초록 ▼

A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region betwe

A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process.

대표청구항 ▼

1. A fan section of a gas turbine engine comprising: a fan having a rotational axis and radially extending fan blades from which ice may be shed in a first direction having a radial and an axial component during operation of the engine, and all or part of a blade of the blades may become detached so

1. A fan section of a gas turbine engine comprising: a fan having a rotational axis and radially extending fan blades from which ice may be shed in a first direction having a radial and an axial component during operation of the engine, and all or part of a blade of the blades may become detached so as to be ejected from the fan in a second direction having a radial and a circumferential component during operation of the engine, anda fan casing liner panel comprising a first sheet element of composite material and a second sheet element of cellular material having a septum layer on one surface of the cellular material, the first sheet element being bonded in face to face relationship to the septum layer of the second sheet element, whereinthe septum layer is perforated, and the perforations comprise holes disposed in a plurality of rows to form lines of preferential weakness to ease passage of the blade or part thereof into the liner panel, each of the plurality of rows extending circumferentially about the rotational axis of the fan in a plane extending perpendicular to the rotational axis, each of the holes being spaced further apart from the nearest hole in an axial direction than from the nearest hole in the circumferential direction, the lines of preferential weakness being aligned with the circumferential component of the second direction, the holes being spaced further apart in a direction at an angle to the lines of preferential weakness to thereby provide lines of enhanced resistance to fracture by impact of ice shed in the first direction. 2. The fan section of claim 1, wherein the cellular material of the second sheet element comprises elongate cells which extend in a direction across the thickness of the second sheet element. 3. The fan section of claim 1, wherein the cellular material of the second sheet element is a metallic material. 4. The fan section of claim 1, wherein the first sheet element comprises a cellular composite material. 5. The fan section of claim 4, wherein the cellular composite material comprises a matrix of composite material having cells which are filled with a filler. 6. The fan section of claim 1, wherein the first sheet element is bonded to the septum layer over substantially the full area of the first sheet element. 7. The fan section of claim 1, wherein the rows of holes extend in the circumferential direction with respect to the rotational axis of the fan. 8. The fan section of claim 1, wherein the holes have a transverse dimension which is not less than 1 mm. 9. The fan section of claim 1, wherein adjacent holes are spaced apart by not less than 4 mm. 10. A gas turbine engine having the fan section of claim 1. 11. A method of manufacturing the fan section of claim 1, which method comprises the steps of: applying a bonding agent to at least one of the first sheet element and the septum layer;placing the first sheet element and the septum layer in face to face contact with the bonding agent between them;placing the first sheet element and the second sheet element in an enclosure;evacuating the enclosure to draw air through the perforated septum layer from the region between the first sheet element and the septum layercausing or allowing the bonding agent to set or cure. 12. A gas turbine engine manufactured by the method of claim 11.