Gas turbine engine component, a turbojet engine provided therewith, and an aircraft provided therewith
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United States of America Patent
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Jun 11, 2013
Grant Date -
May 6, 2010
app pub date -
Mar 28, 2008
filing date -
Mar 30, 2007
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
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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