Turbojet architecture with two fans at the front

Details Turbojet architecture with two fans at the front Turbojet architecture with two fans at the front

2005-01-26

2008-08-19

Look, Edward (Department: 3745)

Power plants

Reaction motor

Interrelated reaction motors

C060S268000, C415S068000, C415S144000, C415S213100

Reexamination Certificate

active

07412819

ABSTRACT:
A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.

REFERENCES:
patent: 3486328 (1969-12-01), Boudigues
patent: 3713748 (1973-01-01), Langley
patent: 3861139 (1975-01-01), Jones
patent: 4860537 (1989-08-01), Taylor
patent: 2003/0163983 (2003-09-01), Seda et al.
patent: 0 623 736 (1994-11-01), None
patent: 1 340 903 (2003-09-01), None
patent: 2 189 844 (1987-11-01), None

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