Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Mitsubishi Jukogyo Kabushiki Kaisha

Yasuoki Tomita

Kiyoshi Suenaga

Hiroki Fukuno

Masamitsu Kuwabara

Friedrich Soechting

Shunsuke Torii

Yukihiro Hashimoto

Eiji Akita

Sunao Aoki

Shigehiro Shiozaki

Eisaku Ito

Taku Ichiryu

Ichiro Fukue

Koji Watanabe

Satoshi Hada

Junichiro Masada

Masahito Kataoka

Tatsuo Ishiguro

Kenichi Arase

Katsuhiko Abe

Charles Ellis

Toshiaki Sano

Shinichi Inoue

Hideki Murata

Kazuo Uematsu

Masaki Ono

Kuniaki Aoyama

Kazuharu Hirokawa

Ryotaro Magoshi

Hideaki Kaneko

Koichi Akagi

Masaaki Matsuura

Masao Terazaki

Tatsuaki Fujikawa

Akihisa Endo

Jun Kubota

Yoshichika Sato

Hisato Arimura

Shigeyuki Maeda

Akihiko Shirota

Kotaro Ohshima

Yugo Tokunaga

Kouji Watanabe

Katsunori Tanaka

Hideaki Sugishita

Hiroyuki Aoki

Masanori Yuri

Tsuyoshi Kitamura

Masumi Nomura

Shintaro Kumano

Hiroshi Asano

Ichiro Nagano

Yoshifumi Okajima

Yukihiko Inoue

Kengo Yamaguchi

Rintaro Chikami

Saki Matsuo

Hidemichi Koyabu

Vincent Laurello

Takahiro Yamauchi

Masato Shida

Masayuki Takahama

Kenichiro Takeishi

Toshishige Ai

Yoshiyuki Morii

Naoki Hagi

Shun Niizuma

Motoshi Takasu

Hiroji Tada

Osamu Isumi

Yoshimasa Takaoka

Tomohiro Baba

Takashi Fukura

Nobuhiro Osaki

Masamitsu Okuzono

Lars Thomsen

Wataru Kawai

Tsuyoshi Kinoshita

Yuki Enomoto

Shinsaku Endo

Etsushi Kanno

Takahiro Kawaguchi

Takayoshi Isoda

Kazuyuki Misawa

Masao Ogino

Hiroshige Matsuoka

A state quantity acquisition unit acquires a state quantity of a target apparatus including a temperature of the target apparatus. A load specification unit specifies a load history of the target apparatus, based on the state quantity. A remaining life calculation unit calculates a parameter related to a remaining life of the target apparatus for each of a plurality of degradation types, based on the load history specified by the load specification unit.

Apparatus state estimation device, apparatus state estimation method and program

A turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade are disclosed. The turbine blade has a blade body having hollow shape, cavities defined inside the blade body, and a cooling passage that opens from the cavities to a rear end portion of the blade body. The cooling passage includes: a first passage on a third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage on a rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.

Turbine blade, gas turbine, intermediate product of turbine blade, and method of manufacturing turbine blade

A diagnostic device includes a storage unit that stores first information including a first abnormal event which occurred in the past in a plant, a first attribution event that is a cause of the first abnormal event, and a first occurrence probability of the first attribution event, in which a causal relationship between the first abnormal and attribution events is indicated by a tree structure, and second information including a second abnormal event which is supposed to occur in the plant but has not yet occurred, a second attribution event that is a cause of the second abnormal event, and a second occurrence probability of the second attribution event, in which a causal relationship between the second abnormal and attribution events is indicated by a tree structure; and an estimation unit that estimates the cause of the sign of the abnormality, based on the first and second information.

Diagnostic device, diagnostic method, and program

A state quantity acquiring unit is configured to acquire a state quantity of a turbine. A time calculation unit is configured to calculate an operable time at an over firing operation of the turbine based on a design life of the turbine and a state quantity. A distance calculation unit configured to calculate a Mahalanobis distance based on the state quantity. A determination unit configured to determine whether or not the over firing operation of the turbine is possible by the Mahalanobis distance and the operable time.

Plant analyzer, plant analysis method, and program thereof

In order to provide a turbine blade fatigue life evaluating method for quantitively evaluating the fatigue life of a turbine blade, the turbine blade is determined to be within its fatigue life if the creep elongation strain in the longitudinal direction of the turbine blade is less than 0.5% of an initial length, and is determined to exceed its fatigue life if the creep elongation strain is 0.5% or more than the initial length. A turbine blade creep elongation strain measuring apparatuscomprises a first fixed end, a second fixed end, and a dial gauge. A dimension in the longitudinal direction is stamped on the surface of a turbine blade.

Turbine blade fatigue life evaluating method

In a gas turbine having a plurality of moving blades provided on a rotary shaft in a circumferentially adjoining condition, a seal pin is provided in a spacing between the shanks of the adjacent moving blades for preventing leakage of cooling air from a blade root portion side to an airfoil side; an arcuately depressed portion is formed on the shank of each of the moving blades; and vibration of each of the moving blades is suppressed in such a manner that the seal pin serves as a spring system while the airfoil portion, the platform, the shank, and the blade root portion serve as a mass system.

Moving blade and gas turbine using the same

A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises a rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in a circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.

Rotating blade body

The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.

Gas turbine stationary blade

An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extend along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.

Ring segment of gas turbine

Holesandhave upstream opening portionsandand downstream opening portionsandwhich have a larger cross-sectional area than upstream opening portionsand, and are formed at top portion TP of each moving blade. Holesandhave tapered shapes Tand Tor step portions, and preferably, downstream opening portionsandare eccentrically formed toward the moving direction. When tip squealeris formed, holeis formed so that its opening portion is provided at the side surface of tip squealer. Without covering the holes for cooling which are formed at the top portion of the turbine blade due to rubbing or the like, the turbine blade is accurately cooled and stably driven.

Turbine blade and gas turbine

The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.

Turbine moving blade and gas turbine

In order to provide a turbine blade creep life evaluating method for quantitively evaluating the life of a turbine blade, the turbine blade is determined to be within its allowable life if the creep elongation strain in the longitudinal direction of the turbine blade is less than 0.5% of an initial length, and is determined to exceed its allowable life if the creep elongation strain is 0.5% or more than the initial length. A turbine blade creep elongation strain measuring apparatuscomprises a first fixed end, a second fixed end, and a dial gauge. A dimension in the longitudinal direction is stamped on the surface of a turbine blade.

Turbine blade creep life evaluating method, turbine blade creep elongation strain measuring apparatus, and turbine blade

The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A low passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.

The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.

Division wall and shroud of gas turbine

A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.

Stationary blade in gas turbine and gas turbine comprising the same

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Takasago, Japan

Yasuoki Tomita