Doosan Enerbility Patente

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A combustor (100) includes an outer can (110) into which fuel is introduced, an outer head (111) disposed on a front side of the outer can, an inner can (120) disposed inside of the outer can and having a combustion chamber (112) in which a fuel-air mixture is combusted, and an inner head (121) disposed to mix the fuel and the compressed air and supply the mixture into the inner can. The inner head includes a head plate (122) covering a front side of the inner can, and nozzle assemblies (123) disposed to mix the fuel and the compressed air and supply the mixture rearwards. The nozzle assembly includes a nozzle head (124) into which fuel is introduced and nozzles (130). The nozzles each is coupled between the nozzle head and the head plate to mix the fuel and the compressed air and supply the mixture rearwards. The nozzles each has a shape with a diameter decreasing and increasing toward the rear side thereof.

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An exhaust gas flow regulator and a heat recovery steam generator including the same are provided. The exhaust gas flow regulator includes a plurality of first tubes spaced apart from each other in a vertical direction, a support plate disposed in a direction perpendicular to the extension direction of the first tubes and through which the plurality of first tubes penetrates, and a second tube disposed at one or both ends of the support plate so as to be coupled to the support plate and extending parallel to the first tubes, wherein the second tube is provided with a guide plate disposed to redirect exhaust gases flowing adjacent to the second tube toward the first tube.

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A nozzle assembly, a combustor (100) using the same, and a gas turbine . The nozzle assembly is configured to inject fuel and compressed air into a combustion chamber of a combustor of a gas turbine, and includes a hollow nozzle frame (1410) , a mixture supply tube (1420) having a plurality of tubes (1421) configured to supply a mixture of air and fuel to the combustion chamber, a fuel supply part (1440) configured to supply fuel to the mixture supply tube, an air supply part (1440) configured to supply air to the mixture supply tube, and a mixing part (1450) including an injection member (1451) formed in each of the tubes and configured to inject fuel supplied from the fuel supply part toward air passing through the tube, and a swirl vane (1452) formed on one side of the injection member and configured to mix fuel and air passing through the injection member.

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An impingement cooling structure (300) is provided. The impingement cooling structure (300) includes a flow channel (330) formed between a first wall (310) and a second wall (320) facing the first wall (310), a plurality of impingement cooling holes (312) disposed in the first wall (310) such that the plurality of impingement cooling holes (312) are spaced apart from each other along the flow channel (330), and a flow diverter (322) convexly protruding from a surface of the second wall (320) in each space between injection axes (314) of the plurality of impingement cooling holes (312).

A micro-mixer (1400) comprises a plurality of fuel tubes (1410) through which air and fuel flow, a casing (1430) accommodating the plurality of fuel tubes (1410) therein, an injection part (1440) formed as a pyramidal protrusion on one side of the casing and connected to a front end of the fuel tube to inject the air and the fuel, and a fuel supply (1450, 1460) divided into a plurality of fuel supply parts to supply the fuel to the fuel tubes.

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A combustor nozzle (1220) comprising a nozzle module (1400) is proposed. The nozzle module (1400) comprises a fuel supply pipe (1420) supplying fuel from the front side to the rear side, a fuel plenum (1510) having an internal fuel flow path through which the fuel flows and communicating with the fuel supply pipe (1420), an air inlet (1511) formed in front of the fuel plenum (1510), a plurality of tubes (1520) disposed through a rear side of the fuel plenum (1510), wherein a front end of each tube (1520) communicates with the air inlet (1511), and a fuel port communicating with the fuel flow path is formed on a lateral side of each tube (1520), and a swirler (1530) provided with a plurality of swirling guides (1531) disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes (1520) to swirl fluid, with a central portion (1530a) thereof opened when viewed from the axial direction of the tube (1520).

A combustor nozzle (1220) comprises a plurality of nozzle modules (1400). The nozzle module (1400) comprises a fuel supply pipe (1410) having an internal fuel flow path through which fuel flows from the front side to the rear side, a plurality of manifolds (1430) communicating with the fuel supply pipe (1410) and arranged in a row in a radial direction so that air flow paths are respectively formed at positions therebetween, and a plurality of fuel mixers (1450) disposed along a circumferential direction at the rear side of the manifold (1430) to receive the fuel from the manifold (1430) and inject the fuel. Each of the plurality of fuel mixers (1450) comprises a mixer body (1451) having one end communicating with the manifold (1430), the other end that is opened, and a mixing flow path through which air and the fuel flow, an air inlet port (1470) formed on a lateral side of the mixer body (1451) so that the air is introduced upstream of the mixing flow path, a fuel port (1453) formed inside the mixer body (1451) and discharging the fuel supplied from the manifold to the mixing flow path, and an extension (1460) located at the other end of the mixer body (1451) and whose flow cross-sectional area increases as the extension (1460) extends downstream of the mixing flow path.

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A combustor nozzle (1120) is provided. The combustor nozzle (1120) comprises a nozzle module, the nozzle module (1400) comprises a central tube (1420) having an air flow path (1423), through which air flows from a front-to-rear direction, and an opening hole at a rear end thereof, a shroud (1430) into which at least a part of the central tube (1420) is inserted, and having an air inlet at a front end thereof, wherein a mixing flow path (1433) is formed between the shroud (1430) and the central tube (1420) so that the air and injected fuel flow therethrough, and a plurality of cooling channels (1450), each of the plurality of cooling channels (1450) extending rearward from an inlet communicating with the air flow path (1423) to an outlet communicating with the mixing flow path (1433) while passing through a sidewall portion of the central tube (1420).

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A turbine blade (1400, 2400, 3400) comprises an airfoil (1410, 2410, 3410) having a suction side (S1) and a pressure side (S2), a platform (1420) coupled to a bottom of the airfoil (1410, 2410, 3410), and a root (1425) coupled to a rotor disk (1310) by protruding downward from the platform (1420). The airfoil (1410, 2410, 3410) comprises a cooling passage (CP) formed therein and a discharge hole (1460, 2460, 3460) connected to an upper portion of the cooling passage (CP) to discharge cooling air. The discharge hole (1460, 2460, 3460) is inclined toward a tip of the turbine (1300, 1400) blade (1400, 2400, 3400) while extending from an inside to an outside thereof.

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