Aircraft engine arrangement

Power plants – Reaction motor – Interrelated reaction motors

Reexamination Certificate

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Details

C060S802000

Reexamination Certificate

active

07484354

ABSTRACT:
In order to avoid external bulging (5) to accommodate accessory mechanisms (27) and gearboxes (30) to drive these mechanisms (27) in accordance with the present invention splitter fairings (26) are located within a bypass duct (23) of an engine (20). The bypass duct (23) is defined between a casing (21) and compressor/turbine propulsion core (22). The fairings (26) are of sufficient dimensions to accommodate the accessory mechanisms (27) whilst the bypass duct (23) is appropriately shaped axi-symmetrically to eliminate and balance any blocking effect of these fairings (26) within the duct (23) upon air flow (24). Further fairings (26′) may be provided to accommodate oil tank reservoirs (34) as well as filter/heat exchanger mechanisms (35) for the engine (20). In such circumstances, a notional elongate cylindrical profile for the engine (20) is maintained such that a reduced cross section is require for that engine (20) and so allowing a smaller airframe with better sonic boom signature.

REFERENCES:
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patent: 4437627 (1984-03-01), Moorehead
patent: 5143329 (1992-09-01), Coffinberry
patent: 5410870 (1995-05-01), Brault et al.
patent: 6134880 (2000-10-01), Yoshinaka
patent: 6289665 (2001-09-01), Saiz
patent: 0 642 585 SP (1950-09-01), None
patent: 0 744 695 SP (1956-02-01), None
patent: 1 127 659 SP (1968-09-01), None
patent: 1 277 853 SP (1972-06-01), None
patent: 1 358 076 SP (1974-06-01), None
patent: 2041090 (1980-09-01), None

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