Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

National Institute for Materials Science

Mitsubishi Heavy Indsutries, Ltd.

Mitsubishi Power, Ltd.

Eiji Akita

Eisaku Ito

Yasuro Sakamoto

Yasuoki Tomita

Koichi Ishizaka

Masamitsu Kuwabara

Hiroki Fukuno

Susumu Wakazono

Kazuya Nishimura

Taiji Torigoe

Sunao Aoki

Kiyoshi Suenaga

Satoshi Tanimura

Kazuo Uematsu

Ikuo Okada

Hideyuki Uechi

Koichiro Iida

Junichiro Masada

Keizo Tsukagoshi

Takashi Hiyama

Yasuhiko Tsuru

Hitoshi Kitagawa

Yukinori Machida

Kentaro Akimoto

Hiroshi Harada

Satoshi Hada

Hideaki Sugishita

Shigemi Mandai

Hiroyuki Kimura

Kazutaka Mori

Tanehiro Shinohara

Satoshi Takiguchi

Masanori Yuri

Sosuke Nakamura

Koji Takahashi

Kei Inoue

Tsuyoshi Kitamura

Kazuharu Hirokawa

Shunsuke Torii

Masahiko Mega

Shuji Tanigawa

Toshiharu Kobayashi

Ichiro Nagano

Yukihiro Hashimoto

Yoshitaka Uemura

Yoshifumi Okajima

Yutaka Koizumi

Kouichi Akagi

Eigo Katou

Hiroyuki Otomo

Yutaka Ozawa

Tomohiro Ishida

Zenichi Yoshida

Masaki Taneike

Tadaharu Yokokawa

Hikaru Kurosaki

Atsushi Yuasa

Daigo Fujimura

Kyoko Kawagishi

Hidemichi Koyabu

Toshifumi Kanno

Yutaka Kawata

Nobuhiro Kunitake

Mitsunori Isono

Shigenari Horie

Naoki Hisada

Masato Shida

Daisuke Kudo

Katsumi Namba

Keita Yunoki

Masahiko Toyoda

Naotoshi Okaya

Takahiro Ohta

Souichirou Tomimoto

Akihiko Shirota

Koji Takeshita

Masao Sakamoto

Sumiu Uchida

Akihiro Kawaguchi

Setunori Sakakibara

Hidehiko Nakane

Motoharu Ueda

Rosic Budmir

Hidataka Oguma

A gas turbine exhaust heat recovery plant includes a plurality of gas turbine exhaust heat recovery devices that have a gas turbine and an exhaust heat recovery boiler for generating steam by recovering exhaust heat of the gas turbine, a steam-utilizing facility that utilizes the steam generated by the exhaust heat recovery boiler, and an inter-device heat medium supply unit capable of supplying a portion of water heated or a portion of the steam generated by at least one of the gas turbine exhaust heat recovery devices out of the plurality of gas turbine exhaust heat recovery devices, to the other gas turbine exhaust heat recovery device.

Gas turbine exhaust heat recovery plant

A control device is a control device for a gas turbine including a plurality of combustors and is configured to select combustors to ignite in accordance with a target load on the basis of a predictor which defines a relationship between a load and the number and arrangement of combustors to ignite and a combustion temperature.

Control device, gas turbine, control method, and program

A rotor blade includes a blade body which has an airfoil shape and a shroudwhich is formed in an end portion of the blade body. The shroud includes a shroud cover and a seal fin which protrudes from the shroud cover toward a radial outside and extends in a direction having a direction component in a circumferential direction. A front end of the seal fin extends in the circumferential direction and a base end of the seal fin extends in a direction having a direction component in the circumferential direction. A part of the seal fin in the circumferential direction forms a shift portion. An axial center position of a base end of the shift portion is different from an axial center position of a front end of the shift portion in the axial direction.

Rotor blade and axial flow rotating machine with the same

An intake air cooling device includes a water supply line and a heat pump device. The water supply line is configured to send water to a waste heat recovery boiler which is configured to generate steam using heat of an exhaust gas from a gas turbine. The heat pump device is configured to transfer heat of air suctioned by the gas turbine to water flowing through the water supply line and thereby cool the air while heating the water.

