Combustor for a gas turbine engine

Details Combustor for a gas turbine engine Combustor for a gas turbine engine

1994-09-16

1998-05-05

Freay, Charles G.

Power plants

Combustion products used as motive fluid

60 3936, 60756, 60757, F02G 300

Patent

active

057460485

ABSTRACT:
A compact gas turbine engine having improved fuel efficiency, lower emissions, better starting capability, and longer operational life is provided at low cost through the use of a combustor incorporating tangential fuel injection in conjunction with certain strategically placed and sized oxidant inlet jets. The oxidant inlet jets include deflector jets which deflect a generally circumferentially spiralling flow of gases within the combustor in a manner causing fuel and oxidant to recirculate for a longer period of time within a primary combustion zone, to thereby improve combustion efficiency and reduce undesirable emissions. Apparatus and methods for regulating injection of the fuel and oxidant in or primary, secondary, and dilution zones of the combustor in a manner providing improvements in fuel efficiency, high altitude starting and other advantages are also defined.

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PCT Search Report mailed Jan. 2, 1996 to Intellectual Property Law Department of Sundstrand Corporation.

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