Lightweight fire protection arrangement for aircraft gas turbine jet engine and method

Abstract

A light weight composite layer arrangement for providing protection for a metal surface from a fire for a predetermined period of time in compliance with Federal Airworthiness Regulation 25. The arrangement which may be easily installed on a metal surface, which typically is an aluminum alloy, includes a silicone rubber sealant layer that is applied to the metal surface in an uncured non-flowing state. A layer of ceramic fiber fabric is then applied to the first silicone rubber sealant layer and due to its inherent flexibility easily conforms to the contours of the underlying metal surface. A second silicone rubber sealant layer may then be applied in its uncured non-flowing state over the ceramic fiber layer to essentially embed the ceramic fabric layer between the two silicone rubber layers. The silicone rubber sealant layers may then be cured at room temperature. Alternatively, the first silicone rubber sealant layer may be cured after application of the ceramic fiber fabric layer and prior to the application of the second silicone rubber sealant layer. Reinforcing or other structures may then be attached to the metal surface, such as by riveting. The resultant protective arrangement is resistant to common solvents, engine oil, hydraulic fluids, and jet fuel and to vibration so as to be able to provide the required fire protection as may be required. The invention finds particular application in the components of an aircraft gas turbine jet engine propulsion system.

Dependencies are inferred from the claim text.