Rolls-royce Corporation

Clive Grafton-Reed

Steven Aleksy Radomski

Dale Edward Evans

James Kell

Dragos Aurelian Axinte

Andrea Lelio Maurizio

Ian Crowston

Steven Radomski

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Vane arrangement for a gas turbine engine

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

A method of laser processing a component within an assembled apparatus using a boroscope, which includes a working head having first and second ends. A first optical fiber extends through the boroscope to a position between the first and second ends. A second optical fiber extends through the boroscope to the second end. A laser optical fiber extends through the boroscope. At least one lens is arranged between the first and second ends of the working head and a mirror is gimballed to the second end. The laser optical fiber directs laser light transmitted through the laser optical fiber onto the lens and then onto the mirror. A first LED is arranged at a position between the first and second ends of the working head and a second LED is arranged at the second end and an actuator device adjust the position of the mirror.

Method of laser processing a component within an assembled apparatus using a boroscope

A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

Manufacture of hollow aerofoil

A boroscope includes a working head having first and second ends. A first optical fiber extends through the boroscope to a position between the first and second ends. A second optical fiber extends through the boroscope to the second end of the working head. A laser optical fiber extends through the boroscope. At least one lens is arranged between the first end and the second end of the working head and a mirror is gimballed to the second end of the working head. The laser optical fiber directs laser light transmitted through the laser optical fiber onto the lens and then onto the mirror. A first LED is arranged at a position between the first end and the second end of the working head and a second LED is arranged at the second end of the working head and an actuator devices adjust the position of the mirror.

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Leicester, United Kingdom

Clive Grafton-Reed