Kabushiki Kaisha Toshiba

8 Rivers Capital, LLC

Toshiba Energy Systems & Solutions Corporation

Nobuhiro Okizono

Hideyuki Maeda

Iwataro Sato

Kazutaka Tsuruta

Naoyuki Okamura

Rodney John Allam

Jeremy Eron Fetvedt

Kunihiko Wada

Yasunori Iwai

Masao Itoh

Daizo Saito

Satoru Kuboya

Takeo Takahashi

Shogo Iwai

Tsuguhisa Tashima

Akihiro Onoda

Masataka Tamura

A thermal insulation coating member includes: a substrate having a surface; a binding layer on the surface, and a thermal insulation layer on the binding layer. The thermal insulation layer includes: a first ceramic layer including a plurality of first flat pores, the plurality of first flat pores being inclined at a first angle with respect to the surface and extending in a first direction; and a second ceramic layer including a plurality of second flat pores, the plurality of second flat pores being inclined at a second angle with respect to the surface and extending in a second direction. The second angle differs from the first angle, the second direction differing from the first direction, or the second angle and the second direction respectively differing from the first angle and the first direction.

Thermal insulation coating member, axial flow turbine, and method for producing thermal insulation coating member

The gas turbine facilityof the embodiment includes a combustorcombusting fuel and oxidant, a turbinerotated by combustion gas, a heat exchangercooling the combustion gas, a heat exchangerremoving water vapor from the combustion gas which passed through the heat exchangerto regenerate dry working gas, and a compressorcompressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facilityincludes a pipeguiding a part of the dry working gas from the compressorto the combustorvia the heat exchanger, a pipeexhausting a part of the dry working gas to the outside, and a pipeintroducing a remaining part of the dry working gas exhausted from the compressorinto a pipecoupling an outlet of the turbineand an inlet of the heat exchanger

Gas turbine facility with supercritical fluid 'CO2' recirculation

A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other.

Turbine, manufacturing method thereof, and power generating system

Gas turbine facility

A single-flow turbine using COas a working fluid. The turbine includes a balance piston portion configured to optimize an axial load of a rotor on a bearing with a fluid having a temperature lower than a temperature of the working fluid introduced into the turbine, wherein a flow path in which at least a part of the fluid passing through the balance piston portion is extracted from a middle part of the passing, and in which at least a part of the extracted fluid is urged to flow to a middle part of a passage where the working fluid passes and where rotor blades at a plurality of stages are provided, is formed at the turbine.

Axially balancing a turbine using low temperature exhaust

In one embodiment, a turbine using COincludes moving blades, stator blades, a working fluid transport flow path, a coolant transport flow path, and a coolant recovery flow path. The stator blades constitute turbine stages together with the moving blades. The working fluid transport flow path is configured to transport the working fluid sequentially to the turbine stages. The coolant transport flow path is configured to transport the coolant by allowing the coolant to sequentially pass through the inside of the stator blades from an upstream to a downstream of the working fluid. The coolant recovery flow path is configured to recover the coolant passing through the inside of the stator blade at a predetermined turbine stage and merge the recovered coolant with the working fluid transport flow path at a turbine stage on an upstream side of the predetermined turbine stage.

Turbine

Growing community of inventors

Yokohama, Japan

Nobuhiro Okizono