Patent application number | Description | Published |
20090208335 | Annulus filler - 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 which defines an airflow surface for air being drawn through the engine, and one or more hook portions which extend radially inwardly from the body portion. The hook portions are for connection to corresponding engagement portions on the radially outer face of the rotor disc. The or each hook portion is attached to the body portion by a joining arrangement in which a wedge part provided by one of the hook portion and the body portion is received in a complementary-shaped retention recess provided by the other of the hook portion and the body portion. | 08-20-2009 |
20100329878 | ADJUSTABLE CAMBER AEROFOIL - The present invention relates to an aerofoil ( | 12-30-2010 |
20110002776 | Actuatable Seal for Aerofoil Blade Tip - The present invention relates to an actuatable seal ( | 01-06-2011 |
20110044807 | ADJUSTABLE FAN CASE LINER AND MOUNTING METHOD - A liner for an interior surface of an engine casing ( | 02-24-2011 |
20110049297 | AEROFOIL WITH EROSION RESISTANT LEADING 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. | 03-03-2011 |
20110236217 | GAS TURBINE ENGINE NOSE CONE - A gas turbine engine nose cone assembly ( | 09-29-2011 |
20120063909 | FAN BLADE WITH WINGLET - A fan blade ( | 03-15-2012 |
20120107102 | ANNULUS FILLER - 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. | 05-03-2012 |
20120134843 | NOSE CONE ASSEMBLY - A nose cone assembly is provided comprising a nose cone | 05-31-2012 |
20120134844 | NOSE CONE ASSEMBLY - A nose cone assembly | 05-31-2012 |
20120148388 | ANNULUS FILLER - 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. | 06-14-2012 |
20130074572 | MANDREL FOR FORMING A COMPONENT - 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. | 03-28-2013 |
Patent application number | Description | Published |
20090269189 | FAN BLADE - A fan blade for the fan of a gas turbine engine has a radially outer tip portion which, in use, is adjacent to a fan case of the engine. The tip portion includes a movable sealing element for sealing a gap between the tip portion and the fan case. The sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case. | 10-29-2009 |
20100158676 | COMPOSITE COMPONENT - A composite component such as a fan rear seal comprises a hub and a body of composite material which is moulded over the outer periphery of the hub. The body is formed from a preform of fibre reinforcement impregnated with a resin, in a compression moulding 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 moulded into the composite material of the body. | 06-24-2010 |
20110076132 | CONTAINMENT CASING FOR AN AERO ENGINE - 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. | 03-31-2011 |
20140086751 | ANNULUS FILLER FOR AXIAL FLOW MACHINE - A fluid-washed assembly for an axial flow machine, such as a fan blade assembly for a gas turbine engine. The assembly has an array of members circumferentially spaced about the machine axis, each member extending from a radially inner end to a radially outer end with respect to the axis of rotation of the machine. Each member has opposing outer surfaces extending between a leading edge and a trailing edge thereof with respect to the direction of oncoming fluid flow in use. A plurality of annulus fillers are provided between each member, wherein each annulus filler is affixed against an outer surface of an associated member at a location between the inner and outer ends in a manner which supports the annulus filler in use. In preferred embodiments, the annulus fillers comprise a composite material which is bonded to the associated member using an adhesive. | 03-27-2014 |
20150050150 | ANNULUS FILLER - 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. | 02-19-2015 |
20150050151 | 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 has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc. The support arrangement includes a first engageable portion at the leading edge of the lid and a second engageable portion at the trailing edge of the lid. The engageable portions engage in use with respective adjacent parts of the gas turbine engine, and have respective galvanic corrosion barriers, which prevent or reduce galvanic corrosion between the material of the lid and the respective adjacent engine parts. | 02-19-2015 |