Rolls-royce Corporation

Twi Gmbh

John Harold Boswell

Daniel Clark

Ian Tibbott

Jeffrey Allen

Andrew Robert Walpole

Kevin Goodwin

Terence Ivan Simpson

Charles Richard Carpenter

Andrew Richard Kennedy

Andrew David Slater

Carl Hauser

Neil Preece

Amanda Barbara Borland

Phillip John Crosby

Martin Tuffs

Paul Owen Hill

Martin John Rawson

George William Whitehurst

A method () for fabricating an integral assembly () is disclosed. The method comprises providing () a first workpiece () having a first surface () and a second workpiece () having a second surface (), performing a first bonding process between the first surface () of the first workpiece () and the second surface () of the second workpiece () to form a sub-assembly workpiece (), and performing a second bonding process between a third surface () of the sub-assembly workpiece () and a fourth surface () of a third workpiece () to form the integral assembly (). The material properties of the first workpiece () are different from material properties of the third workpiece ().

Bladed disc and method of manufacturing the same

A method of attaching a projection to a thin walled component, the thin walled component having a first surface and an opposite second surface, the method comprises the steps of:

Method of attaching a projection to a thin walled component

A method includes forming a mold, the mold having at least one mold portion defining the shape of an element to be removed from the component in a subsequent manufacturing step and having a reduced cross-sectional area. The at least one mold portion includes at least one recess which further reduces the cross sectional area of the cavity and increases the surface area of the at least one mold portion or the at least one mold portion includes a plurality of projections which increase the surface area of the least one mold portion thereby increasing radiative heat loss from the at least one mold portion during the process. A mold for use in this method and a turbine blade formed using this method, are also provided.

Component casting

A powder deposition apparatus for producing a component comprises a base plate, an annular stack of heating elements, accommodating the base plate, one or more insulating elements, being interleaved between adjoining heating elements, a mechanism operable to deposit a plurality of layers of a powder material onto the base plate, and a laser energy source operable to selectively fuse a portion of the deposited layer. The annular stack of heating elements is sized such that a predetermined clearance is defined between the component and the annular stack of heating elements. As successive layers of the powder material are deposited onto the base plate, the base plate is lowered into the stack of heating elements, the heating elements being actuated sequentially to maintain a pre-determined temperature profile in the deposited layers.

Method for producing a component and an apparatus for working the method

A method of manufacturing a component from a nickel-based superalloy comprises the steps of:

Method of manufacturing a component from a nickel-based superalloy

A method and apparatus for removing a canisterfrom a componentby forming an openingin the canister wall thicknessand introducing a pressurised fluid into the openingcausing hydrostatic pressure build up between an internal canister surfaceand the component, leading to the removal of the canister. This method and apparatus obviates the need to expend significant machining or chemical processing to remove the canister

Method and apparatus for separating a canister and component

An arrangement for heating and cooling a turbine casing of a gas turbine engine, the arrangement comprising an inboard duct, adjacent to an inboard surface of the turbine casing, an outboard facing wall of the inboard duct having a plurality of impingement holes opening towards the inboard surface of the casing, through which temperature control fluid can pass from within the inboard duct to impinge upon the inboard surface of the turbine casing.

Tip clearance control for turbine blades

A method of forming a bonded assembly (). The method comprises: providing at least first and second parts () of an assembly () to be bonded; assembling the first and second parts () in a required relative position to define a bond interface region therebetween; sealing part way along an edge () of the bond interface region using laser beam welding to define a cavity between the first and second parts (); in a vacuum environment, sealing the remainder of the edge () of the bond interface region using electron beam welding to form a fluid tight seal around the cavity; and applying heat and pressure to an external surface of the cavity to diffusion bond the first and second parts () together.

Method of forming a bonded assembly

A casting arrangement for the single crystal casting of a component in which a common feed for molten metal is provided with a filtration arrangement that incorporates an annular filter. Outlets in a housing surrounding the filter direct the filtered molten metal on to a seed crystal and into a spiral grain selector.

Single crystal casting apparatus

A method is disclosed for measuring the crystallographic orientation of a component cast by a directional solidification process. The method comprises the steps of: illuminating at least a region of the component surface with substantially coherent light, measuring the mean angle and intensity of the light reflected from the component surface, and correlating said mean angle and intensity to the crystallographic orientation of the component. The method has been found to lend itself particularly well to automation.

Crystallographic orientation measurement

A turbine blade arrangement comprises turbine blades which are secured in adjacent positions to a rotor disc with a cavity defined between root segments and platform segments. A flow deflector within the cavity is provided as an insert such that through a recessed portion coolant flow .from a coolant path is constrained to remain adjacent to a rim surface. By constraining the coolant flow to remain adjacent to the surface greater cooling efficiency is achieved. Inner surfaces of the deflector may also be coated with low emissivity materials to reduce radiant heat flux transfer. The flow deflector supports a damper member in association with the platform segments.

Turbine blade arrangement

A deflector element is provided, in order to improve temperature interface control with respect to directional solidification of a component casting. This deflector element is formed during the mould making process and is arranged to be positioned with respect to a part of a principal mould formation within which the final cast component is produced. The deflector element ensures a uniform temperature throughout the component cross-section relative to other parts of the component as it is solidified.

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Derby, United Kingdom

John Harold Boswell