Intake air cooling method, intake air cooling device executing said method, and waste heat recovery facility and gas turbine plant each comprising said intake air cooling device

An axial flow rotating machine has: a rotor with a plurality of rotor blades; a stator with a plurality of stator blades; an axial flow rotating portion defined by the rotor and the stator; and a diffuser connected to the axial flow rotating portion on a downstream side of the axial flow rotating portion. A final blade portion inner-circumferential inner wall, which is a portion of an inner-circumferential inner wall of the axial flow rotating portion, is defined such that a diameter thereof at a trailing edge position of a final blade is smaller than the diameter at a leading edge position of the final blade. In addition, a diameter of all or a portion of a diffuser inner-circumferential inner wall decreases in a direction of the downstream side in an axial direction.

Axial flow rotating machine and diffuser

A turbine rotor blade includes an airfoil portion having an airfoil defined by a pressure surface and a suction surface; and a squealer rib on a tip surface of the turbine rotor blade, the squealer rib extending from a leading-edge side (toward a trailing-edge side. The squealer rib has a ridge extending in an extending direction of the squealer rib. The turbine rotor blade is configured to provide a clearance between the tip surface of the turbine rotor blade and an inner wall surface of a casing of a turbine such that the inner wall surface of the casing of the turbine faces the tip surface of the turbine rotor blade and the clearance has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Turbine blade and gas turbine

A gas turbine provided with an air bleeder tube () that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (), wherein the air bleeder tube () is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.

Gas turbine with an air bleeder tube

An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor () includes a pilot nozzle (); a plurality of main nozzles () arranged apart from the pilot nozzle () in the circumferential direction on the outer peripheral side of the pilot nozzle () and configured to perform premix combustion; a combustor basket () surrounding the pilot nozzle () and each main nozzle (); an outlet outer ring () provided at a tip end of the combustor basket (); and a combustion liner () fitted, at an inner surface thereof, onto the outer periphery of the combustor basket () and surrounding the outlet outer ring (). The outlet outer ring () is formed parallel to an inner wall surface () of the combustion liner ().

Combustor and gas turbine

An erosion test apparatus includes a combustor configured to obtain a combustion gas by mixing and combusting compressed air and a fuel, and an erodent supply unit configured to supply an erodent to the combustion gas. The erosion test apparatus further includes an accommodation support unit configured to accommodate and support a test piece having a front surface coated through thermal barrier coating, and an accelerator configured to accelerate the combustion gas including the erodent to collide with the test piece.

Erosion test apparatus, accelerator and erosion test method

In a turbine exhaust structure and a gas turbine, a turbine casing () formed in an annular shape to constitute a combustion gas passage A is provided. An exhaust diffuser () formed in an annular shape to constitute a flue gas passage (B) is connected to the turbine casing () to constitute a configuration. By providing a pressure loss body () in the exhaust diffuser (), efficient pressure recovery can be carried out, which improves turbine efficiency, thereby enabling improvement of the performance.

Turbine exhaust structure and gas turbine

A flow path structure includes a wall surface in which a flow path is formed, a structure configured to extend in a direction intersecting a main stream direction of a fluid flowing through the flow path from the wall surface, and a concave section forming region formed throughout a range including the structure in the main stream direction and having a concave section formed in the wall surface. As the structure occupies a partial range of the flow path in the flow path cross section intersecting the main stream, a cross-sectional area of the flow path is varied in accordance with positional variation in the main stream direction.

Flow path structure and gas turbine exhaust diffuser

A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.

Gas turbine with improved blade and vane and flue gas diffuser

A gas turbine includes a turbine blade, a turbine vane, a ring segment circumferentially surrounding the turbine blade, an outer shroud circumferentially surrounding the turbine vane, and a combustion gas flow-path provided in the ring segment and the outer shroud. The outer shroud is positioned on an upstream side of the ring segment in a gas flow direction of the combustion gas. Seal gas, of which temperature is lower than that of the combustion gas, is fed between the ring segment- and the outer shroud into the combustion gas flow-path. The outer shroud has a guide surface that is provided on an inner circumference thereof on a downstream side of the gas flow direction. The guide surface is formed such that a flow passage area of the combustion gas flow-path is gradually increased.

Gas turbine and outer shroud

Growing community of inventors

Tokyo, Japan

Eisaku Ito