Gas turbine engine aerofoil

• US 6,874,992 B2
• Filed: 11/15/2002
• Issued: 04/05/2005
• Est. Priority Date: 11/27/2001
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Dailey, Geoffrey M
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): White, Dwayne J.
• Application Number:
  US10/294,666
• Publication Number:
  US 20030133798A1
• Time in Patent Office: 872 Days
• Field of Search: 416/97.R, 416/97.A, 416/96.R, 415/115, 415/116
• US Class Current: 416/96.00R
• CPC Class Codes: F01D 5/187 Convection cooling

Abstract

An aerofoil blade or vane for a gas turbine engine comprises a body member having an inner end for mounting the blade on a shaft and an outer or tip end. A plurality of cooling passages are formed within the blade, the cooling passages comprising a plurality of inlet passages along which cooling air flows from the base towards the tip region of the blade and a plurality of return passages along which cooling air flows from the tip towards the base region of the blade. At least some of the passages are connected by a common chamber located within the tip region of the blade.

Claims

1. An aerofoil for a gas turbine engine comprising an elongated body member having a base and a tip region and having an inner end by means of which the aerofoil may be mounted on a shaft, an outer end, and a plurality of cooling passages comprising a plurality of inlet passages along which cooling air flows from said base towards said tip region of the aerofoil and a plurality of return passages along which cooling air flows from the tip region towards the region of said base of the aerofoil, of said inlet and return passages being connected by a common chamber located within the tip region of the aerofoil, interior wall members defining said inlet and return passages, each of said interior wall members extending from said region of said base toward said tip region end being spaced from said tip region to leave said common chamber unobstructed for the flow of cooling air.

2. An aerofoil as claimed in claim 1 having a leading edge region and a trailing edge region wherein one of said passages is farmed within the leading edge region of said aerofoil and includes an opening at its radially inner end through which cooling fluid may be introduced into the passage.

3. An aerofoil as claimed In claim 1 wherein at least one of said passages Is in communication with the exterior of said aerofoil to enable discharge of said cooling fluid from said aerofoil.

4. An aerofoil as claimed in claim 3 wherein said aerofoil has convex and concave walls and at least one of the convex and concave walls of said aerofoil is provided with an opening connected to the base of a cooling passage so as to provide an exhaust hole for cooling air.

5. An aerofoil for a gas turbine engine comprising an elongated body member having an inner end by means of which the aerofoil may be mounted on a shaft, an outer end, and a plurality of cooling passages comprising a plurality of inlet passages along which cooling air flows from the base towards the tip region of the aerofoil and a plurality of return passages along which cooling air flows from the tip towards the base region of the aerofoil, at least some of said inlet and return passages being connected by a common chamber located within the tip region of the aerofoil wherein at least one of said passages is in communication with the exterior of said aerofoil to enable discharge of said cooling from said aerofoil and wherein said cooling passage is arranged to receive cooling fluid at its radially outer opening.