Abstract: A liner for use with a gas turbine engine includes a first liner portion including a first upstream surface and a first downstream surface. The liner further includes a second liner portion spaced apart from the first liner portion. The second liner portion includes a second upstream surface and a second downstream surface. The second upstream surface faces the first downstream surface. Each of the first liner portion and the second liner portion at least circumferentially and radially extends with respect to a central axis. Each of the first liner portion and the second liner portion includes a substrate made of a metallic material and a wear resistant coating disposed on at least a portion of the substrate. The wear resistant coating is made of a polymeric material. The wear resistant coating at least forms the first downstream surface and the second upstream surface.

Abstract: An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Abstract: A method of forming a protective sheath for an aerofoil component includes: providing a first sheath portion and a second sheath portion, the first sheath portion and the second sheath portion each comprising an inner surface, an outer surface and an end surface between the inner and outer surfaces and having a sacrificial flange at its distal end; positioning the first sheath portion and second sheath portion so that the inner surface of the first sheath portion abuts against the inner surface of the second sheath portion with the end surfaces of the first and second sheath portions aligned to form a mating edge; and joining the first sheath portion to the second sheath portion by welding along the mating edge, wherein the sacrificial flanges are completely consumed and a curved outer profile is formed.

Abstract: A method of forming a protective sheath for an aerofoil component includes: providing a first sheath portion and a second sheath portion, the first sheath portion and the second sheath portion each comprising an inner surface, an outer surface and an end surface between the inner and outer surfaces and having a sacrificial flange at its distal end; positioning the first sheath portion and second sheath portion so that the inner surface of the first sheath portion abuts against the inner surface of the second sheath portion with the end surfaces of the first and second sheath portions aligned to form a mating edge; and joining the first sheath portion to the second sheath portion by welding along the mating edge, wherein the sacrificial flanges are completely consumed and a curved outer profile is formed.

Abstract: An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Abstract: A method is provided of bonding a first component to a second component. The method includes: locating the first component against the second component to form an interface between the components, a curable adhesive being provided at the interface; locating a pressurizable, fluid-filled bladder against the first component such that the first component is sandwiched between the second component and the bladder; locating a backing member against the bladder such that the bladder is sandwiched between the backing member and the first component; pressurizing the bladder such that a consolidating pressure is exerted by the bladder on the first component to conform the first component to the second component; and curing the adhesive while the first component is conformed to the second component by the consolidating pressure.

Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.

Abstract: A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.

Abstract: A fan casing arrangement for a gas turbine engine, the arrangement comprising an annular casing member and a fan track liner provided radially inward of the casing member and connected thereto. A forward portion of a gas washed surface of the fan track liner is curved so as to define a concave portion of the gas washed surface (e.g. curved such that the radial position of said forward portion of the gas washed surface varies in an axial direction).

Abstract: A method is provided of bonding a first component to a second component. The method includes: locating the first component against the second component to form an interface between the components, a curable adhesive being provided at the interface; locating a pressurisable, fluid-filled bladder against the first component such that the first component is sandwiched between the second component and the bladder; locating a backing member against the bladder such that the bladder is sandwiched between the backing member and the first component; pressurising the bladder such that a consolidating pressure is exerted by the bladder on the first component to conform the first component to the second component; and curing the adhesive while the first component is conformed to the second component by the consolidating pressure.

Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.

Abstract: A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.

Abstract: A component for use in a gas turbine engine comprises an indicator operable to provide a visual indication when strain over a threshold value has been experienced by the component by transitioning from a rest state to an indication state on occurrence of strain above the threshold value. Also disclosed is a method of detecting foreign object damage in a component of a gas turbine engine, comprising: identifying at least one of a component or a region of a component that is subject to increased strain during a foreign object impact; and mounting an indicator on the identified component or region of a component, the indicator providing a visual indication when increased strain has been experienced.

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 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: A component for use in a gas turbine engine comprises an indicator operable to provide a visual indication when strain over a threshold value has been experienced by the component by transitioning from a rest state to an indication state on occurrence of strain above the threshold value. Also disclosed is a method of detecting foreign object damage in a component of a gas turbine engine, comprising: identifying at least one of a component or a region of a component that is subject to increased strain during a foreign object impact; and mounting an indicator on the identified component or region of a component, the indicator providing a visual indication when increased strain has been experienced.

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 mold (46) to define a cavity (48) between the external surface (50) of the core structure (44) and the internal surface (52) of the mold (46), the internal surface (52) of the mold (46) substantially defining the external shape of the hollow article (10). Filling the cavity (48) between the core structure (44) and the mold (46) with a powder material (54), sealing the open edge of the core structure (44) to the mold (46).

Abstract: An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact.

Abstract: An artificial bird projectile is provided for simulating bird strike events. The projectile has a solid foam phase and a gel or liquid phase. The gel or liquid phase is supported by the foam phase. The projectile may be suitable for simulating bird strike events on aero gas turbine engines.