Patent ID: 7914251
Filing Date: 2011-03-29
Classification: F01D,F02C,F02K

Abstract:
1. A liner panel for an annular fan casing of a gas turbine engine, the engine including a plurality of generally radially-extending fan blades that are located radially inward of the fan casing and, in use, rotate about an axis concentric with the fan casing, wherein, in use, ice may be released from a fan blade in a first direction, the first direction forming a first angle with a radial direction of the engine, and wherein, in use, a fan blade or part of a fan blade may be released in a second direction, the second direction forming a second angle with a radial direction of the engine, the liner panel having a compressive strength greater in the first direction than in the second direction such that the released ice will be deflected by the liner panel but the released fan blade or part of a fan blade will pass through the liner panel, wherein the liner panel comprises an ice impact layer including a layer of a first honeycomb material, wherein, in use, cell walls of the first honeycomb material are aligned substantially in the first direction.