[특허]Fan case liner for a gas turbine engine with improved foreign body impact resistance

Fan case liner for a gas turbine engine with improved foreign body impact resistance 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-021/00
출원번호	US-0660302 (1991-02-25)
발명자 / 주소	Clarke Jonathan P. (West Chester OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 46 인용 특허 : 0

초록 ▼

A fan case liner for a gas turbine engine includes a foreign body impact resistant area and a sound suppression area. The foreign body impact resistant area includes a face sheet of a high impact resistant material which substantially resists denting when struck by a foreign body. A first honeycombed layer of aluminum or an aluminum alloy is disposed over and attached to the face sheet. The first layer has a selected compressive strength to distribute loading forces caused by the impact of a foreign body and to resist plastic deformation. The hexagonally shaped voids in the honeycombed structure of the first layer are filled with a microballoon/resin filler material to further improve resistance to damage or denting. At least one second honeycombed layer of a aluminum or an aluminum alloy is disposed over and attached to the first honeycombed layer. The at least one second layer has a compressive strength greater than the first layer to further distribute forces caused by the impact of a foreign body and to further resist denting or plastic deformation of the fan case liner. A backsheet may be disposed over and attached to the second honeycombed layer.

대표청구항 ▼

A fan case liner for a gas turbine engine, comprising: a foreign body impact resistant area, including: a face sheet including multiple plies of an impact resistant material which substantially resists plastic deformation when struck by a foreign body; a first honeycombed layer disposed over and attached to said face sheet, said first honeycombed layer being made of one of aluminum and an aluminum alloy and having a multiplicity of hexagonally shaped cells formed therein, each of said cells having a selected width and a selected wall thickness to provide a selected compressive strength to resist plastic deformation of the fan case liner; a microballoon filler material disposed within each of said cells of said first honeycombed layer to increase the compressive strength of said first layer and to distribute the forces caused by the impact of a foreign body to further resist plastic deformation of the fan case liner; at least one second honeycombed layer disposed over and attached to said first honeycombed layer, said at least one second honeycombed layer being made of one of aluminum and an aluminum alloy and having a multiplicity of hexagonally shaped cells formed therein, each of said cells having a chosen width and a chosen wall thickness to provide a compressive strength greater than said selected compressive strength of said first honeycombed layer to further distribute foreign body impact forces and to resist plastic deformation of the fan case liner; and a backsheet disposed over and attached to said at least one second honeycombed layer. A method for making a fan case liner for a gas turbine engine, comprising the steps of: forming a face sheet of a first selected number of plies of fiberglass material; forming a backsheet of a second selected number of plies of fiberglass material; forming a first honeycombed layer made of one of aluminum and an aluminum alloy, the first layer having a multiplicity of hexagonally shaped cells formed therein, each of said cells having a selected width and wall thickness to provide a selected compressive strength; filling the first honeycombed layer cells with a microballoon filler material to further increase the compressive strength of the first layer to prevent denting when impacted by a foreign body; forming a second honeycombed layer made of one of aluminum and an aluminum alloy, the second honeycombed layer having a multiplicity of hexagonally shaped cells formed therein, each of said cells having a chosen width and a chosen wall thickness to provide a chosen compressive strength; attaching the backsheet to one surface of the second honeycombed layer by an adhesive; attaching an opposite surface of the second honeycombed layer to one surface of the first honeycombed layer by an adhesive; and attaching the face sheet to an opposite surface of the first honeycombed layer by an adhesive.

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Fan case liner for a gas turbine engine with improved foreign body impact resistance 원문보기

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Fan case liner for a gas turbine engine with improved foreign body impact resistance 원문보기

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