Doosan Enerbility Co., Ltd.

Other

Doosan Heavy Industries & Construction Co., Ltd

Ho Keun Kim

Young Jun Shin

Dong Sik Han

Afzal Pasha Mohammed

Young Gun Go

Ho Jin Kim

Eun Seong Cho

Griffin C Beck

Brian Connolly

Joong Hyun Lim

Chea Hong Choi

Prabhat Jha

Sung Hyun Kim

Jose Grana-otero

Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen. The nozzle includes a cylindrical tube through which air and fuel flow, and the cylindrical tube has an inlet formed at a longitudinal end thereof for introduction of a first fluid (e.g., compressed air) into the cylindrical tube. The cylindrical tube has one or more supply ports formed on a circumferential surface of the cylindrical tube for introduction of a second fluid (e.g., fuel such as hydrogen) into the cylindrical tube. The cylindrical tube has at least one fuel/air separator disposed interior of the longitudinal end, the fuel/air separator operative to cause a flow of the second fluid to be sandwiched between two flows of the first fluid before the first and second fluids subsequently mix inside the cylindrical tube. The nozzle may be included in a combustor of a gas turbine engine.

Combustor nozzle, combustor and gas turbine including same

A combustor nozzle includes a plurality of mixing tubes through which air and fuel flow, a plurality of accommodation tubes each accommodating and supporting the plurality of mixing tubes therein, a first fuel tube coupled to each accommodation tube to supply a first fuel into the accommodation tube, a second fuel tube coupled to each accommodation tube to supply a second fuel into the accommodation tube, and a fuel supply member supplying the first fuel accommodated in the accommodation tube into each mixing tube, wherein the accommodation tube has a fuel container combined with the second fuel tube to contain the second fuel therein, and an auxiliary injection member is disposed on the fuel container to inject the second fuel from the accommodation tube.

Combustor nozzle, combustor, and gas turbine including same

Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen. The nozzle comprised of a cylindrical tube is configured for introduction of a first fluid (for example, compressed air) and a second fluid (for example, hydrogen or a fuel containing hydrogen). Along an inner surface of the nozzle, one or more fluid vortex generators are disposed. As compressed air flows over the one or more fluid vortex generators, the compressed air swirls inside the nozzle resulting in a turbulent flow of the compressed air. As fuel is then introduced into the nozzle, the fuel encounters the swirling or turbulent flow of compressed air, and the introduced fuel is thoroughly mixed with the compressed air so that the fuel/air mixture will be combusted in a uniform manner. The nozzle may be included in a combustor of a gas turbine engine.

A combustor nozzle using fuel containing hydrogen, a combustor and gas turbine including the same are provided. The nozzle for a combustor configured to burn fuel containing hydrogen includes a fuel supply duct including a plurality of injection tubes through which air and fuel flow and a fuel passage through which fuel flows, a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide air outside the injection tube to be introduced thereinto for swirling, and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow fuel to flow through the fuel passage to the injection tube.

Combustor nozzle, combustor, and gas turbine including the same

A combustion apparatus can avoid instability in combustion by controlling a pressure ratio of fuel mixed with air. The combustion apparatus includes a casing; a pilot nozzle disposed at the center of the casing and supplied with fuel by a pilot fuel supply pipe; and a plurality of main nozzles arranged around the pilot nozzle and supplied with fuel by a main fuel supply pipe, each main nozzle including a pair of parallel fuel channels each extending to a respective fuel spray position within the main nozzle. A gas turbine adopting the combustion apparatus includes a plurality of combustors, each combustor including the casing, pilot nozzle, and plurality of main nozzles, with each main nozzle having first and second fuel channels respectively extending to a fuel spray position of the corresponding fuel channel. A pilot manifold connects the respective pilot nozzles, and a main manifold connects the respective main nozzles.

Combustion apparatus and gas turbine including the same

Disclosed therein is a reinforced leather. The reinforced leather includes: a leather sheet layer made of a leather-like material; a bonded layer positioned on an upper face of the leather sheet layer; a textile layer positioned on an upper face of the bonded layer and made of cotton fabrics; and a coated layer positioned on an upper face of the textile layer. The reinforced leather can remedy the shortcoming that leather-like materials produced from waste resources get torn easily, be used as leather for shoes due to its high tensile strength and shear strength, and provide a beautiful appearance.

Growing community of inventors

Daejeon, South Korea

Ho Keun Kim