Gknaerospace Sweden Ab

Per Widstrom

Egon Aronsson

Johan Tholérus

Elinor Magnusson

Christian Lundh

An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.

Aircraft engine lubricant circulation

The present invention relates to a support structure () for a gas turbine engine (). The support structure () has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure () comprises a plurality of tubular members () of a first material type arranged in sequence in the circumferential direction (C). Each tubular member () at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure () comprises a leading portion () and a trailing portion () in the axial direction (A). Furthermore, the support structure () comprises a leading edge member () of a second material type, the leading edge member () being located at the leading portion (). At least two of the tubular members () are fixedly attached to a leading edge member (). According to the present invention, the first material type is different from the second material type.

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Grastorp, Sweden

Per Widstrom