A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fiber cloth impregnated with a sacrifi
A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fiber cloth impregnated with a sacrificial resin which has a melting point that is below that of the fiber cloth. When exposed to fire, the fiber cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed.
대표청구항▼
1. An aircraft fire shielding system comprising: a fire-critical aircraft component within a fire risk-zone of the aircraft, the fire-critical component being required to withstand fire for a minimum period of time, the component comprising a body, the system having a protective fire shield covering
1. An aircraft fire shielding system comprising: a fire-critical aircraft component within a fire risk-zone of the aircraft, the fire-critical component being required to withstand fire for a minimum period of time, the component comprising a body, the system having a protective fire shield covering the body, the fire shield directly exposed to said fire-risk zone and separating said fire-critical component from said fire-risk zone, the protective fire shield having an entirely composite construction composed of fibre cloth impregnated with a sacrificial resin, the sacrificial resin having a melting point that is below that of the fibre cloth, the fibre cloth having a melting point that is above an expected temperature of a fire in the fire-risk zone, such that when directly exposed to fire having a temperature of at least 2000° F. within said fire-risk zone the fibre cloth of the protective fire shield remains substantially intact for at least 15 minutes while the sacrificial resin is allowed to be at least partially consumed by the fire thereby absorbing heat energy and limiting heat transfer to the fire-critical component for at least said minimum period of time. 2. The system as defined in claim 1, wherein the sacrificial resin is completely consumed prior to said minimum period of time elapsing. 3. The system as defined in claim 1, wherein the fibre cloth comprises a multiple-ply fibrous matrix. 4. The system as defined in claim 3, wherein the fibrous matrix includes four plies of said fibre cloth. 5. The system as defined in claim 1, wherein the fibre cloth includes carbon fibre and the sacrificial resin includes an epoxy resin. 6. The system as defined in claim 1, wherein the protective fire shield is disposed over of the fire-critical component. 7. The system as defined in claim 6, wherein the protective fire shield is disposed in direct contact with the fire-critical component. 8. The system as defined in claim 1, wherein the fire shield is a structurally self-supporting pre-moulded cover which encloses the fire-critical component. 9. A method of protecting a fire-critical aircraft component from fire for a minimum period of time, the method comprising: providing a fire-critical aircraft component for mounting within a fire-risk zone of the aircraft;providing a fire shield having an entirely composite construction including a fibrous matrix within a sacrificial resin, the step of providing including selecting the fibrous matrix to have a melting point above an expected temperature of a fire within the fire-risk zone such that it remains substantially intact for at least 15 minutes when exposed to fire having a temperature of at least 2000° F. and selecting the sacrificial resin to have a melting point below that of the fibrous matrix; andallowing the sacrificial resin of the fire shield to be at least partially consumed by the fire when the fire shield is exposed thereto, while the fibrous matrix remains substantially intact for at least said minimum period of time. 10. The method as defined in claim 9, further comprising the step of installing the fire shield between the fire-critical part and the fire-risk zone of the aircraft. 11. The method as defined in claim 10, wherein said minimum period of time is defined by airworthiness certification standards. 12. The method as defined in claim 9, wherein the step of allowing further comprises allowing the sacrificial resin to be completely consumed by the time said minimum period of time elapses. 13. The method as defined in claim 9, wherein the fire shield is a structurally self-supporting, pre-moulded cover which encloses the fire-critical component, the method further comprising the step of replacing an original metallic cover enclosing said fire-critical component by the pre-moulded cover such as to retro-fit the gas turbine engine with said composite fire shield. 14. A fire-critical aircraft component, the fire-critical component comprising a body configured for mounting within a fire-risk zone of an aircraft, the component having a protective fire shield covering the body, the fire shield being directly exposed to said fire-risk zone and separating said body of the component from said fire-risk zone, the protective fire shield configured to withstand a 2000° F. fire for at least a 15-minute period, the protective fire shield having an entirely composite construction composed of a fibrous matrix having multiple plies of carbon fibre cloth impregnated with a sacrificial epoxy resin, the sacrificial epoxy resin having a melting point that is below that of the carbon fibre cloth and the carbon fibre cloth having a melting point that is above 2000° F. such that when directly exposed to said 2000° F. fire within said fire-risk zone the carbon fibre cloth of the protective fire shield remains substantially intact for at least said 15-minute period while the sacrificial epoxy resin is configured to be at least partially consumed by the fire before expiry of said 15-minute period, the at least partial consumption of the sacrificial epoxy resin thereby absorbing heat energy and limiting heat transfer to the fire-critical component for at least said 15-minute period. 15. The component as defined in claim 14, wherein the protective fire shield the fibrous matrix of the protective fire shield includes at least four plies of the carbon fibre cloth. 16. The component as defined in claim 14, wherein the sacrificial epoxy resin is completely consumed prior to said certification standard time period elapsing. 17. The component as defined in claim 14, wherein the fire shield is a structurally self-supporting pre-moulded cover which encloses the fire-critical component.
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이 특허에 인용된 특허 (9)
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