Abstract: A gas turbine combustor of the pre-mixed combustion system in which the pre-mixed fuel and the air are combusted. The gas turbine combustor comprises main cylindrical nozzles provided in the end wall on the upstream side of a cylindrical combustion chamber, auxiliary nozzles formed to surround the main nozzles, a main pre-mixed gas supply for supplying a pre-mixed gas to the main nozzles, and an auxiliary pre-mixed gas supply for supplying a pre-mixed gas having an fuel/air ratio smaller than that of the main pre-mixed gas to the auxiliary nozzles, and wherein it is allowed to stably burn a lean pre-mixed gas having an fuel/air ratio of greater than 1 from a low-load condition through and up to a high-load condition of the gas turbine.

Abstract: A premixed combustor for a gas turbine, comprises, a combustion chamber for burning a fuel with an air therein, at least two premixed fuel/air mixture outlets which are juxtaposed with each other, and through each of which a premixed fuel/air mixture flows out into the combustion chamber, and a flow deflection member arranged between the premixed fuel/air mixture outlets, urging the permixed fuel/air mixture from one of the premixed fuel/air mixture outlets to go away from another one of the premixed fuel/air mixture outlets, and terminating in the combustion chamber so that the premixed fuel/air mixture from the one of the premixed fuel/air mixture outlets is permitted to move toward the premixed fuel/air mixture flowing out from the another one of the premixed fuel/air mixture outlets after going away from the another one of the premixed fuel/air mixture outlets.

Abstract: A burner comprises at least one swirl member for mixing a fuel with an air previously to burning of the fuel, and at least one eddy generating device which is arranged in a flow of a mixture of the fuel and air to generate an eddy flow in the flow so that the eddy flow maintains a shape of a flame of the burned fuel. The at least one eddy generating device is arranged apart from a downstream end of the swirl member by a fixed sufficient distance so that the shape of the flame maintained by the eddy flow is prevented from moving toward the downstream end of the swirler member.

Abstract: Method of burning a premixed gas and a combustor for practicing the method. A jet of the premixed gas is burnt from an inside to an outside of the jet to form a premix flame. A burned gas is mixed into the premixed gas from the outside of the jet. The burned gas is produced when premixed gas is burned.

Abstract: A combustor includes a first premixture supply device provided in a central portion of a combustion chamber disposed generally concentric with a combustion cylinder, and a second premixture supply means provided adjacent to an outer periphery of the first premixture supply device. The first premixture supply device is operable when the combustor is under a high load, and the second premixture supply device is operable when the combustor is under a low load. A method of operating a combustor is also proposed wherein the combustor comprises a combustion cylinder having a combustion chamber therein and a premixture supply device provided on one side of the combustion cylinder for supplying a combustible mixture to the combustion chamber. The premixture supply device comprising at least two inner and outer premixture supply devices.

Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber.

Abstract: A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.

Abstract: A combustor for driving a gas turbine includes a first burning stage and a second burning stage. The combustor further comprises a primary combustion chamber in which air from the associated compressor and fuel are burnt, a pre-mixing chamber in which air from the associated compressor and fuel are pre-mixed, a main combustion chamber in which fuel/air mixture is burnt and forwarded to the gas turbine, an air passage provided in a wall of the main combustion chamber, through which air from the compressor flows to cool the wall thereof, and an intercommunicating air passage for intercommunicating the air passage to the pre-mixing chamber, whereby cooling air for the main combustion chamber wall is used to supplement the air in the pre-mixing chamber.

Abstract: A gas turbine combustor comprising a head combustion chamber and a rear combustion chamber connected to a downstream side of the head combustion chamber, a first stage burner for premixing first stage fuel and air and supplying the resultant fuel and air premixture into the head combustion chamber to effect first stage premix combution, a second stage burner for premixing second stage fuel and air and the resultant fuel and air premixture into the rear combustion chamber to effect premix combustion in addition to the first stage premix combustion, and a device for regulating flow rates of combustion air to be premixed with first and second stage fuel. The combustor is further provided with a pilot burner in the head combustion chamber to form pilot flame and stabilize the first stage premix combustion.

Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Abstract: A gas turbine combustor comprises a combustion chamber, a premixing chamber in which hydrocarbon fuel and air are premixed, a nozzle with swirler for swirling and injecting the premixed fuel and air into the combustion chamber, to effect premixed combustion, and a fuel nozzle projecting into the combustion chamber and adapted to inject fuel at region wherein the premixed combustion is completed, so as to effect low air-ratio diffusion combustion thereby to produce reducing substance. NOx produced by the premixed combustion is reduced by reducing reaction with the reducing substances, so that the NOx concentration in the combustion gas is reduced. The combustor further includes an after-air ports on a peripheral wall defining the combustion chamber to effect combustion of unburnt substances.

Abstract: A low NOx burning method and apparatus wherein a low air ratio flame burned with an amount of air less than an amount of air in a theoretical air ratio required for burning fuel perfectly is formed, and combustibles discharged from the low air ratio flame are burned at a trailing stream of the low air ratio flame while supplying air. The low air ratio flame is a premixing flame burned by premixing the fuel and air, and combustion of the premixing flames is maintained in the vicinity of the premixing flame. In this way, the generation of the NOx during the burning can be greatly decreased, and the required apparatus can be small-sized.

