Abstract: A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

Abstract: A seal assembly for a gas turbine engine having a rotor arranged to rotate about an axis in use. The seal assembly has a static support structure for the gas turbine engine and a casing structure of the engine. Rotation of the engine rotor causes a deflection of the casing structure relative to the static support structure in a first direction. A seal is provided at an interface between the static support structure and the casing structure, and comprising a first seal portion and a second seal portion spaced from one another in the first direction. The first seal portion is provided against a first surface of the casing structure and the second seal portion is provided against a second surface of the casing structure opposing the first surface.

Abstract: A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

Abstract: A gas turbine engine casing is described as having a cowl door hinged to a casing support structure by at least one hinge. The cowl door is openable outwardly from the casing to expose a casing interior. The hinge is located above a longitudinal axis of the casing and comprises a pivoting linkage arranged such that, upon actuation between closed and open cowl door conditions, the pivoting linkage moves an upper portion of the cowl door downwards towards the longitudinal axis.

Abstract: A gas turbine engine casing is described as having a cowl door hinged to a casing support structure by at least one hinge. The cowl door is openable outwardly from the casing to expose a casing interior. The hinge is located above a longitudinal axis of the casing and comprises a pivoting linkage arranged such that, upon actuation between closed and open cowl door conditions, the pivoting linkage moves an upper portion of the cowl door downwards towards the longitudinal axis.

Abstract: A seal assembly for a gas turbine engine having a rotor arranged to rotate about an axis in use. The seal assembly has a static support structure for the gas turbine engine and a casing structure of the engine. Rotation of the engine rotor causes a deflection of the casing structure relative to the static support structure in a first direction. A seal is provided at an interface between the static support structure and the casing structure, and comprising a first seal portion and a second seal portion spaced from one another in the first direction. The first seal portion is provided against a first surface of the casing structure and the second seal portion is provided against a second surface of the casing structure opposing the first surface.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

Abstract: A gas turbine engine (10) comprises a bypass duct cowl (21), an engine core housing (22) defining an engine core inlet, a bypass fan (13) and a plurality of outlet guide vanes (24). Each outlet guide vane 24 extends between a radially inner surface of the bypass duct cowl (21) and a radially outer surface of the engine core housing (22, 23) to define an outlet guide vane span (SPANOGV). The outlet guide vanes (24) are configured to support the engine core housing (22, 23) relative to the bypass duct cowl (21). The bypass fan (13) and an engine core inlet (34) define a bypass ratio between 10 and 17, and a ratio of the outlet guide vane span (OGVSPAN) to a bypass fan radius (RFAN) is between 0.45 and 0.55.

Abstract: A blade or a vane for a gas turbine engine. The blade or vane having an aerofoil and a leading edge member attached to the aerofoil. The leading edge has an electrically conductive support member and a nano-coating formed on the support member.

Abstract: The present disclosure relates to outlet guide vanes in a gas turbine engine, and in particular to such vanes with particular ranges of relative dimensions. Example embodiments include a gas turbine engine (10) comprising a plurality of outlet guide vanes (31) each having a length extending across a bypass duct (22) of the gas turbine engine (10), wherein for each outlet guide vane a minimum thickness to chord ratio is less than 80% of a maximum thickness to chord ratio.

Abstract: A gas turbine engine casing comprising: an inner circumferential wall; an outer circumferential wall spaced radially outwardly from the inner wall; wherein the inner and outer circumferential walls are formed by an axially repeating profile comprising an inner wall portion and an outer wall portion connected to one another by an intermediate portion, the axially repeating profile being arranged such that the inner wall portion abuts against and is connected to an adjacent inner wall portion to form the inner circumferential wall and the outer wall portion abuts against and is connected to an adjacent outer wall portion to form the outer circumferential wall.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Abstract: There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24). A related method of installing a fan track liner in a gas turbine engine is also disclosed.

Abstract: A gas turbine engine comprising a stator, wherein the stator comprises laminated oscillating heat pipes.

Abstract: A vane for a gas turbine engine has a pressure surface and a suction surface. The vane comprises an arrangement of internal channels and a plurality of conducting members extends from the channels towards the suction surface and/or the pressure surface.

Abstract: A gas turbine engine casing 2 comprising: an inner circumferential wall 12; an outer circumferential wall 14 spaced radially outwardly from the inner wall 12; wherein the inner and outer circumferential walls 12, 14 are formed by an axially repeating profile comprising an inner wall portion 6 and an outer wall portion 8 connected to one another by an intermediate portion 10, the axially repeating profile being arranged such that the inner wall portion 6 abuts against and is connected to an adjacent inner wall portion 6 to form the inner circumferential wall 12 and the outer wall portion 8 abuts against and is connected to an adjacent outer wall portion 8 to form the outer circumferential wall 14.

Abstract: A blade or a vane for a gas turbine engine. The blade or vane comprising an aerofoil and a leading edge member attached to the aerofoil. The leading edge comprises an electrically conductive support member and a nano-coating formed on the support member.

Abstract: There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24). A related method of installing a fan track liner in a gas turbine engine is also disclosed.