초록 ▼

A combustor for a gas turbine engine including a two-stage burner having first and second combustion and exhaust sections and a burner casing coaxially surrounding the burner to define an annular conduit for reverse flow of inlet air. The burner includes a fuel injector at the upstream end thereof,

A combustor for a gas turbine engine including a two-stage burner having first and second combustion and exhaust sections and a burner casing coaxially surrounding the burner to define an annular conduit for reverse flow of inlet air. The burner includes a fuel injector at the upstream end thereof, primary inlet ports introducing 18% of inlet air into the first combustion section, first cooling ports introducing 12% of inlet air into the first combustion section for generating a swirling cooling flow which mixes with primary air after cooling the upstream end of the first combustion section, secondary inlet ports introducing 18% of inlet air into second stage combustion section, second cooling ports introducing 8% of inlet air into the second combustion section to generate a swirling flow which mixes with primary air after cooling the upstream end of the second combustion section, and dilution ports introducing 44% of inlet air into the exhaust section to cool the exhaust gas.

대표청구항 ▼

A combustor for a gas turbine engine, comprising: (a) a burner defining an axial fluid-flow path between upstream and downstream ends thereof, said burner including a first portion having a constant cross-sectional area and defining a first combustion zone proximate said upstream end, a second porti

A combustor for a gas turbine engine, comprising: (a) a burner defining an axial fluid-flow path between upstream and downstream ends thereof, said burner including a first portion having a constant cross-sectional area and defining a first combustion zone proximate said upstream end, a second portion having constant cross-sectional area greater than said first area and defining a second combustion zone axially downstream of said first combustion zone, and a third portion defining an exhaust zone proximate said downstream end, said first and second cross-sectional flow areas being sized to provide a combustion gas axial velocity of about 150 ft/sec.; (b) a burner casing coaxially surrounding said burner and defining an annular conduit for a flow of inlet air from said downstream to said upstream end of said burner, said burner casing being separated from said burner by the air in said inlet air flow; (c) means at the upstream end of said burner for introducing fuel into said first combustion zone; (d) first primary means at the upstream end of said burner and communicating with said annular conduit for introducing a first primary portion of said inlet air into said first combustion zone and for directing said first primary portion into mixing contact with said fuel; (e) first convection cooling means positioned at the upstream end of said burner and communicating with said annular conduit for introducing a first cooling portion in the amount of about 12% of said inlet air into said first combustion zone and for directing said first cooling portion axially at an angle of inclination to the axial fluid-flow path, said angularly directed first cooling air portion generating a swirling flow of air which initially forms an annular layer proximate the burner wall at the upstream end of the first combustion zone and subsequently radially converges toward said axial fluid-flow path into mixing contact with said first primary portion downstream in said first combustion zone; (f) second primary means positioned in the downstream end of said first burner portion and upstream of said second combustion zone for introducing a second primary portion of said inlet air into said second combustion zone and for directing said second primary portion radially into mixing contact with gases entering said second combustion zone from said first combustion zone, wherein the first burner portion wall between said first cooling means and said second primary means is configured to prohibit the flow of inlet air from said annular conduit to said first combustion zone; (g) second convection cooling means at the upstream end of said second combustion zone and communicating with said annular conduit for introducing a second cooling portion in the amount of about 8% of said inlet air into said second combustion zone and for directing said second cooling portion axially at an angle of inclination to the axial fluid-flow path, said angularly directed second cooling air portion generating a swirling flow of air which initially forms an annular layer proximated the burner wall at the upstream end of the second combustion zone and subsequently radially converges toward the axial fluid-flow path into mixing contact with primary portion downstream in said second combustion zone; and (h) dilution means for introducing a dilution portion of said inlet air into said exhaust zone and for directing said dilution portion into mixing contact with exhaust gas in said exhaust zone.