| 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 liner extending only over an upstream part of the fan blades, and the local stiffness and internal shape of the casing are structured to promote the break-up of a released fan blade while permitting the leading edge region of the blade to pass through the fan track liner and be contained by the fan casing. This structure 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 |
