Doosan Enerbility Co., Ltd.

Other

Doosan Enerbnity Co., Ltd.

Vincent Galoul

Simon Hauswirth

Richard Jones

Wade Beaumont

Yunchang Jang

Impingement insert for an airfoil of a blade/vane of a gas turbine is provided. The impingement insert includes a double-walled section having an outer and an inner walls, that define&#x2014;an inner channel at an inner surface of the inner wall, an outer channel at an outer surface of the outer wall and a middle channel between the outer and the inner walls. Impingement cooling holes are provided in the outer wall that use the cooling air of the middle channel to eject impingement jets into the outer channel. The impingement insert includes at least one extraction duct that extends between the outer and the inner walls across the middle channel, and has an inlet at the outer channel, and an outlet at the inner channel, for flowing the cooling air, after impingement, from the outer channel into the inner channel.

Insert for re-using impingement air in an airfoil, airfoil comprising an impingement insert, turbomachine component and a gas turbine having the same

An impingement insert for an airfoil of a turbomachine component is provided. The insert includes first and second body parts, each having inner and outer surfaces; and first and second contact parts provided on the outer surfaces of the first and the second body parts. The insert includes a flexible mechanical seal part between the body parts. A flow channel for cooling air is defined by the seal part and the inner surfaces of the body parts. One or both of the body parts include impingement holes. The insert has an elastic part connected to the body parts. When the elastic part is subjected to deformation, the elastic part is configured to apply a force, on the first and/or the second body parts, in a direction of increasing a separation between the first contact part and the second contact part.

Impingement insert for a turbomachine component, turbomachine component and gas turbine having the same

A turbine vane is provided. The turbine vane may include an inner shroud having an upper surface and a lower surface, a seal unit disposed in the lower surface of the inner shroud and defining a first region and a second region in the lower surface of the inner shroud, a first impingement unit arranged in the first region and comprising a first impingement plate facing the inner shroud defining a first impingement chamber therebetween, wherein the first impingement plate is configured to receive cooling air and form impingement jet directed to the first impingement chamber, a second impingement unit arranged in the second region and comprising a second impingement plate facing the inner shroud defining a second impingement chamber therebetween, and at least one connector flow channel configured to direct cooling air from the first impingement chamber to the second region, wherein the second impingement plate is configured to receive cooling air from the at least one connector flow channel and form impingement jet directed to the second impingement chamber.

Technique for cooling inner shroud of a gas turbine vane

The present invention presents a ring assemblydisposed radially outwardly of an array of circumferentially arranged bladesof a gas turbine engine rotor R. The ring assemblyincludes ring segmentsdisposed circumferentially one adjacent to another and having a first circumferential endand a second circumferential endcircumferentially spaced apart from each other. The first endof a ring segmentand the second endof an adjacent ring segmentof the plurality of ring segmentsare arranged facing each other. An integrally formed projecting seal partis formed at the first end. An integrally formed receiving seal partis formed at the second endfacing the first end. The receiving seal partreceives the projecting seal partto form a mating connection between the ring segmentand the adjacent ring segment. A gas turbine engine including the ring assemblyis also provided. Furthermore, a method of manufacturing the ring segmentof the ring assemblyis also provided.

Gas turbine ring assembly comprising ring segments having integrated interconnecting seal

The present technique presents a turbomachine component having an airfoil e.g. a vane of a gas turbine. The airfoil wall defines an internal space which includes a first and a second cooling channels having a first and a second impingement inserts, that define a first main and a first peripheral flow channels in the first cooling channel and a second main and a second peripheral flow channels in the second cooling channel, respectively. Impingement jets ejected from the main flow channels via impingement holes of the corresponding impingement inserts are received in the corresponding peripheral flow channels. A channel connecting conduit conducts a flow of the cooling air from the first cooling channel to the second cooling channel. The channel connecting conduit includes an inlet connected to an outlet of the first cooling channel, and an outlet connected to an inlet of the second cooling channel.

Turbomachine component for a gas turbine, turbomachine assembly and gas turbine having the same

Impingement insert for an airfoil of a blade/vane of a gas turbine is provided. The impingement insert includes a triple-walled section having a central wall, an outer and an inner peripheral walls, that define&#x2014;a central channel at an inner surface of the central wall, an inner channel between the central wall and the inner peripheral wall, a middle channel between the inner peripheral wall and the outer peripheral wall, and an outer channel at an outer surface of the outer peripheral wall. Impingement cooling holes are provided in the outer peripheral wall that use the cooling air of the middle channel to eject impingement jets into the outer channel. The impingement insert includes at least one supply duct that fluidly connects the central channel to the middle channel for supplying the cooling air from the central channel to the middle channel, at least one extraction duct that extends between the outer and the inner peripheral walls across the middle channel, and has an inlet at the outer channel, and an outlet at the inner channel, for flowing the cooling air, after impingement, from the outer channel into the inner channel.

Triple-walled impingement insert for re-using impingement air in an airfoil, airfoil comprising the impingement insert, turbomachine component and a gas turbine having the same

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Baden, Switzerland

Vincent Galoul