Swirl combustor with counter swirl fuel slinger

Power plants – Combustion products used as motive fluid – Process

Reexamination Certificate

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Details

C060S745000, C431S168000, C239S214150

Reexamination Certificate

active

08006500

ABSTRACT:
A combustor for a small gas turbine engine in which a compressor discharges a swirling air flow into the combustor, and a fuel impeller is rotatably connected to the compressor and slings atomized fuel into the combustor in a direction to produce a stagnation zone within the combustor. A plurality of fuel injectors delivers fuel to the inlet end of the fuel impeller. The combustor outlet is a nozzle shape that produces a high enough pressure level in the swirl air flow such that the cooler air flows along the inner combustor wall to form an insulation layer from the hot combustor gas flow within the combustor. The fuel impeller produces a very fine mist of fuel and the stagnation zone produced results in easy starting of the engine and stable combustor burning.

REFERENCES:
patent: 2568921 (1951-09-01), Kroon
patent: 2617252 (1952-11-01), Klein
patent: 2784551 (1957-03-01), Karlby et al.
patent: 2787319 (1957-04-01), Ryder
patent: 2981066 (1961-04-01), Johnson
patent: 3408154 (1968-10-01), Bachi, Jr.
patent: 3932988 (1976-01-01), Beaufrere
patent: 4045159 (1977-08-01), Nishi et al.
patent: 6003297 (1999-12-01), Ziegner
patent: 6925812 (2005-08-01), Condevaux et al.

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