Flow diverter system for multiple streams for gas turbine engine

Details Flow diverter system for multiple streams for gas turbine engine Flow diverter system for multiple streams for gas turbine engine

1998-05-30

2000-08-15

Eldred, J. Woodrow

Aeronautics and astronautics

Aircraft power plants

244 23D, 602261, 602263, 60229, 60266, 60228, 602262, B64B 124

Patent

active

061023299

ABSTRACT:
A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

REFERENCES:
patent: 4463921 (1984-08-01), Metz
patent: 4482107 (1984-11-01), Metz
patent: 4519543 (1985-05-01), Szuminski et al.
patent: 4552309 (1985-11-01), Szuminski et al.
patent: 4805401 (1989-02-01), Thayer et al.
patent: 5082209 (1992-01-01), Keyser
patent: 5098022 (1992-03-01), Thayer
patent: 5809772 (1998-09-01), Giffin, III et al.

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