Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of making an aerofoil comprises the steps of providing first and second skin panels and first and second web-forming membranes. The web-forming membranes each have a series of elongate slots formed longitudinally therein so as to define a series of alternating wide and narrow strips. The wide strips of one membrane are arranged against the narrow strips of the other membrane and the skin panels are arranged either side of the two web-forming membranes. Parts of the web-forming membranes and parts of the skin panels are treated with a release layer and the sub-assembly is compressed and heated so as to effect diffusion bonding between those parts of the membranes and skin panels which are not treated with the release layer. The sub-assembly is then heated and inflated so as to draw the first and second skin panels apart and that, in turn, causes the web-forming membranes to form webs internally.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of manufacturing a component, the method including the steps of: providing a component having a first portion, which first portion defines a cavity, characterized by; identifying a first frequency response of the first portion and/or the entire component, and introducing material into the cavity to achieve an adjusted frequency response of the first portion and hence a desired frequency response of the component.

Abstract: A method of manufacturing a rotating component, the method comprising the providing a component comprising a first portion, which first portion defines a first cavity, characterised by; identifying a first inertial property of the first portion and/or the entire component, introducing material into the first cavity to achieve an adjusted inertial property of the first portion and hence a desired inertial property of the component. A rotating component including a first portion defining a first cavity, a second portion defining a second cavity, the second portion being circumferentially spaced from said first portion, the first cavity has a first material deposit therein, said material having predetermined inertial characteristics so as to adjust the centre of mass (Z) of the rotating component.

Abstract: A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).

Abstract: An aerofoil sub-assembly of a blade, in particular an aerofoil blade for a gas turbine engine. A multi-layer construction including first and second skin panels which together define the external surfaces of the aerofoil and aerofoil leading and trailing edges. Between the skin panels at least there is at least one web-forming membrane which has a multiplicity of fingers trapped between the first and second panels at one of the edges and which extend away from the edge region. The fingers each have “dog-leg” shapes which are overlaid immediately behind the blade leading edge to form a transition zone providing additional support to resist crumpling of the hollow blade in the event of an external foreign object striking the leading edge.

Abstract: A method of making an aerofoil comprises the steps of providing first and second skin panels and first and second web-forming membranes. The web-forming membranes each have a series of elongate slots formed longitudinally therein so as to define a series of alternating wide and narrow strips. The wide strips of one membrane are arranged against the narrow strips of the other membrane and the skin panels are arranged either side of the two web-forming membranes. Parts of the web-forming membranes and parts of the skin panels are treated with a release layer and the sub-assembly is compressed and heated so as to effect diffusion bonding between those parts of the membranes and skin panels which are not treated with the release layer. The sub-assembly is then heated and inflated so as to draw the first and second skin panels apart and that, in turn, causes the web-forming membranes to form webs internally.

Abstract: A method of manufacturing a component (110), the method comprising the steps of: providing a component having a first portion (20, 40, 60, 80, 100, 116), which first portion defines a cavity (26, 46, 66, 86, 106), characterised by; identifying a first frequency response of the first portion and/or the entire component, and introducing material (28, 48, 68, 88, 108) into the cavity to achieve an adjusted frequency response of the first portion and hence a desired frequency response of the component.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of manufacturing a rotating component (110), the method comprising the following steps: providing a component comprising a first portion (20, 40, 60, 80, 100, 116), which first portion defines a first cavity (26, 46, 66, 86, 106), characterised by; identifying a first inertial property of the first portion and/or the entire component, introducing material (28, 48, 68, 88, 108) into the first cavity to achieve an adjusted inertial property of the first portion and hence a desired inertial property of the component. A rotating component (110) comprising: a first portion (20, 40, 60, 80, 100, 116) defining a first cavity (26, 46, 66, 86, 106), a second portion (118) defining a second cavity, the second portion being circumferentially spaced from said first portion, characterised in that the first cavity has a first material (28) deposit therein, said material having predetermined inertial characteristics so as to adjust the centre of mass (Z) of the rotating component.