Abstract: A gas turbine combustor for reducing a production of NOx. The combustor includes a head combustion chamber and a rear combustion chamber which is larger in diameter than the head combustion chamber. The head combustion chamber is provided with an axially extending hollow frustoconical tubular member to form an annular combustion space therein, air holes for axially jetting air into the annular combustion chamber, air holes formed on a peripheral wall for injecting air and a plurality of fuel nozzles projected into the annular combustion space for injecting fuel into vortex formed by the air jet and the injected air flow whereby the flame is stabilized and lean combustion can be effected. The rear combustion chamber has a fuel and air supply means on the upstream side which includes air inlets formed by whirling vanes and fuel nozzles disposed in the air inlets so that fuel and air are mixed well.

Abstract: A combustor of two-stage combustion type in which fuel is supplied only from primary fuel nozzles for combustion only in primary combustion chamber under the operating condition where gas turbine load is low, and premixed mixture is supplied into a secondary combustion chamber provided on the downstream side of the primary combustion chamber for combustion in both the primary and secondary combustion chambers under the operating condition where the load is high. An air-bleed passageway opens on a downstream side of air holes for intaking secondary combustion air to be mixed with secondary fuel and communicates with the outside of the combustor. The air-bleed passageway is provided with a regulating valve and the secondary combustion air is bled at the minimum point of the load where the secondary fuel is supplied so that the fuel to air ratio of secondary premixed mixture may not be excessively lean, thereby reducing the production of non-burned components.

Abstract: A gas turbine combustor has a plurality of burner units each having an inner tube defining a combustion chamber therein and an outer tube surrounding the inner tube coaxially therewith. A fuel is injected into the head portion of the inner tube and is burnt in the combustion chamber to produce hot combustion gases which are guided through a tail tube to stationary blades of a gas turbine. Combustion air is supplied through an annular passage between the inner and outer tubes from the area around the tail tube to the head portion of the inner tube. A flow-uniformalizing tube is disposed between the inner and outer tubes to cooperate with the inner tube to define therebetween an air passage.

Abstract: A method of starting a gas turbine plant, which plant has at least one combustor including a primary combustion chamber into which primary fuel nozzles open and a secondary combustion chamber into which secondary fuel nozzles open, a compressor for supplying the combustor with compressed combustion air, and a gas turbine driven by the combustion gas generated in the combustor and adapted to drive a load such as an electric power generator. When the gas turbine is being accelerated to a rated speed or while the load is still below a normal load range, a fuel is supplied only to the primary fuel nozzle, whereas, in other loaded operation range, the fuel is supplied to both the primary and secondary fuel nozzles. Before the fuel supply to the secondary fuel nozzles is commenced, a part of the compressed air is bled through at least one air bleed pipe leading from the compressor and having an air bleed valve.

Abstract: A gas turbine combustor having a head combustion chamber and a rear combustion chamber, with a plurality of air supply ports arranged in a circumferential wall of the rear combustion chamber, and a fuel nozzle. An outer cylinder forms a cylindrical air flow passage between the inner cylinder and the outer cylinder. A cylindrical control member is provided which is adapted to be movable in an axial direction for regulating an opening of the air supply ports. The control member is supported by a supporting means which is adapted to maintain a gap between the control member and the wall of the rear combustion chamber. The supporting member includes a flexible member for absorbing a deformation of the control member during the axial movement of the control member so that it is possible to prevent, if not avoid, mechanical wear on the control member and to reduce the No.sub.x concentration as well as obtain a highly reliable operation of the gas turbine combustor.

Abstract: A premixture of compressed air and gaseous fuel is supplied and conbusted into a head combustion chamber of a combustor for gas turbine and main combustion of lean, low flame temperature is carried out in a rear combustion chamber following the heat combustion chamber to prevent the formation of high flame temperature which tends to promote NOx generation.

Abstract: A fuel supply method for a gas turbine combustor having first and second stage combustion chambers. The method comprises supplying the fuel from only first stage fuel supply from the start of the gas turbine until its low output range so as to operate only the first stage combustion chamber, supplying the fuel from both first and second stage fuel supply in a high output range of the gas turbine including its maximum output so as to operate both first and second stage combustion chambers. The method makes it possible to reduce NO.sub.x without deteriorating the combustion performance by step-wise supplying a predetermined flow rate of the fuel when the second stage fuel is to be supplied and at the same time, step-wise reducing the same quantity of the fuel that is being supplied from the first stage fuel supply.

Abstract: A gas turbine combustor comprises an inner cylinder provided with louvers in an outer periphery thereof, defines a head combustion chamber and a main combustion chamber located downstream of and greater in diameter than the head combustion. An outer cylinder surrounds the inner cylinder and defines an air passage therebetween. A first burner communicates with the head combustion chamber and supplies air with gaseous fuel, and a second burner being disposed in the air passage near the head combustion chamber and supplying air and gaseous fuel into the main combustion chamber. The second burner is formed with a plurality of air inlets by a plurality of vanes which are disposed in an annular passage and which swirl the air, and with gaseous fuel jet ports near the inner peripheries of the air inlets.