Abstract: An annulus filler (101) is provided for mounting to a rotor disc (102) of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc (102). The annulus filler (101) has an outer part (106) which defines an airflow surface for air being drawn through the engine, and a separate, support part (105) which is connectable to the outer part (106) and to the rotor disc (102) to support the outer part (106) on the lo rotor disc (102). The outer (106) and support parts (105) are configured to allow a procedure for mounting the annulus filler (101) to the rotor disc (102). In a first step the support part (105) is connected to the rotor disc (102) without the outer part (106), and in a subsequent second step the outer part (106) is connected to the support part (105).

Abstract: An aircraft engine mounting assembly comprising a bracket arrangement with two plates located either side of an opening in the structural bypass duct. The bracket arrangement mounts two inclined links which connect to the engine. In normal usage, tension/compression from the links will be passed by the bracket arrangement into the airframe. Upon failure of one of the links the bracket arrangement will engage with the structural bypass duct to transmit engine loads into the airframe via the duct.

Abstract: A method of manufacturing a hollow article (10) comprising the steps of cold pressing two members (30,34) to form at least one depression (32,36) in the members (30,34). Arranging the two members (30,34) in abutting relationship such that the at least one depression (32,36) defines at least one chamber between the two members (30,34). Sealing (41) the edges (40,42) of the two members (30,34) together to form a core structure (44). Positioning the core structure (44) in a mould (46) to define a cavity (48) between the external surface (50) of the core structure (44) and the internal surface (52) of the mould (46), the internal surface (52) of the mould (46) substantially defining the external shape of the hollow article (10). Filling the cavity (48) between the core structure (44) and the mould (46) with a powder material (54), sealing the open edge of the core structure (44) to the mould (46).

Abstract: A mounting arrangement (26) is provided for mounting an engine (10), typically a gas turbine engine, to a vehicle. The mounting arrangement (26) includes connecting means (28, 30) constructed to extend from a core assembly (14) of the engine (10) through an outer component (24) to the vehicle. The mounting arrangement (26) also includes transmission means (41) extending from the connecting means (28, 30) to transmit thrust from the engine (10) to the vehicle.

Abstract: A mounting arrangement (26) is provided for mounting an engine (10), typically a gas turbine engine, to a vehicle. The mounting arrangement (26) includes connecting means (28, 30) constructed to extend from a core assembly (14) of the engine (10) through an outer component (24) to the vehicle. The mounting arrangement (26) also includes transmission means (41) extending from the connecting means (28, 30) to transmit thrust from the engine (10) to the vehicle.

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.