Doosan Enerbility Patente

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A wind turbine blade capable of being easily manufactured and improving structural strength, and a wind turbine including the same are provided. The wind turbine blade includes an outer skin defining an external appearance, an inner skin spaced apart from the outer skin, a plurality of spar caps positioned between the outer skin and the inner skin and spaced apart from each other in a thickness direction of the blade, and shear webs configured to connect the plurality of spar caps, wherein at least one of the plurality of spar caps has a structure in which a resin is impregnated with reinforcing fiber sheets, and the other spar caps each have a structure in which support plates including reinforcing fibers are stacked.

Disclosed herein is a nozzle(1400) for a combustor(1200) that burns fuel containing hydrogen, which includes a plurality of mixing tubes(1420) through which air and fuel flow, a multi-tube(1410) configured to contain and support the mixing tubes(1420), a fuel tube(1450) formed inside the multi-tube(1410) and through which fuel flows, a tip plate(1415) coupled to a tip of the multi-tube(1410), and a front plate(1460, 2460, 3460) spaced apart from the tip plate(1415) to define a cooling space(CS1).

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The present invention relates to a method for measuring vibration of an internal structure of a small-scaled reactor vessel model, the method comprising the steps of: arranging a detachable sensor fixing unit on the internal structure; installing a vibration measurement sensor that is coupled to the sensor fixing unit and measures the vibration of the internal structure; evaluating a level of the vibration of the internal structure by using the vibration measurement sensor; and disassembling the sensor fixing unit and the vibration measurement sensor after the evaluation.

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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.