Gknaerospace Sweden Ab

Volvo Aero Corporation

Robert Reimers

Niklas Jansson

Rickard Samuelsson

Anders Sjunnesson

A method for joining two structural elements by welding, in particular by butt welding comprises forming a weld line joining the two structural elements; and adding material across the weld line, thereby forming one or more crack stoppers for limiting crack propagation along the weld line. The one or more crack stoppers each have a limited extension along the weld line as seen in relation to a length of the weld line. A structural system comprising two structural elements joined by the method is disclosed. The method may be applied, e.g., to components of aircraft engines.

Crack stopper for welds

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 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 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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Uddevalla, Sweden

Robert Reimers