초록 ▼

A fire seal (52) for an aircraft propulsion system including at least one mating plate pair (54) formed between a nozzle body (44) and an outer structure (24) and a support pylon (26). The mating plate pairs (54) each include an upper plate row (58) and a lower plate row (60), both rows extending in

A fire seal (52) for an aircraft propulsion system including at least one mating plate pair (54) formed between a nozzle body (44) and an outer structure (24) and a support pylon (26). The mating plate pairs (54) each include an upper plate row (58) and a lower plate row (60), both rows extending in an arc (66) about an upper region (56) of the propulsion system, with a vertical overlap (88) existing between the upper and lower plate rows. A gap (90) exists between the upper plate row (58) and lower plate row (60) of each mating plate pair (54), preferably at all times. A seal region (62) exists between the forward-most mating pair and the aft-most mating pair. A pressure equalization mechanism controls pressure between the area forward of the seal region (62) and the area aft of the seal region (62). A number of endplates (110) are positioned at various longitudinal locations near the lateral ends of the mating plate pairs. A method of fire-sealing an aircraft propulsion system fire zone area including providing at least one mating plate pair (54) positioned between opposed surfaces in order to create a labyrinth path through which flame has difficulty passing. The method further includes controlling pressure between the area forward of the mating plate pairs and the area aft of the mating plate pairs.

대표청구항 ▼

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] A fire seal for an aircraft power generation system for discouraging the passage of flame between two regions, the aircraft power generation system having a first surface in oppose

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] A fire seal for an aircraft power generation system for discouraging the passage of flame between two regions, the aircraft power generation system having a first surface in opposed relation to a second surface, the fire seal comprising at least one mating plate pair formed between the first surface and the second surface and oriented in a manner transverse to an anticipated direction of flame travel, each mating plate pair comprising an upper plate row and a lower plate row, both rows being positioned between the first and second surface in a generally parallel-planar orientation, a portion of noncontacting overlap existing between the upper and lower plate rows; and further including a means for equalizing pressure between the area forward of the fire seal and the area aft of the fire seal. [7.] A method of fire-sealing an aircraft propulsion system fire zone area comprising the steps of providing at least one mating plate pair having upper and lower plate rows connected to generally opposed surfaces in a propulsion system fire zone, the at least one mating plate pair for creating a labyrinth path through which flame has difficulty passing; and positioning the upper and lower plate rows near each other to form a gap therebetween and a portion of vertical overlap,further comprising the step of providing endplates positioned at the lateral ends of the mating plate pairs, the endplates for adding additional corners to the labyrinth path.