Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Abstract: A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

Abstract: Fan containment system fitting around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling the array of fan blades and a hook projecting in a radially inward direction from the annular casing element and positioned axially forward of the array of fan blades when the fan containment system fitted around fan blades. An annular fan track liner positioned substantially coaxial to the annular casing element. Clamping arrangement connects fan track liner to the hook. Clamping arrangement is configured under the condition that a fan blade impacts the fan track liner, the clamping arrangement releases connection between the hook and a portion of fan track liner so that a portion of the fan track liner can move towards the annular casing element to encourage the fan blade to impact the hook.

Abstract: A turbomachine casing assembly includes 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 and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.

Abstract: A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract: An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag.

Abstract: A composite casing comprising a barrel and a stiffening ring provided around the barrel. The stiffening ring includes a section having a waved profile in a circumferential direction.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.

Abstract: A turbomachine casing assembly includes 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. 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 fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Abstract: A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fibre/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Abstract: Fan containment system fitting around array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling array of fan blades and a hook projecting in radially inward direction from the annular casing element and positioned axially forward of an array of fan blades when the fan containment system fitted around fan blades. An annular fan track liner positioned substantially coaxial to the annular casing element. Clamping arrangement connects fan track liner to the hook. Clamping arrangement is configured under the condition that a fan blade impacts the fan track liner, the clamping arrangement releases connection between the hook and a portion of fan track liner so that a portion of the fan track liner can move towards the annular casing element to encourage the fan blade to impact the hook.

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element, with a void being defined between the first and second casing elements. Each of the first and second casing elements includes, at a first end thereof, respective co-operating first and second interface portions. In the event that an aerofoil element becomes detached from the turbomachine and impacts the first casing element, the second interface portion; slides along the first interface portion and the first end of the first casing element enters the void.