Doosan Enerbility Co., Ltd.

Other

Doosan Heavy Industries & Construction Co., Ltd

Borys Shershnyov

Alexander Myatlev

Yunyoung Doh

Mu Hwan Chon

Jungmin Seok

Alexander Bograd

Muhwan Chon

Hanjin Jeong

A combustor nozzle, a combustor including the combustor nozzle, and a gas turbine including the combustor. The combustor nozzle may include a plurality of mixing tubes through which air and fuel flow, a multi-tube into which the mixing tubes are inserted, the multi-tube supporting the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, a front plate spaced apart from the tip plate, the front plate forming a cooling space, and a dispersion plate spaced apart from the front plate and connected to the fuel tube, the dispersion plate forming a dispersion space in which fuel discharged from the fuel tube is diffused.

Combustor nozzle, combustor, and gas turbine including same

A combustor nozzle, a combustor, and a gas turbine including the same are provided. The combustor nozzle includes a nozzle module. The nozzle module includes a central tube having an air flow path, through which air flows from a front-to-rear direction, and an opening hole at a rear end thereof, a shroud into which at least a part of the central tube is inserted, and having an air inlet at a front end thereof, wherein a mixing flow path is formed between the shroud and the central tube so that the air and injected fuel flow therethrough, and a plurality of cooling channels, each of the plurality of cooling channels extending rearward from an inlet communicating with the air flow path to an outlet communicating with the mixing flow path while passing through a sidewall portion of the central tube.

Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen, which includes a plurality of mixing tubes through which air and fuel flow, a multi-tube configured to contain and support the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, and a front plate spaced apart from the tip plate to define a cooling space.

Combustor nozzle, combustor, and gas turbine including the same

A combustor nozzle capable of injecting fuel uniformly, and a combustor and gas turbine including the same are provided. The combustor nozzle includes a main cylinder having a fuel passage through which fuel flows, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel, wherein the fuel injection module includes a plurality of first struts protruding from the main cylinder and having strut injection holes to inject fuel, a first support tube coupled to outer ends of the first struts, and a plurality of second struts protruding from the first support tube and having strut injection holes to inject fuel, and each of the first and second struts includes a swirl guide inclined with respect to a longitudinal direction of the main cylinder.

Combustor nozzle, and combustor and gas turbine including the same

A combustor nozzle, a combustor, and a gas turbine including the same are proposed. The combustor nozzle includes a nozzle module. The nozzle module includes a fuel supply pipe supplying fuel from the front side to the rear side, a fuel plenum having an internal fuel flow path through which the fuel flows and communicating with the fuel supply pipe, an air inlet formed in front of the fuel plenum, a plurality of tubes disposed through a rear side of the fuel plenum, wherein a front end of each tube communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side of each tube, and a swirler provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes to swirl fluid, with a central portion thereof opened when viewed from the axial direction of the tube.

A combustor nozzle and a combustor for a gas turbine including the same are provided. The combustor nozzle may include a plurality of vanes disposed radially on an outer circumferential surface thereof, each vane including an internal cavity to which fuel is supplied, wherein the vane may include an airfoil in cross-section, wherein at least one of a pressure surface and/or a suction surface of the airfoil is disposed in a height direction thereof with a plurality of nozzle holes communicating with the cavity, wherein the vane may include a V-shaped nozzle hole including a pair of outlets on both sides of the airfoil based on a leading edge of the airfoil, wherein the V-shaped nozzle hole may form an angle (&#x3b1;) diverging outward with respect to a horizontal plane across the leading edge, and an acute angle (&#x3b2;) radially outward with respect to a vertical plane perpendicular to the horizontal plane.

Combustor nozzle enhancing spatial uniformity of pre-mixture and gas turbine having same

A combustor nozzle capable of injecting fuel uniformly, a combustor including the combustor nozzle, and a gas turbine including the combustor are provided. The combustor nozzle includes a premix passage in which air and fuel are mixed, wherein the premix passage includes a plurality of pegs configured to inject fuel and guide an air flow and a plurality of mixing bars configured to mix air and fuel injected from the plurality of pegs, the mixing bar having a twisted structure.

