Kabushiki Kaisha Toshiba

Toshiba Energy Systems & Solutions Corporation

Akihiro Onoda

Daisuke Nomura

Hiroshi Kawakami

Kenichi Imai

Iwataro Sato

Kazutaka Tsuruta

Naoki Shibukawa

Tomohiko Tsukuda

Sakae Kawasaki

Yuki Mimura

Kentaro Tani

Yasunori Iwai

Tomohiro Tejima

Asako Inomata

Shoko Ito

Toshio Hirano

Shinichiro Ohashi

Junichi Tominaga

Osamu Furuya

Nobuhiro Okizono

Hiroyuki Kawagishi

Yoriharu Murata

Naoyuki Okamura

A steam turbineof an embodiment includes a turbine rotor, rotor blade cascadeshaving rotor blades, stationary blade cascadeshaving stationary blades, and a steam passageformed on a turbine stage, among turbine stages, including the rotor blades each having a blade height equal to or more than a blade height at which a loss generated when a leakage steam flown between a diaphragm inner ringand the turbine rotorjets into a main steam and a benefit brought by increasing the blade height of each of the rotor bladesin accordance with an increase in a flow rate of the main steam by an amount of the leakage steam are cancelled, and leading the leakage steam from an upstream side to a downstream side of a rotor disk

Steam 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

An axial-flow turbine according to an embodiment includes a plurality of nozzle structures and a plurality of blade structures. At least one nozzle structure includes an outer ring diaphragm and an inner ring diaphragm. The outer ring diaphragm and the inner ring diaphragm form an annular opening portion which extends in a circumferential direction therebetween. A nozzle is provided in a portion of a region of the annular opening portion in the circumferential direction, and a closing part is provided in another portion of the region of the annular opening portion in the circumferential direction. The closing part closes this other portion of the region to prevent a working fluid from flowing into this other portion of the region. A closing part medium passage is provided in the closing part and is configured to flow a cooling medium which cools the closing part.

Axial-flow turbine and power plant including the same

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

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 turbine rotor assemblycomprises a turbine rotor and a plurality of moving bladesimplanted in a circumferential direction of the rotor. A flow passage is formed between each of the moving bladesand a circumferentially adjacent moving blade. Each of the moving bladescomprises a suction side connecting memberprotruded on a blade suction surfaceand a pressure side connecting memberprotruded on a blade pressure surface, wherein the suction side connecting memberof each of the moving bladesis configured to be connected with the pressure side connecting memberof the circumferentially adjacent moving bladeto form an intermediate connecting memberbetween the moving bladeand the circumferentially adjacent moving bladeduring a rotation of the turbine rotor. A downstream side end edgeof the intermediate connecting memberis positioned at an upstream side of a throat S of the flow passage.

Turbine rotor assembly and steam turbine

In one embodiment, a calculation method of moisture loss in a steam turbine calculates first a wetness fraction at the inlet and outlet of each of stationary blade cascades and rotor blade cascades. Subsequently, the moisture loss is classified into (1) supersaturation loss, (2) condensation loss, (3) acceleration loss, (4) braking loss, (5) capture loss and (6) pumping loss, and a loss for calculation of the moisture loss is selected from the above losses (1) to (6) according to the wetness fraction of steam at the inlet and outlet of each blade cascade. An amount of each selected loss is calculated, and an amount of moisture loss at each blade cascade is calculated.

Calculation method of moisture loss in steam turbine

An axial flow turbine stage structure has: an annular diaphragm inner ring; an annular diaphragm outer ring arranged radially outside and coaxially with the diaphragm inner ring and separated from the diaphragm inner ring by an annular flow path interposed between them; stationary blades arranged peripherally at intervals in the annular flow path and rigidly secured to the diaphragm inner ring and the diaphragm outer ring; and moving blades rigidly secured to the outer periphery of a rotatable rotor and arranged peripherally at intervals respectively at axially downstream sides of the stationary blades. Through holes are formed in the diaphragm outer ring so as to allow axial upstream side and axially downstream side of the stationary blades to communicate with each other.

Axial flow turbine and stage structure thereof

An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.

Axial flow turbine

A gas-turbine dual-fuel injector is operated on liquid fuel at start-up and on gaseous fuel from a gasifier during steady state. During load transients, the operation is switched back to liquid fuel, however a small amount of gaseous fuel continues to be injected as well.

Methods of operation a dual-fuel injector for a gas turbine with simultaneous liquid and gaseous fuels injection during transients

A coal gasification combined cycle power generation plant generally includes a gas turbine system, a fuel supply system, an air supply system and an exhaust gas system, which are operatively connected to each other. The gas turbine system includes a combustor for selectively burning a coal gasification fuel obtained by gasifying a coal and a liquid fuel atomized by an atomization air and a gas turbine to which a combustion gas generated in the combustor is supplied. The fuel supply system is provided with a liquid fuel supply passage for the combustor through a fuel nozzle provided for the combustor, an atomization air supply passage for the combustor through the fuel nozzle and a coal gasification fuel supply passage for the combustor through the fuel nozzle, all of these supply passages being arranged so as to be adjacent to each other. The atomization air supply passage is provided with an outlet portion to which a branching outlet port for injecting the atomization air toward an outlet portion of the coal gasification supply passage is formed so as to secure a minimum flow rate for preventing the coal gasification fuel from conversely flowing into the fuel nozzle.

Growing community of inventors

Yokohama, Japan

Akihiro Onoda