Volvo Aero Corporation

Gknaerospace Sweden Ab

Anders Sjunnesson

Robert Reimers

Joakim Berglund

Niklas Jansson

Rickard Samuelsson

Jens Dahlin

Patrik Johansson

Alf Andersson

Sonny Lundgren

Rolf Gabrielsson

Stefan Hansson

Torbj&ouml;rn Salomonson

Henrik Johansson

Peter Ivarsson

Ola Isaksson

Peter Emvin

Ronald Borg

Mathias Andersson

Henrik Karlsson

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.

Gas turbine engine component, a turbojet engine provided therewith, and an aircraft provided therewith

A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell.

Static gas turbine component and method for repairing such a component

In an annular torsional rigid static component for an aircraft engine, the component includes at least one arrangement for mounting the engine to an aircraft. The mounting arrangement comprises a body formed in a composite material.

Annular torsional rigid static component for an aircraft engine

The invention refers to a flameholder device for afterburners in gas turbine engines with a cooling air fan of by-pass type, comprising a plurality of radial flameholder means ( ) which at their radially outer end are mounted to the afterburner casing ( ) and have a longitudinal air channel which ends at the radially inner end of said means ( ), at which end is arranged a circumferentially extending arcuate flameholder gutter. In order to provide for a relief of the stresses from said flameholder device on the casing ( ) it is suggested according to the invention that the flameholder means ( ) at their radially outer ends each are pivotably and releasably mounted to said casing and in that the gutters of the respective flameholder means are formed as a common integral annular supporting and load-carrying body ( ).

Flameholder device for afterburners in gas turbine engines

Low-emission combustion chamber for gas turbine engines

Growing community of inventors

Trollhättan, Sweden

Anders Sjunnesson