| 摘要 |
A flow reverser comprises first 1 and second 2 parts defining a flow path B which are axially separable from each other about a conjunction formed by respective profile edges 3, 4 of the first and second parts. The profile edges 3, 4 overlap in the stowed position. In the deployed position the profile edges 3, 4 define a nozzle which has a width that varies along the circumferential direction of the engine casing. The reverser nozzle is preferably wider at the centre, that at the upper and lower ends. The profile edges ideally define a crescent (or 'half-moon') nozzle and jet in the deployed position. Ideally, one of the profile edges defines a reverser part 5 located adjacent the core 6 which serves to deflect the bypass flow B to provide reverse thrust BR. The reverser part 5 may seal against a hump 7 part of the core 6 when the cowling axially separates. |
