage,

wherein the at least one impingement cooling passage extends into the aerofoil wall in the region of the leading edge and opens into, and terminates in, the at least one film cooling hole, the at least one film cooling hole passes through the aerofoil wall from the pressure surface side to the suction surface side of the aerofoil at a position downstream of the leading edge such that, in use, cooling fluid from the at least one internal cavity exits the at least one impingement cooling passage into the at least one film cooling hole as an impingement jet against the internal surface of the at least one film cooling hole in the region of the leading edge and exits the at least one film cooling hole as a film on the external surface of the aerofoil downstream of the leading edge.

2. An aerofoil as claimed in claim 1, wherein the at least one film cooling hole is substantially straight.

3. An aerofoil as claimed in claim 1, wherein the at least one film cooling hole is arcuate.

4. An aerofoil as claimed in claim 3, wherein the film cooling hole is angled with respect to at least one of the aerofoil pressure surface or the aerofoil suction surface at a respective pressure or suction side exit opening.

5. An aerofoil as claimed in claim 1, comprising a plurality of film cooling holes spaced apart in the spanwise direction of the aerofoil.

6. An aerofoil as claimed in claim 5, comprising a plurality of impingement cooling passages spaced apart in the spanwise direction of the aerofoil, wherein each impingement passage opens into a respective film cooling hole.

7. An aerofoil as claimed in claim 6, wherein each film cooling hole is provided with at least two impingement cooling passages spaced along a length of the film cooling hole.

8. An aerofoil as claimed in claim 5, wherein the impingement cooling passage comprises an elongate slot, or a series of slots positioned in end to end relation, extending in the spanwise direction of the aerofoil with the plurality of film cooling holes branching from the slot or slots at positions along the length of the aerofoil towards the pressure and suction surfaces of the aerofoil.

9. An aerofoil as claimed in claim 1, wherein the at least one film cooling hole is inclined with respect to a plane normal to the spanwise direction of the aerofoil.

10. An aerofoil as claimed in claim 1, wherein the at least one impingement cooling passage extends substantially normal to the longitudinal direction of the respective at least one film cooling hole.

11. An aerofoil as claimed in claim 1, wherein the aerofoil is cast and the at least one impingement cooling passage is integrally cast in the interior of the aerofoil.

12. An aerofoil as claimed in claim 1, wherein the at least one film cooling hole is a drilled hole.

13. An aerofoil as claimed in claim 12, wherein the at least one film cooling hole is an EDM or laser drilled hole.

14. A turbine rotor blade or nozzle guide vane comprising an aerofoil according to claim 1.