摘要:
A method for controlling a gas turbine combustor which comprises nozzles for injecting fuel into a combustor and which serves to combust the fuel with air in a combustion chamber so as to rotatively drive a gas turbine by combustion gas compressed as a result of combustion of a fuel, wherein the ratio of a flow rate of fuel supplied into the combustor to a flow rate of air supplied into the combustor is changed in accordance with at least one of the states of fuel, air and rotational frequency of the turbine.
摘要:
A gas turbine combustor has an inner cylinder provided with a multiplicity of louvers for introducing cooling air and a plurality of air ports for introducing combustion air. The portions of the inner cylinder wall at both ends of each louver, where the concentration of stress due to thermal stress is heaviest, is reinforced by build-up welding thereby to prevent cracking at these portions of the cylinder wall. The build-up welding effectively stops the propagation of crack happened to be caused in the inner cylinder wall for any reason. The portions of the inner cylinder wall around the air ports also may be reinforced by build-up welding over the entire peripheries of these air ports. The build-up weld on the periphery of each air port prevents any crack from being propagated to the brim of each air port.
摘要:
In a combustion air flow rate adjusting device in which a cylindrical regulating ring fitted about an outer peripheral surface of an inner cylinder of a gas turbine combustor is translated along the outer peripheral surface of the inner cylinder in order to vary an opening area of air intake ports formed in the peripheral wall of the inner cylinder, an arcuately moving part at a forward end of a lever fixedly connected to a forward end of a shaft extending inwardly through a peripheral wall of an outer cylinder of the gas turbine combustor is connected to a part reciprocating together with the regulating ring, by leaf springs.
摘要:
A surface, of an inner sleeve of a combustion apparatus for a gas turbine, which is subjected to a flame radiation heat is coated with a ceramic coating. A coating which is superior in high temperature corrosion resistant characteristics to a metal material forming the inner sleeve is provided on the opposite surface of the inner sleeve. Thus, heat transferred to the inner sleeve by the radiation from the flame is shielded by the ceramic coating. A formation of oxides on the coating of the corrosion resistant metal material formed on the opposite surface of the sleeve is prevented. A heat release through the surface from the metal material forming the inner sleeve is enhanced, whereby a thermal stress generated in the inner sleeve is suppressed to thereby prevent a generation of a cracks.
摘要:
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.
摘要:
A gas turbine apparatus has a gas turbine and a plurality of burners for providing combustion gas to drive the turbine. A flow control means of each burner for fuel or combustion air is adjusted by control means to control each said burner individually in dependence on a predetermined combustion characteristic of the respective burner. Sensed quantities relating to the combustion performance of the burners are input to the control means which adjusts the flow control means of each burner in dependence on the sensed quantities and the predetermined combustion characteristic of the respective burner.
摘要:
A combined gas turbine plant comprises an air compressor, a combustor including a combustion chamber, a gas turbine, a steam turbine, and an exhaust heat recovery device having a denitration device and arranged at a location through which an exhaust gas passage for leading exhaust gas from the gas turbine to the atmosphere extends. An air extraction pipe equipped with a valve is provided for extracting a part of the air from the air compressor to prevent surging of the air compressor during starting of the plant, and another air extraction pipe equipped with a valve is provided for extracting a part of the air from an air passage extending from the compressor to the combustion chamber to improve stability of a flame and combustibility in the combustion chamber during the plant starting. The extraction pipes extend to and hence lead the extracted air into a portion of the exhaust gas passage located downstream of the denitration device.
摘要:
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. The flow-uniformalizing tube imparts a greater flow resistance to air flow from the back side of the tail tube than to the air flow from the side thereof diametrically remote from the back side, so that the flow velocity of the air flowing through the air passage is substantially uniformalized in the circumferential direction of the inner tube.
摘要:
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. The air bleed valve is controlled in such a manner that the opening degree thereof is maximized when the fuel supply to the secondary fuel nozzles is commenced and is progressively decreased in accordance with the increase of the load such as to become substantially zero when the load has been increased to the normal load range.
摘要:
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.