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Doosan Enerbility Co., Ltd.

General Electric Corporation Gmbh

Andrey Sedlov

Yun Chang Jang

Thomas Kotteck

Vladimir Vassiliev

Igor Baibuzenko

A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.

Ring segment and gas turbine including the same

A ring segment, a turbine, and a gas turbine having improved cooling performance are provided. The ring segment may include a shielding wall mounted to a turbine casing which accommodates a turbine blade and configured to face an inner circumferential surface of the turbine casing, a first hook part and a second hook part configured to protrude from the shielding wall toward the turbine casing to be coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, a plurality of first cooling passages configured to connect the main cavity and first side surfaces facing each other of the shielding wall, a plurality of second cooling passages configured to extend in a direction crossing the first cooling passage and connect the main cavity and second side surfaces facing each other of the shielding wall, and a chamber configured to be connected to the first cooling passages.

Ring segment, and turbine and gas turbine including the same

A turbine vane improves cooling performance by guiding an impingement cooling fluid, introduced through a cooling hole of an inner sidewall provided inside the turbine vane, to flow while in contact with an inner surface of the turbine vane for a relatively long time. The turbine vane includes an outer sidewall configured to form an airfoil comprising a leading edge and a trailing edge; an inner sidewall disposed inside the outer sidewall to form a gap between the inner sidewall and an inner surface of the outer sidewall, the inner sidewall having a plurality of cooling holes communicating with the gap; and a plurality of spiral guides formed on the inner surface of the outer sidewall and disposed at positions facing the respective cooling holes, the plurality of spiral guides configured to guide a cooling fluid having passed through the cooling holes to impinge on the spiral guides.

Turbine vane, ring segment, and gas turbine including the same

A combustor includes a combustor shell, an inner liner disposed inside the combustor shell and having an inner surface defining a cavity configured to receive hot combustion gases from a combustion chamber of the combustor, and an outer surface, the combustor shell and the inner liner defining an annular flow channel therebetween, and a segment carrier operatively connected to the inner liner and operative to receive an upper portion of the inner liner, the segment carrier and the inner liner defining a purging cavity therebetween. The inner liner includes a plurality of impingement jet holes configured to direct a flow of cooling air from the annular flow channel to the purging cavity.

Growing community of inventors

Wurenlos, Switzerland

Andrey Sedlov