Abstract: A turbomachine casing assembly including: a first casing element arrangeable adjacent to one or more rotating aerofoil structures of a turbomachine; a second casing element provided at a radially outer position with respect to the first casing element; and an infill member disposed between the first and second casing elements, wherein an end of the infill member is set back from an end of the first casing element such that a void is provided between the first and second casing elements.

Abstract: A turbomachine casing assembly comprises a first casing portion for at least partially encasing one or more rotating aerofoil structures of a turbomachine and a second casing portion; the first casing portion being movable with respect to the second casing portion. One or more resilient elements are arranged so as to resist movement of the first casing portion with respect to the second casing portion.

Abstract: A turbomachine casing assembly including a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

Abstract: A stator vane assembly includes: inner and outer vane supports, and vanes extending radially between the supports. The supports have openings for receiving the ends of the vanes, and each vane is connected to the supports by a vane boot. Each vane boot has: a rim portion shaped to locate the boot within the corresponding opening in the vane support, the rim portion engaging with the inner surface defining the opening, an abutting portion for abutting against the vane support in the region surrounding the opening, and a vane pocket for accommodating the end of the vane. The vane pockets of the vane boots are shaped so as to position the vane with a predetermined stagger angle.

Abstract: A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process.

Abstract: A sealing assembly (100) for at least partially sealing a gap (102) leading to a void (104) between first and second members (110, 120), the first and second members forming part of a gas-washed surface of a jet engine, wherein the sealing assembly comprises: a bridging portion (130) couplable to one of the first and second members and movable to engage the other of the first and second members so as to block off the void between the first and second members from the gas-washed surface.

Abstract: A turbomachine casing assembly including a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

Abstract: A turbomachine casing assembly including: a first casing element arrangeable adjacent to one or more rotating aerofoil structures of a turbomachine; a second casing element provided at a radially outer position with respect to the first casing element; and an infill member disposed between the first and second casing elements, wherein an end of the infill member is set back from an end of the first casing element such that a void is provided between the first and second casing elements.

Abstract: An acoustic assembly for a fan casing of a turbofan engine is made up from acoustic liner panel components which each comprise a body and a backing sheet. The body is an integral injection moulding that generally includes an acoustic structure, a perforated sheet and fastening portions. Adjacent panel components engage each other at non-linear circumferential edges which generally includes lugs on one of the components which are received in recesses of the other component. The lugs are defined by following cell walls over a convoluted path along the circumferential edge.

Abstract: A liner panel for a fan casing of a gas turbine engine includes a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade failure. In use, ice may be released from a fan blade in a first direction, and (in the case of a blade-off event) a fan blade or part of a fan blade may be released in a second direction. The panel has a compressive strength greater in the first direction than in the second direction such that the released ice will be deflected by the panel but the released fan blade or part of a fan blade will pass through the panel.

Abstract: A turbomachine casing assembly comprises a first casing portion for at least partially encasing one or more rotating aerofoil structures of a turbomachine and a second casing portion; the first casing portion being movable with respect to the second casing portion. One or more resilient elements are arranged so as to resist movement of the first casing portion with respect to the second casing portion.

Abstract: A sealing assembly (100) for at least partially sealing a gap (102) leading to a void (104) between first and second members (110, 120), the first and second members forming part of a gas-washed surface of a jet engine, wherein the sealing assembly comprises: a bridging portion (130) couplable to one of the first and second members and movable to engage the other of the first and second members so as to block off the void between the first and second members from the gas-washed surface.

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 (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade. A set of cassettes (120) carries fan blade track panels (71B, 71C, 71D). The cassettes (120) are secured to the metal casing (40) by axially extending members (124, 128) on the upstream and downstream ends (122, 126) of the cassettes (120) which locate on the annular member (54) and are secured to inserts (136) on the inner face of the casing (40).

Abstract: A stator vane assembly comprising: an inner vane support (44); an outer vane support; and a plurality of vanes (50) extending radially between the inner vane support (44) and the outer vane support; wherein each of the inner (44) and outer vane supports has openings for receiving respective first and second ends of the vanes (50) and each said vane (50) is connected to the inner vane support (44) at its first end by a first vane boot (40) received in a said opening and to the outer vane support at its second end by a second vane boot (40) received in another said opening, wherein each vane boot (40) has a rim portion (41) shaped to locate the boot (40) within the corresponding opening in the vane support, the rim portion (41) engaging with the inner surface defining the opening, an abutting portion (47) for abutting against the vane support (44) in the region surrounding the opening, and a vane pocket (42) for accommodating the end of the vane, wherein the vane pockets (42) of the first and second vane boots

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 (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). A set of cassettes (120) carries fan blade track panels (71B,71C,71D). The cassettes (120) are secured to the metal casing (40) by axially extending members (124,128) on the upstream and downstream ends (122,126) of the cassettes (120) which locate on the annular member (54) and are secured to inserts (136) on the inner face of the casing (40).

Abstract: A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process.

Abstract: An acoustic assembly for a fan casing of a turbofan engine is made up from acoustic liner panel components which each comprise a body and a backing sheet. The body is an integral injection moulding comprising an acoustic structure, a perforated sheet and fastening portions. Adjacent panel components engage each other at non-linear circumferential edges which comprise lugs on one of the components which are received in recesses of the other component. The lugs are defined by following cell walls over a convoluted path along the circumferential edge.

Abstract: A clip used to attach an acoustic panel to a fan casing of a gas turbine engine is “U” shaped. One arm of the clip is provided with a spacing portion cut into the material of the arm and which may be bent to define the spacing between the outer face of the arm and a support. An engagement portion, which may also be cut into the material of the clip, may be bent to engage a recess in a tenon inserted into the receiving portion.

Abstract: A vane mounting arrangement 21, 31 is provided in which a vane 22, 32 is secured through a mounting end 23, 33 within an aperture 25, 35 formed in a mounting platform 24, 34. An expandable or expansive member 26, 36 is located between the mounting end 33 and the aperture 35 in order to create compressive engagement between the mounting end 33 and the aperture 25, 35 of the platform 24, 34. The member 26, 36 is hollow with a fluid within a cavity 27, 37 in order to create the desired pressurised location by selective expansion. Thus, the assembly 21, 31 through the expandable members 26, 36 achieves a seal along with vibration decoupling and appropriate presentation of the vane 22, 32 relative to the platform 24, 34.