Abstract: A bladed disc for a rotating machine comprising a central disc that rotates about a central axis, the central disc having a series of blades arranged around its periphery; the blades have dovetail roots which engage with slots on the central disc; the bladed disc being configured so that there is a pre-loading force between the blades and the central disc such that each blade is forced away from the central axis of the bladed disc; and wherein the pre-loading force is equal or greater than 40% of the maximum centrifugal force applied to the blade during a flight cycle.

Abstract: A de-icing system for one or more vanes of a gas turbine engine. The system comprises a vane comprising an electrically and thermally conductive material and a plurality of magnets located circumferentially about a rotating shaft and configured to be driven by the shaft in the circumferential direction to generate a rotating magnetic field. The vane has a composite structure that includes a core laminate layer of the thermally conductive material located between two laminate layers of titanium, stainless steel or an alloy thereof. A portion of the thermally conductive material is located within the rotating magnetic field such that the conductive material directly heated by electromagnetic induction.

Abstract: A de-icing system for one or more vanes of a gas turbine engine. The system comprises a coating of electrically conductive material on at least a portion of a vane and a plurality of magnets located circumferentially about a rotor shaft of the gas turbine engine and configured to be driven by the rotor shaft in the circumferential direction to generate a rotating magnetic field. A coiled wire is configured to remain stationary within the rotating magnetic field so as to induce a current therein, the coiled wire being connected to the coating for supplying the induced current to the electrically conductive material. In this way, the coating of electrically conductive material is heated by the induced current, for inhibiting ice accretion on the vane.

Abstract: There is described a casing assembly for a gas turbine engine, the casing assembly comprising: an annular casing having a longitudinal axis; a unison ring assembly configured for rotation about the longitudinal axis; a plurality of vanes rotatably coupled to the annular casing; and a plurality of linkages, wherein each of the plurality of vanes is coupled to the unison ring assembly by a respective one of the plurality of linkages. Each linkage comprises: a first link coupled to the respective vane; and a second link rotatably coupled to the first link and rotatably coupled to the unison ring assembly, such that rotation of the unison ring assembly about the longitudinal axis effects rotation of the respective vane.

Abstract: There is disclosed a variable vane actuation arrangement 100, 200 comprising a crankshaft 48, 148 comprising a crank web 50,150 and a unison ring assembly 45 comprising a unison ring 34 moveable to vary the pitch of a plurality of variable vanes 26. A connector 42 is fixed with respect to the unison ring 34. The crank web 50, 150 and the connector 42 cooperate by a pin 56—slot 52, 152 mechanism configured so that rotation of the crankshaft 48, 148 causes rotation of the unison ring 34. There is further disclosed a gas turbine engine with a variable vane actuation arrangement.

Abstract: A crankshaft assembly for a gas turbine engine guide vane actuator. Example embodiments include a crankshaft assembly for a gas turbine engine guide vane actuator, the crankshaft assembly comprising: a crankshaft mounted for rotation about a central axis; a lug mounted to the crankshaft for rotation with the crankshaft about the central axis, the lug having a first end with a crankshaft connection securing the lug to the crankshaft and a second opposing end for connecting the lug to a control rod such that rotation of the crankshaft causes actuation of the control rod in a direction orthogonal to the central axis, wherein the crankshaft connection is adjustable to allow the first end of the lug to be secured relative to the crankshaft over a range of rotational positions about the central axis.

Abstract: A variable stator vane arrangement is provided in which the variable stator vanes extend from a first end at a radially inner flow boundary to a second end at a radially outer flow boundary. At least one of the radially inner flow boundary and the radially outer flow boundary is faceted, such that the surface of the faceted flow boundary comprises flat portions at the interfaces with the respective first or second end of each stator vane. The flat portions mean that the tips of the variable stator vanes can be made substantially flush with the flat casing portions. This may improve aerodynamic efficiency and/or increase the design flexibility on where to position the pivot axis of the variable stator vanes.

Abstract: There is disclosed a variable vane actuation arrangement 100, 200 comprising a crankshaft 48, 148 comprising a crank web 50,150 and a unison ring assembly 45 comprising a unison ring 34 moveable to vary the pitch of a plurality of variable vanes 26. A connector 42 is fixed with respect to the unison ring 34. The crank web 50, 150 and the connector 42 cooperate by a pin 56—slot 52, 152 mechanism configured so that rotation of the crankshaft 48, 148 causes rotation of the unison ring 34. There is further disclosed a gas turbine engine with a variable vane actuation arrangement.