Volvo Aero Corporation

Gknaerospace Sweden Ab

Niklas Jansson

Robert Reimers

Rickard Samuelsson

Anders Sjunnesson

A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing. The first opening extends in a first opening direction which forms an angle with the guide vane direction. The guide vane includes a cover portion including a first material and a core portion which is at least partially enclosed by the cover portion.

Composite guide vane

A gas turbine structure includes a guide vane. The gas turbine structure (further includes a first housing and a second housing and the guide vane extends from the first housing to the second housing. The guide vane includes a leading edge and a trailing edge and the guide vane extends from the leading edge to the trailing edge along a mean camber line. The guide vane includes a first attachment structure, a first fastening arrangement and a second fastening arrangement. Moreover, the first attachment structure includes a stiffening member extending over at least a portion of a circumference of the first housing. Furthermore, the stiffening member includes a stiffening member center point as measured along the mean camber line.

Gas turbine structure

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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Mölndal, Sweden

Niklas Jansson