Fan casing for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorJulian M. Reed
Life of this patent
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Abstract
A fan casing for a gas turbine engine has a fan track radially outward of the fan blades, and the fan track has sufficient strength and stiffness that, if a blade is released, it is broken up and deflected by the fan track rather than passing through to a containment system as in known arrangements. Optionally, a weakened region in the fan track may be provided, so that the leading edge portion of the blade will penetrate the fan track and be contained within the fan casing. This is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap.
Claims5
A fan casing for a gas turbine engine, the engine comprising a plurality of fan blades that in use rotate about an axis of the engine, the casing comprising:
- an annular structure radially outward of the fan blades and extending axially both upstream and downstream of the fan blades, in which in use a fan blade may be released in a generally radially outward direction and strike the casing;
- and
- a fan track that in use is radially outward of the plurality of fan blades, the fan track comprising a weakened region so that in use part of a released fan blade can pass into or through the weakened region while a remainder of the released fan blade will be deflected by the fan track, wherein substantially all of the released blade will be deflected by the fan track.
Dependencies are inferred from the claim text.