Rolls-royce Corporation

Michael Philip Keenan

Gareth M Armstrong

Stewart T Thornton

Stuart Ellis

Nicholas Thomas

There is disclosed a blade for a gas turbine engine comprising an asymmetrical blade root.

Blade for a gas turbine engine

The present disclosure relates to a metallic shaft for connecting components of a gas turbine engine. Example embodiments include a metallic shaft () for connecting components of a gas turbine engine, the shaft () having a longitudinal axis () and comprising: a first section () extending from a first end () of the shaft () to a joint (), the first section () composed of a material having a first thermal expansion coefficient along the longitudinal axis (); a second section () extending from a second opposing end () of the shaft to the joint (), the second section () composed of a material having a second thermal expansion coefficient along the longitudinal axis () that is different to the first thermal expansion coefficient.

Metallic shaft

There is disclosed an auxiliary rotation devicefor a gas turbine engine. The auxiliary rotation devicecomprises: an electric machineconfigured to be coupled to a rotor of the gas turbine engine; and a dedicated electrical storage devicecoupled to the electric machine. During a period of powered operation of the gas turbine enginethe electric machineis configured to act as a generator so as to charge the dedicated electrical storage device. Following the period of powered operation of the gas turbine enginethe electric machineis configured to act as a motor by discharging the dedicated electrical storage deviceso as to cause the rotor to rotate for a period of time to provide even cooling of the rotor around its circumference. There is also disclosed a method of cooling a rotor of a gas turbine engineusing an auxiliary rotation device

Auxiliary rotation device for a gas turbine engine and a method of cooling a rotor of a gas turbine engine using an auxiliary rotation device

A variable vane mechanism for adjusting the angle of stator vanes in a gas turbine engine is provided. The mechanism includes a circumferentially extending unison ring that is driven circumferentially around a casing by an actuator. The unison ring is connected to the stator vanes via levers such that the angle of the vanes changes with circumferential movement of the unison ring. The unison ring and the casing are each provided with at least one rigging hole in order to set the initial angle of the vanes. At least one of the unison ring and the casing are each provided with at least two rigging holes, so that the initial angle of the vanes can be adjusted by selecting different combinations of rigging holes. This may allow accumulations in tolerances to be compensated for and/or may allow the engine to be tested at different initial vane angles.

Variable stator vane rigging

A bladed disc for use in a turbine engine comprises: a central cob portion; a main diaphragm attached to, and extending around, the cob portion; a rim surrounding the main diaphragm; and two rows of blades attached to the rim.

Bladed disc

A method of balancing a rotor, where the rotor comprises a plurality of holes, comprises the steps of measuring an imbalance of the rotor, identifying at least one characteristic dimension associated with at least one hole, identifying a change to the or each characteristic dimension to reduce the imbalance, and changing the or each characteristic dimension.

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Sheffield, United Kingdom

Michael Philip Keenan