Combustion system

Claim 2

In combination with a source of compressed air and a source of one of a gaseous and a liquid fuel, a combustion system comprising: a rich zone combustor, means connecting said rich zone combustor to said source of compressed air and to said source of one of said gaseous and said liquid fuel, said fuel being burned in a primary portion of said compressed air in said rich zone combustor at an equivalence ratio exceeding 1 and at on the order of about 2800 degrees F. whereby rapid formation of oxides of nitrogen is inhibited and a continuous stream of combustible hot gas issues from said rich zone combustor, a quench stage connected to said rich zone combustor having a throat portion therein receiving said continuous stream of combustible hot gases, means on said quench stage defining a curtain of one of water and steam stretching across said throat portion and intercepting all of said continuous stream of combustible hot gas to reduce the temperature of said continuous stream of combustible hot gas from on the order of about 2800 degrees F. entering said quench stage to on the order of about 1900 degrees F. exiting said quench stage, a lean zone combustor connected to said quench stage receiving therefrom the total outflow of said quenched combustible hot gas and to said source of compressed air operative to mix said quenched combustible hot gas and a secondary portion of said compressed air to initiate spontaneous combustion of said quenched combustible hot gas in said lean zone combustor at an equivalent ratio of less than 1, said spontaneous combustion generating a continuous stream of non-combustible hot gas motive fluid at a temperature not exceeding about 3000° F., and duct means connected to said lean zone combustor for transporting said non-combustible hot gas motive fluid to a consuming device.

Claim 3

In combination with a source of one of a gaseous fuel and a liquid fuel and a gas turbine engine having a compressor supplying compressed air and a turbine connected to said compressor, an external combustion system for said gas turbine engine comprising: a rich zone combustor including a generally cylindrical combustion chamber centered on a vertical axis and having a circular discharge from said combustion chamber with a first diameter, means connecting said rich zone combustor to said compressor and to said source of one of said gaseous fuel and said liquid fuel, said one of said gaseous fuel and said liquid fuel being burned in a primary portion of said compressed air in said rich zone combustor at an equivalence ration exceeding 1 and at on the order of about 2800 degrees F. whereby rapid formation of oxides of nitrogen is inhibited and a continuous stream of combustible hot gas issues in a downward direction through said circular discharge, a quench stage connected to said rich zone combustor including a cylindrical throat centered on said vertical axis having a second diameter exceeding said first diameter and receiving the total outflow of said continuous stream of combustible hot gas from said rich zone combustor, a plurality of nozzles on said quench stage connected to a source of water and spraying said water across said cylindrical throat whereby a coolant curtain is defined stretching across said quench stage throat in a plane perpendicular to said vertical axis intercepting said continuous stream of combustible hot gas and reducing the temperature thereof from on the order of about 2800 degrees F. entering said quench stage to on the order of about 1900 degrees F. exiting said quench stage, a lean zone combustor connected to said quench stage and to said source of compressed air operative to mix said quenched combustible hot gas and a secondary portion of said compressed air to initiate spontaneous combustion of said quenched combustible hot gas at an equivalence ratio of less than 1, said spontaneous combustion generating a continuous stream of hot gas motive fluid at a temperature not exceeding about 3000° F., a dilution stage connected to said lean zone combustor and to said compressor receiving and mixing said continuous stream of hot gas motive fluid with a dilution portion of said compressed air to reduce the temperature of said continuous stream of hot gas motive fluid to a predetermined turbine inlet temperature, and duct means connected to said dilution stage for transporting said continuous stream of hot gas motive fluid to said turbine.

Claim 4

In combination with a source of one of a gaseous fuel and a liquid fuel and a gas turbine engine having a compressor supplying compressed air and a turbine connected to said compressor, an external combustion system for said gas turbine engine comprising: a rich zone combustor including a generally cylindrical combustion chamber centered on a vertical axis and having a circular discharge from said combustion chamber with a first diameter, means connecting said rich zone combustor to said compressor and to said source of one of said gaseous fuel and said liquid fuel, said one of said gaseous fuel and said liquid fuel being burned in a primary portion of said compressed air in said rich zone combustor at an equivalence ration exceeding 1 and at on the order of about 2800 degrees F. whereby rapid formation of oxides of nitrogen is inhibited and a continuous stream of combustible hot gas issues in a downward direction through said circular discharge, a quench stage connected to said rich zone combustor including a cylindrical throat centered on said vertical axis having a second diameter exceeding said first diameter and receiving the total outflow of said continuous stream of combustible hot gas from said rich zone combustor, a plurality of nozzles on said quench stage connected to a source of water and spraying said water across said cylindrical throat whereby a coolant curtain is defined stretching across said quench stage throat in a plane perpendicular to said vertical axis intercepting said continuous stream of combustible hot gas and reducing the temperature thereof from on the order of about 2800 degrees F. entering said quench stage to on the order of about 1900 degrees F. exiting said quench stage, a lean zone combustor connected to said quench stage and to said source of compressed air operative to mix said quenched combustible hot gas and a secondary portion of said compressed air to initiate spontaneous combustion of said quenched combustible hot gas at an equivalence ratio of less than 1, said spontaneous combustion generating a continuous stream of hot gas motive fluid at a temperature not exceeding about 3000° F., a dilution stage connected to said lean zone combustor and to said compressor receiving and mixing said continuous stream of hot gas motive fluid with a dilution portion of said compressed air to reduce the temperature of said continuous stream of hot gas motive fluid to a predetermined turbine inlet temperature, and duct means connected to said dilution stage for transporting said continuous stream of hot gas motive fluid to said turbine.