Rolls-royce Corporation

Facc Ag

Kristofer John Bottome

Ian C D Care

Ian Colin Deuchar Care

Paul J Mason

Matthew Paul Jevons

Ewan Fergus Thompson

Eric P Ravey

James Andrew Lee

Konstantin Horejsi

Martin Fleischmann

Christof Obertscheider

Thomas Keusch

Gion Barandun

Markus Henne

James Lee

A nose cone assembly is provided comprising a nose cone, a support ring on which the nose cone is mounted, and an insulating layer disposed between the nose cone and the support ring, the insulating layer at least partially comprising glass fibres. A composite nose cone is also provided comprising an attachment region A, in which composite fibres are oriented substantially perpendicular to an axis of rotation of the nose cone, and an impact region I, in which composite fibres are oriented substantially parallel to the axis of rotation of the nose cone. Also provided is a support ring for a nose cone assembly, the support ring comprising an annular main body and an annular projecting attachment flange, the attachment flange terminating in a plurality of circumferentially spaced attachment tabs, wherein the attachment flange forms with the main body a cross section having at least two C curves.

Nose cone assembly

An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. Under centrifugal loads, the opposing support walls resiliently deform. Each support wall has a concave rear edge. Each rear edge has a first curved section, a second curved section and a substantially straight section therebetween.

Annulus filler

An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighboring the attachment strap.

A component of a gas turbine engine is provided. The component has a leading edge with two air-washed surfaces extending rearwardly therefrom to define opposing sides of the component. The component has a leading edge protector formed as a plurality of protector segments which succeed in a line along the leading edge. Each protector segment includes a sheath which covers the leading edge and the air-washed surfaces at regions adjacent the leading edge. Each protector segment overlaps with the neighboring sheath of the succeeding segment.

Leading edge protector

A nose cone assembly is provided comprising a nose cone, a support ringon which the nose coneis mounted, and an insulating layerdisposed between the nose coneand the support ring, the insulating layerat least partially comprising glass fibers. A composite nose cone is also provided comprising an attachment region A, in which composite fibers are oriented substantially perpendicular to an axis of rotation of the nose cone, and an impact region I, in which composite fibers are oriented substantially parallel to the axis of rotation of the nose cone Also provided is a support ringfor a nose cone assembly, the support ringcomprising an annular main bodyand an annular projecting attachment flange, the attachment flangeterminating in a plurality of circumferentially spaced attachment tabs, wherein the attachment flangeforms with the main bodya cross section having at least two C curves

A mandrel includes a support structure; main sectors carried by the support structure and each having a main forming surface; and intermediate sectors carried by the support structure and each having an intermediate forming surface. The main sectors and intermediate sectors are alternately arranged around the axis. The main sectors are moveable relative to the support structure between a radially inner main retracted position, and a radially outer main forming position. The intermediate sectors are moveable relative to the support structure between a radially inner intermediate retracted position, and a radially outer intermediate forming position. The mandrel further includes drive means for moving the main sectors and intermediate sectors from their respective retracted positions to their respective forming positions. The drive means is configured such that each main sector reaches its main forming position before the adjacent intermediate sectors reach their respective intermediate forming positions.

Mandrel for forming a component

A nose cone assemblyis disclosed, comprising a one piece nose coneand a support ringon which the nose coneis mounted. The support ringcomprises a plurality of circumferentially distributed resilient attachment tabs, via which the nose coneis mounted on the support ring. The support ringfurther comprises a load spreader, and each of the resilient attachment tabsis operably connected to the load spreader, such that deflections and forces experienced by any one attachment tabare distributed to other attachment tabsvia the load spreader

An annulus filler for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion including a lid which has a leading edge, a trailing edge and opposing side edges which connect respective ends of the leading and trailing edges. The lid defines an airflow surface for air being drawn through the engine. The annulus filler further has one or more attachment formations which, in use, connect the body portion to the rotor disc. The lid is configured such that the stiffness of the lid under compressive loading exerted on the opposing side edges by sideways blade movement is greater at the leading edge than at the trailing edge.

The present invention relates to an aerofoil having an erosion resistant leading edge. The aerofoil comprises an aerofoil main body portion and a leading edge portion. The leading edge portion comprises a plurality of functionally distinct parts, including at least; a first part for resisting abrasion of the leading edge portion, and a second part for resisting a bending force applied to the leading edge portion, and located behind the first part.

Aerofoil with erosion resistant leading edge

A fan blade () for a turbofan aero engine comprises a blade body including a root () for engagement with a rotor, and a tip, wherein the tip is provided with a winglet ().

Fan blade with winglet

An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion defining an airflow surface for air being drawn through the engine. The annulus filler further has a front attachment formation connecting a forward end of the body portion to the rotor disc and which allows rotational movement of the body portion thereabout. The annulus filler further has a rear attachment formation connecting a rearward end of the body portion to the rotor disc. The rear attachment formation comprises a spring element which extends between the body portion and the rotor disc. The spring element expands under operational centrifugal loading such that the rearward end of the body portion moves radially outwardly with the body portion rotating about the front attachment formation.

A gas turbine engine nose cone assembly () comprises a tapering spinner (). The tapering spinner () has a point () at a first end () and a circular base () at a second end (). The tapering spinner () comprises a carbon fiber containing composite material layer (), an electrically insulating layer () arranged on an inner surface () of the carbon fiber containing composite material layer (), an electrically conducting layer () arranged on an inner surface () of the electrically insulating layer () and an electrically conducting member () extends through the first end of the tapering spinner () and is connected to the electrically conducting layer (). This arrangement provides lightning protection for the gas turbine engine nose cone assembly ().

Gas turbine engine nose cone

A composite component such as a fan rear seal comprises a hub and a body of composite material which is molded over the outer periphery of the hub. The body is formed from a preform of fiber reinforcement impregnated with a resin, in a compression molding process. The body has an annular projection provided with a sealing surface. The sealing surface may comprise circumferential fins, or may be a surface of, for example, an abradable seal insert molded into the composite material of the body.

Composite component

A liner for an interior surface of an engine casing, comprises a number of liner panels disposed radially outwardly of a rotatable component of the engine, such as a fan blade, and the panels are mounted on the interior surface of the casing, wherein each panel is individually adjustable, such that the clearance between the panel and the rotatable component of the engine may be varied individually for each panel.

Adjustable fan case liner and mounting method

A containment assembly for a turbo fan engine, has a casing arranged in use around a rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface between the casing and blades of a rotatable fan. The liner element includes a body portion mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct. The wall portion and the body portion being attached and defining a containment cavity therebetween for containment of a detached fan blade fragment in use, wherein the wall portion has a moveable portion movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity.

Growing community of inventors

Nottingham, United Kingdom

Kristofer John Bottome