Rolls-royce Corporation

Christopher Neale

Paul J Wilson

Andrew S Barr

Marta Villasante Llarena

James R Kingsley-rowe

A gas turbine engine component that has a web provided with an array of cooling holes distributed with respect to a first direction, wherein the cooling holes have a cross-sectional shape that varies along the first direction. The component may be configured so that the first direction corresponds to a loading distribution of the component which increases along the first direction from a low loading position to a high loading position.

Gas turbine engine component with variable cooling hole geometry

Method for casting a turbine component body including; providing a mould defining the external geometry of the component body and providing a core defining an internal geometry of the component body. The core includes a main body defining an internal chamber of the component body and an array of pedestals extending between opposing walls of the internal chamber. A molten material is cast between the mould and the core and the core is then removed after the molten material has solidified. The core is provided using a core die which has an inlet for receiving fluid core material. The core die is configured such as to provide a gradient of injection pressure which decreases from a first position proximal to the inlet to a second position distal to the inlet. The pedestal array is arranged such that the separation of the pedestals increases between the first and second positions.

Cooling of turbine blades and method for turbine blade manufacture

Investment casting of an engine part using a pair of core members having respective opposed faces spaced apart by a first distance, a face of a first core member of the pair being provided with one or more protrusions thereon and a face of the second core member of the pair being provided with one or more respective open recesses therein, each protrusion facing a respective open recess, wherein during a casting procedure the first and second core members are maintained positioned relative to each other so major portions of the opposed faces of the first and second core members assume mutual spacing equaling a corresponding predetermined thickness of a portion of a resulting cast wall of the first distance; and at least a head portion of the protrusion is located within the respective open recess to define a minor portion of the resulting cast wall.

Casting of engine parts

A method for casting a turbine blade body comprises; providing a mold defining the external geometry of the blade body; providing a core defining an internal geometry of the blade body, the core comprising a main body defining an internal chamber of the blade body and having a root end and a tip end and a plurality of pedestals defining an array of cooling channels extending from the internal chamber; casting a molten material between the mold and the core; and removing the core after the molten material has solidified, wherein the pedestals are arranged in a single row starting from the root end to a mid-portion of the main body branching into multiple and divergent rows towards the tip end of the body.

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Bristol, United Kingdom

Christopher Neale