Kabushiki Kaisha Toshiba

Toshiba Energy Systems & Solutions Corporation

Iwataro Sato

Kazutaka Tsuruta

Hideyuki Maeda

Nobuhiro Okizono

Asako Inomata

Akihiro Onoda

Satoru Sekine

Naoyuki Okamura

Kunihiko Wada

Shoko Ito

Tomohiko Tsukuda

Daizo Saito

Satoru Kuboya

Yuki Mimura

Takeo Takahashi

Shogo Iwai

Takeo Suga

Yasunori Iwai

Masao Itoh

Kazutaka Ikeda

Tsuguhisa Tashima

Yuichi Morisawa

Masataka Tamura

Naoki Shibukawa

Toshio Hirano

Shinji Tanigawa

A stator blade of an embodiment includes: a blade effective part having hollow portions; an outer shroud having an outer plate flange portion provided on a radial-direction outer side of the blade effective part, and a pair of outer mounting portions provided in a circumferential direction on a front edge side and a rear edge side; an inner shroud having an inner plate flange portion provided on a radial-direction inner side of the blade effective part; cooling medium introduction passages which introduce a cooling medium via opening portions formed in the outer plate flange portion and passing through the outer plate flange portion in a radial direction, to the hollow portions; and a cooling medium introduction passage formed in a direction along a surface of the outer plate flange portion in a wall thickness of the outer plate flange portion, which introduces a cooling medium to the hollow portion.

Turbine stator blade

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

A turbine rotor blade comprises: a blade effective part; a snubber disposed on radially outer side of the blade effective part; a platform disposed on radially inner side of the blade effective part; and an implanted part disposed on radially inner side of the platform. A first flow path is formed inside the implanted part for a cooling medium to pass through. A second flow path is formed inside the platform for the cooling medium having passed through the first flow to pass through. A blade effective part flow path is formed inside the blade effective part for the cooling medium having passed through the second flow path to pass through. A snubber flow path is formed inside the snubber for the cooling medium having passed through the blade effective part flow paths to pass through.

Turbine rotor blade and turbine

An ignition device of an embodiment is provided to a gas turbine combustor to which supercritical-pressure COis introduced. The ignition device includes: a shutoff valve provided on an outer side face of a casing of the combustor to make the inside of the casing and the outside of the casing communicate with each other or shut off from each other; an ignition rod formed of a long rod including a spark discharge portion at a leading end, and capable of advancing to and retreating from the inside of a combustor liner provided in the casing from/to the outside of the casing through the shutoff valve; and a driving part which makes the ignition rod advance and retreat.

Ignition device and gas turbine combustor

According to an embodiment, a turbine comprises: a cylindrical casing; and turbine stator blades arranged in the casing along a circumferential direction. The turbine stator blades each includes: a blade effective part; a coolant flow path through which a coolant flows in the blade effective part to cool the blade effective part; an outer ring sidewall provided on an outer periphery of the blade effective part; an inner ring sidewall provided on an inner periphery of the blade effective part; and a contact part provided at an end part of the inner ring sidewall with at least part thereof being along a flow direction of a working fluid, coming into contact with the inner ring sidewall of the adjacent blade during operation, and separating from the inner ring sidewall of the adjacent blade when the operation is stopped.

Turbine and turbine stator blade

A turbineincludes: a turbine rotor having a rotor main body including a hollow part into which a cooling fluid flows, and a plurality of rotor wheels arranged in an axial direction of the rotor main body and protruding from the rotor main body. A cooling-fluid introducing passage extending from the hollow part in a direction intersecting with the axial direction of the rotor main body is formed in the rotor main body so as to allow the cooling fluid in the hollow part to flow through the cooling-fluid introducing passage and then to flow around the rotor wheel to be conducted to the working-fluid flow passage. A flow-rate control plug regulating a flow rate of the cooling fluid flowing through the cooling-fluid introducing passage is disposed in the cooling-fluid introducing passage.

Turbine

A sealing device for a turbine has a sealing member provided in a gap between a rotor and a stator arranged to surround the rotor, and a fluid path provided within the stator, to introduce, into the stator, a cooling medium used to cool stationary blades extending radially inward from the stator, and to flow the cooling medium at least to an upstream side of the sealing member.

Seal apparatus of turbine and thermal power system

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

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.

According to an embodiment, at least one first outer ring has an annular outer ring cavity to which external cooling steam is supplied. A radial direction cooling hole connecting with the outer ring cavity is formed in the stator blades connected to the first outer ring. An annular inner ring cavity connecting with the radial direction cooling hole is formed in a first inner ring constituting one diaphragm together with the first outer ring. Cooling steam blowing holes connecting an annular wheel space and the inner ring cavity are formed. The annular wheel space is formed between the first inner ring and a rotor wheel adjacent to the first inner ring.

Steam turbine

An axial-flow turbine has turbine nozzles, a heat shield plate, a first communication hole formed in the turbine rotor and connected to the space, to flow a cooling medium, a first opening formed in at least any one of the two adjacent rotor disks, to be connected to the space, a second communication hole connected to the space through the first opening, to communicate with an implant unit of the turbine rotor blade in the rotor disk, a third communication hole connected to the second communication hole, to communicate along an effective length of the turbine rotor blade, a second opening formed in a side face of the turbine rotor blade, to be connected to the third communication hole, and a third opening formed in an outer circumferential end face of the turbine rotor blade, to be connected to the third communication hole.

Axial turbine and power plant

A hydrogen-combustion gas turbine plant includes a first system for using inert gas as a working fluid, and a second system for using steam as a working fluid. The first system includes a compressor on a turbine shaft, a first heat exchanger, and a second heat exchanger. The first heat exchanger heats gas compressed by the compressor and supplies the compressed gas to a high pressure intake of a second turbine. The second heat exchanger cools gas exhausted from the second turbine and supplies the cooled gas to a low pressure intake of the compressor. The second system includes the first heat exchanger and the second heat exchanger. The first heat exchanger uses heat generated by combustion of a gas mixture including hydrogen and oxygen to heat the inert gas, and supplies steam resulting from the combustion to a high pressure intake of a first turbine. The second heat exchanger uses heat from the inert gas of the first system to heat steam exhausted from a low temperature outlet of the first turbine, and passes the heated steam to a third turbine.

Growing community of inventors

Hiratsuka, Japan

Iwataro Sato