STAGE-BY-STAGE FUEL COMBUSTION IN BURNER Russian patent published in 2012 - IPC F23R3/34 

FIELD: power industry.

SUBSTANCE: stage-by-stage fuel combustion method at start-up of burner for combustion chamber of gas turbine engine, which includes burner housing enveloping the burner that includes upstream and downstream end parts located in opposite axial direction and auxiliary combustion chamber located on upstream end of the above burner consists in the following: auxiliary combustion chamber is provided with fuel and air for fuel combustion to form the flow of unblocked concentration of radicals on unbalanced level and heat from auxiliary combustion zone, which is directed downstream along axial line of auxiliary combustion chamber through the throat at auxiliary combustion chamber outlet. In addition, burner is provided with the primary combustion space restricted with downstream refractory walls relative to outlet of auxiliary combustion chamber to keep the main flame and arrange the main recirculation zone for circulating unburnt radicals. The above method involves the following stages: fuel mixed with air is added to auxiliary combustion chamber. Mixture is ignited using an ignition device provided on upstream end of auxiliary combustion chamber for initiation of flame of poor mixture inside auxiliary combustion chamber and for supply of the above flow of radicals and heat to downstream combustion space. First vortex of air-and-fuel mixture is supplied on the outside at auxiliary combustion chamber outlet on upstream end of combustion space for creation and keeping of the main flame of poor mixture in the primary combustion space. Then, formation of the second vortex of air-and-fuel mixture is performed from outlet of the first channel for preliminary formation of downstream poor mixture relative to outlet of auxiliary combustion chamber and from outlet of the second channel for preliminary formation of downstream poor mixture relative to the above outlet of the first channel for preliminary formation of poor mixture. Step-by-step addition of the second vortex of air-and-fuel mixture is performed to provide the full-load stage at least to one of the above first and second channels for supply of the main air and fuel flow to the main flame of poor mixture.

EFFECT: stabilisation of combustion in burner for burning in poor and rich zones of partially formed mixture with low contaminant matter, which is intended for combustion chamber of gas turbine in all engine operating modes.

3 cl, 7 dwg