A combustor and a gas turbine including the same which can reduce a loss of pressure and enhance a cooling efficiency of a liner and transition piece are provided. The combustor may include a liner configured to define a combustion chamber, a transition piece coupled to a rear end of the liner, a flow sleeve configured to surround the liner and the transition piece, a plurality of impingement holes formed in the flow sleeve, and a plurality of inserts inserted into at least some of the impingement holes, wherein each of the inserts may include a first channel configured to guide combustion air, introduced into an associated one of the impingement holes, in a direction parallel to a direction of extension of an annular passage between the flow sleeve and the liner or an annular passage between the flow sleeve and the transition piece, and a second channel configured to guide the combustion air, introduced into the associated one of the impingement holes, in a direction transverse to the annular passage between the flow sleeve and the liner or the annular passage between the flow sleeve and the transition piece.

Combustor and gas turbine including the same

A liner cooling structure of a duct assembly reduces pressure loss generated in the compressed air flow for cooling the liner. The duct assembly includes a liner, a transition piece, and a flow sleeve, and the transition piece and the flow sleeve form a transition piece channel through which a main stream of compressed air is introduced to the duct assembly. The liner cooling structure includes a first flow passage through which the main stream of compressed air passes in a first direction; and a second flow passage formed as a plurality of inlet holes in the flow sleeve to communicate with the first flow passage and configured to pass an auxiliary stream of compressed air in a second direction from outside the flow sleeve to inside the flow sleeve, the auxiliary stream joining the main stream such that the second direction forms an acute angle with the first direction.

Liner cooling structure with reduced pressure losses and gas turbine combustor having same

A nozzle, a combustor, and a gas turbine are capable of efficiently atomizing fuel. The nozzle includes an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

Nozzle for combustors, combustor, and gas turbine including the same

The gas turbine includes a compressor to compress air introduced thereinto, a combustor to mix the compressed air with fuel for combustion, a main turbine having a plurality of turbine blades rotated by an energy produced by combustion gas in the combustor, a heat recovery boiler to produce steam by heat exchange with the combustion gas, and a fluid accelerator supplied with a first fluid compressed in the compressor to compress the first fluid and supply the compressed first fluid to the combustor, where the fluid accelerator includes a first inlet through which the first fluid is introduced, a second inlet through which a second fluid having a higher pressure than the first fluid is introduced, and an outlet through which the first and second fluids are mixed and discharged.

Gas turbine and method of operating the same

Disclosed herein are a nozzle capable of efficiently atomizing fuel, a combustor, and a gas turbine. The nozzle for the combustor includes a tube assembly including an air passage through which air moves, a main fuel passage disposed inside the air passage so that main fuel moves through the main fuel passage, and a pilot fuel passage disposed inside the main fuel passage so that pilot fuel moves through the pilot fuel passage as well as a nozzle tip configured to eject the pilot fuel and the main fuel, where the nozzle tip includes an injection passage coupled with the pilot fuel passage and a plurality of centrifugal flow chambers disposed outside the injection passage and communicating with the main fuel passage.

Nozzle for combustors and gas turbine including the same

Disclosed are a pilot fuel injector, and a fuel nozzle and a gas turbine having the same. The pilot fuel injector is mounted on the fuel nozzle to uniformize the flow of the introduced air and to enable uniform mixing with the fuel, so that a fuel mixed air having a high mixing rate is provided to the combustion chamber. The mixing rate of the fuel mixed air directed to the combustion chamber is increased, thereby suppressing the generation of nitrogen oxides and preventing the flame stagnation.

Pilot fuel injector, and fuel nozzle and gas turbine having same

A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

Growing community of inventors

Changwon-si, South Korea

Borys Shershnyov