Abstract: A combustor includes a fueling nozzle that jets a fuel towards a combustion chamber located downstream and a flat-plate-shaped air blowhole plate that faces the upstream side of the combustion chamber and that is disposed between the fueling nozzle and the combustion chamber. The air blowhole plate has a plurality of air blowholes arranged at equal intervals in a circumferential direction relative to the center of the air blowhole plate, in order to jet a flow of fuel and a flow of air that is formed at the outer circumferential side of the fuel flow toward the combustion chamber.

Abstract: An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen.

Abstract: An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. A combustor includes a fuel nozzle for jetting out a fuel into a combustion chamber formed at a downstream side; an air hole plate of a flat-plate shape disposed between the fuel nozzle and the chamber, the air hole plate facing an upstream side of the chamber; and a plurality of air holes provided in the air hole plate, in a circumferential direction relative to a central axis of the air hole plate, such that a fuel flow and an air flow formed at an outer circumferential side of the fuel flow are blown out into the chamber from the respective air holes; wherein a clearance defined between any two circumferentially adjacent air hole inlets provided on a face of the air hole plate that is nearer to the fuel nozzle is wider than a clearance defined between any two circumferentially adjacent air hole outlets formed on a face of the air hole plate that is nearer to the chamber.

Abstract: A combustor for a gas turbine capable of performing stable combustion even by using high temperature air, comprising a first burner (5) jetting fuel and air into a combustion chamber (2) and a second burner (8) causing the circulating jet of the fuel and air installed at a position corresponding to the tip part of a flame caused by the first burner (5).

Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.

Abstract: A combustor is provided that can ensure combustion stability even when operated on low BTU gas without needing any equipment for preventing back-flow of fuel gas during operation on pilot fuel. The combustor includes a first perforated plate disposed upstream of a combustion chamber, the first plate having a plurality of nozzle holes and air holes; a second perforated plate disposed on the upstream side of the first plate; and a plurality of gas nozzles each of which is inserted into corresponding nozzle holes. The gas nozzle has a leading end located inside the corresponding one of the nozzle holes. Each of the gas nozzles includes a jet hole portion having a diameter smaller than that of a gas jet hole of the gas nozzle; and a passage portion designed to form an air passage on the outer circumference of the leading end portion of the gas nozzle.

Abstract: A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. A combustor 2 according to the present invention includes a combustion chamber 5 to which fuel and air are supplied; air holes 32 adapted to supply air to the combustion chamber 5; fuel nozzles 25 adapted to supply gaseous fuel to the air holes 32; and orifices 24 adapted to allow the gaseous fuel supplied to the air holes 32 to cause a pressure drop.

Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.

Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.

Abstract: A gas turbine combustor includes plural multi-coaxial-injection-hole burners in which plural fuel nozzles and plural air holes provided in an air plate to correspond to the respective fuel nozzles are coaxially arranged. Each of the multi-coaxial-injection-hole burners includes a first coaxial injection burner disposed on an inner circumferential side, and a second coaxial injection burner disposed on an outer circumferential side, and a diameter of the air holes of the first coaxial injection burner is smaller than a diameter of the air holes of the second coaxial injection burner. Combustion for carrying out flame holding of a gas turbine combustor is performed by the first coaxial injection burner, and low NOx combustion of the gas turbine combustor is performed by the second coaxial injection burner.

Abstract: An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen.

Abstract: This invention is directed to supply a combustor having a structure that reduces NOx emissions while maintaining combustion stability. The combustor has a chamber into which fuel and air are supplied. An air hole plate having a plurality of air holes upstream of the chamber is also disclosed, and fuel nozzles supplying fuel to the air holes of the air hole plate are further disclosed. In the combustor, a center of a chamber-side of the air hole plate is closer to the chamber than exits of outermost peripheral air holes.

Abstract: This invention is intended to maintain combustor reliability.

Abstract: Provided is a gas turbine power plant in which a rotor of a generator is journalled by water lubrication bearings into which a part of cooling water for cooling the generator is fed. Since the lubrication water has a viscosity lower than that of lubrication oil, it is possible to provide a gas turbine power plant with less energy loss resulting in lower power consumption for accessories, and in high power generation efficiency.

Abstract: An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. A combustor includes a fuel nozzle for jetting out a fuel into a combustion chamber formed at a downstream side; an air hole plate of a flat-plate shape disposed between the fuel nozzle and the chamber, the air hole plate facing an upstream side of the chamber; and a plurality of air holes provided in the air hole plate, in a circumferential direction relative to a central axis of the air hole plate, such that a fuel flow and an air flow formed at an outer circumferential side of the fuel flow are blown out into the chamber from the respective air holes; wherein a clearance defined between any two circumferentially adjacent air hole inlets provided on a face of the air hole plate that is nearer to the fuel nozzle is wider than a clearance defined between any two circumferentially adjacent air hole outlets formed on a face of the air hole plate that is nearer to the chamber.

Abstract: An object of this invention is to accelerate further mixing of a fuel and air independently of a flow rate of the fuel. A gas turbine combustor comprises: a fuel nozzle for blowing out a gas fuel; an air nozzle plate with an air nozzle for jetting out the fuel and air into a combustion chamber after the blowout of the fuel from the fuel nozzle; and an obstacle formed inside the air nozzle; wherein the obstacle causes a collision of the fuel jet blown out from the fuel nozzle, and hence causes turbulence in an airflow streaming into the air nozzle. According to the invention, mixing between the fuel and the air can be further accelerated independently of the flow rate of the fuel.

Abstract: A turbine nozzle (2) that, among components constructing a turbine, reaches particularly high temperature is efficiently cooled with a relatively simple structure. A double casing structure in which a turbine casing (7) is provided outside a turbine shell (5) is formed. The turbine casing (7) functions as a flow path (24) for compressed air (20?21) before combustion. The turbine shell (5) covers a turbine nozzle (2) and a radial turbine impeller (3) and forms flow paths (15, 16) for combustion gas (10?11?12?13). The compressed air (21) before combustion flowing in the flow path (24), for compressed air, having air-tightness between itself and the outside air is blown to the turbine nozzle (2) through a through-hole (51) penetrating both wall surfaces of the turbine shell (5) so that the turbine nozzle (2) is evenly cooled and the compressed air used to cool the turbine nozzle is made to flow toward the turbine impeller (3).

Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.

Abstract: Provided is a gas turbine power plant in which a rotor of a generator is journalled by water lubrication bearings into which a part of cooling water for cooling the generator is fed. Since the lubrication water has a viscosity lower than that of lubrication oil, it is possible to provide a gas turbine power plant with less energy loss resulting in lower power consumption for accessories, and in high power generation efficiency.

Abstract: A micro gas turbine system is provided which increases power generation efficiency and output of power generation by means of water spray and which can exercise effective water spray control with simple control. The micro gas turbine system, according to the present invention, including a compressor, a combustor, a regenerative heat exchanger, a generator and a power transducer is provided with a plurality of spray water supply lines which include spray water nozzles and shutoff valves and which supply a prescribed amount of spray water by opening and closing the shutoff valves.