Burner and process for operating gas turbines

Details Burner and process for operating gas turbines Burner and process for operating gas turbines

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/18 (2006.01) F23R 3/28 (2006.01)

Patent

CA 2354520

A porous, low-conductivity material formed of metal or ceramic fibers provides the burner face of a gaseous fuel combustor for gas turbines capable of minimizing nitrogen oxides (NO x) emissions in the combustion product gases. A preferred burner face when fired at atmospheric pressure, yields radiant surface combustion with interspersed areas of blue flame combustion. A rigid but porous mat of sintered metal fibers with interspersed bands of perforations is illustrative of a preferred burner face that can be fired at pressures exceeding 3 atmospheres at the rate of at least about 500,000 BTU/hr/sf/atm.

L'invention porte sur un matériau poreux à faible conductivité constitué de fibres métalliques ou céramiques, qui forme l'orifice (39) d'un brûleur à combustible gazeux (16) équipant des turbines à gaz capables de réduire au minimum les émissions d'oxyde d'azote (NOx) dans les gaz des produits de combustion. Un orifice (39) préféré, lorsqu'il est enflammé à la pression atmosphérique, donne une combustion de surface rayonnante présentant des zones intercalées de combustion à flamme bleue. Un tapis (107) rigide mais poreux de fibres métalliques frittées comportant des bandes de perforations intercalées caractérise un orifice préféré pouvant être enflammé à des pressions supérieures à 3 atmosphères à un taux d'au moins 500.000 Btu/h/m<2>/atm.

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