MULTILAYER SHIELDING RING FOR A FLIGHT DRIVING MECHANISM
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United States of America Patent
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Issued Date -
Aug 12, 2010
app pub date -
Aug 27, 2008
filing date -
Sep 7, 2007
priority date (Note) -
Abandoned
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Abstract
A shielding (6) of a turbine housing (3) of an aircraft engine against radial escape of blade fragments, especially for a high-speed low-pressure turbine, is characterized in that the shielding (6) is embodied as a rigid ring-shaped component of several layers (8). Through the decoupling of the containment function from the design of the turbine exhaust gas channel, which is fabricated as a cast part, the disadvantages of the prior art are avoided. Particularly, the design of the turbine exhaust gas channel can be carried out in a cost- and weight-optimized manner.
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