Gas turbine engine

Power plants – Combustion products used as motive fluid – Multiple fluid-operated motors

Reexamination Certificate

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Details

C060S039250, C060S726000

Reexamination Certificate

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06865891

ABSTRACT:
A gas turbine engine (10) comprises a first compressor (16), a combustor (22) and a first turbine (24) arranged in flow series. The first turbine (24) is arranged to drive the first compressor (16). The first compressor (16) has variable inlet guide vanes (38) and the first turbine (24) has variable inlet guide vanes (42). A second compressor (48) is arranged upstream of the first compressor (16). An auxiliary intake (12) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). A valve (54) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). The valve (54) is movable between a first position in which the second compressor (48) supplies air to the first compressor (16) and a second position in which the second compressor (48) does not supply fluid to the second compressor (16) and the auxiliary intake (12) supplies fluid to the first compressor (16). A drive means (60,62,64,66) is arranged to selectively drive the second compressor (48).

REFERENCES:
patent: 3548597 (1970-12-01), Etessam
patent: 3585795 (1971-06-01), Grieb
patent: 3899886 (1975-08-01), Swick
patent: 4160362 (1979-07-01), Martens et al.
patent: 4803837 (1989-02-01), Simmons
patent: 6332313 (2001-12-01), Willis et al.
patent: 20010020360 (2001-09-01), Tsukamoto
patent: 20010039794 (2001-11-01), Rocklin
patent: 0770771 (1996-10-01), None
patent: 2280223 (1995-01-01), None
patent: 2301402 (1996-04-01), None
patent: 103080 (1998-04-01), None
patent: WO 05904 (1994-03-01), None

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