| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a containment assembly for a gas turbine engine especially suitable for use in a composite fan blade or other light weight fan blades. <P>SOLUTION: 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 structure. 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. <P>COPYRIGHT: (C)2010,JPO&INPIT |
