Gas turbine combustor swirl vane arrangement

Power plants – Combustion products used as motive fluid – With variable oxidizer control

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60737, 60748, 60747, F02C 920, F23R 314

Patent

active

053946880

ABSTRACT:
A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages, each of which has a circumferential array of individually rotatable swirl vanes. The swirl vanes are mounted on axially oriented primary fuel pegs that extend through the air inlet passages. The middle and outer liners form an outer annular passage in which radially oriented secondary fuel pegs are disposed. The middle and inner liners form an inner annular passage that is supplied with cooling air. A perforated circumferentially extending baffle is locating in the inner annular passage and directs the cooling air to flow over the inner liner.

REFERENCES:
patent: 2271587 (1942-02-01), Haynes
patent: 2439554 (1948-04-01), Anderson
patent: 2889871 (1959-06-01), Voorheis
patent: 4907962 (1990-03-01), Azuhata et al.
patent: 5117637 (1992-06-01), Howell et al.
patent: 5145359 (1992-09-01), Ancona et al.
Willis et al., "Industrial RB211 Dry Low Emission Combustion", ASME Journal, pp. 1-7 (1993).

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