Gas turbine combustor swirl vane arrangement
AssigneeWestinghouse Electric Corp.
InventorDavid J. Amos
Life of this patent
Estimating the term…
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.
Claims8
A gas turbine comprising:
- a) a compressor section for producing compressed air;
- b) a combustion section in which said compressed air is heated, said combustion section including a combustor having (i) an air inlet, having a first passage and a second passage, in air flow communication with said compressor section, (ii) a plurality of first swirl vanes disposed in said first passage and a plurality of second swirl vanes disposed in said second passage for imparting a first swirl angle to at least a first portion of said compressed air and a second swirl angle to a second portion of said compressed air, and (iii) means for rotating each of said first swirl vanes and second swirl vanes into at least first and second positions, whereby said first swirl angle and said second swirl angle may be adjusted;
- and
- means for introducing a fuel into said air inlet.
A turbine, comprising:
- a compressor section for producing compressed air;
- a combustion section in which said compressed air is heated, said combustion section including a combustor having an air inlet, having first and second annular passages, in air flow communication with said compressor section;
- a plurality of first swirl vanes disposed in said first passage and a plurality of second swirl vanes disposed in said second passage for imparting a first swirl angle to at least a first portion of said compressed air and a second swirl angle to a second portion of said compressed air, said first swirl angle opposing said second swirl angle;
- means for rotating each of said first swirl vanes and said second swirl vanes into at least first and second positions whereby said first swirl angle and said second swirl angle may be adjusted;
- means for locking said first swirl vanes and said second swirl vanes into a predetermined angular orientation;
- and
- a plurality of fuel injectors having a plurality of fuel discharge ports extending radially into said first passage and said second passage for introducing a fuel into said air inlet.
Dependencies are inferred from the claim text.