Volvo Aero Corporation

Gknaerospace Sweden Ab

Rickard Samuelsson

Robert Reimers

Niklas Jansson

Anders Sjunnesson

Goran Johnsson

Göran Johnsson

A supporting structure for a gas turbine engine includes an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings. The radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge. At least one of the radial elements includes a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure. The gas passage arrangement includes a radially extending gas channel arranged inside the radial element and at least one opening in communication with the gas channel. The at least one opening is arranged at one of the two opposite sides of the radial element.

Supporting structure for a gas turbine engine

A gas turbine engine component includes a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. At least one of the vanes is made of a composite material. The at least one composite vane is fastened to the ring element. The component further includes first and second wall portions that are fixed in relation to the ring element and arranged on opposite sides of the composite vane. At least a first hole extends through the first wall portion, the composite vane and the second wall portion. The first hole is adapted to receive a first insertion member. The component is arranged such as to, with regard to the first hole, provide a tight fit for the first insertion member in the first wall portion as well as in the composite vane and to provide a loose fit with a radial play in the second wall portion.

Gas turbine engine component

A component includes a first member, a second member and a device for fastening the first member to the second member. A first hole extends through a portion of the first member and a second hole extends through a portion of the second member. The first member and the second member are positioned such that the first hole and the second hole coincide. The fastening device includes an elongated fastening element arranged in the coinciding holes and a bushing arrangement arranged around the fastening element and adapted to establish a load transmission path between the first member and the second member. A first part of the bushing arrangement is arranged such that an inner surface thereof is positioned at a distance from an exterior surface of the fastening element for establishing a first load transmission path via the bushing arrangement and bypassing the fastening element in a first load condition. Further, the fastening device is adapted to allow the first member to move relative to the fastening element in a second load condition such that the first part of the bushing arrangement can be brought into contact with the fastening element for establishing a second load transmission path between the first member and the second member via the fastening element.

Component and a gas turbine engine comprising the component

A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure.

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Trollhättan, Sweden

Rickard Samuelsson