Hitachi, Ltd.

The Tokyo Electric Power Company, Incorporated

Other

Central Research Institute of Electric Power Industry

Hitaci Maxell, Ltd.

Yoshitaka Kojima

Hiroshi Nakano

Hideyuki Arikawa

Akira Mebata

Katsuhiro Komuro

Yoshimi Hakamata

Toru Tanimizu

Mitsuo Haginoya

Hajime Toriya

Shizuka Yamaguchi

Yoshio Koguchi

Shunkichi Endo

Tetsuo Sasada

Kunihiro Ichikawa

Naotatsu Asahi

Noriyuki Ohnaka

Katsuo Wada

Norio Watanabe

Shoichi Nakashima

Masayuki Doi

Sai Ogawa

Yukiyoshi Hara

Hiroshi Haruyama

Ryoichiro Ohoshima

Ryuta Watanabe

Shin Yoshino

Katsumi Kuroda

Akihiko Chiba

Masanori Sakai

Makoto Hayashi

Hisanobu Kanamaru

Haruo Akahoshi

Yukio Kurosawa

Yoshiaki Matsushita

Hiroyuki Doi

Kenji Araki

Nobuyuki Iizuka

Masahisa Inagaki

Yoshiharu Hayashi

Motoya Ito

Noriyoshi Takahashi

Katsumi Mabuchi

Noboru Baba

Fumiyuki Hirose

Katsumi Ohsumi

Masateru Suwa

Masahiko Arai

Ryo Hiraga

Takuya Takahashi

Tooru Tanimizu

Masatoshi Takada

Isao Masaoka

Shigeru Kikuchi

Seishin Kirihara

Katsuyoshi Terakado

Kenjiro Narita

Nobuhiro Umebayashi

Toshiaki Arato

Masakiyo Izumiya

Susumu Aoyama

Miyako Hotta

Kimihiko Akahori

Yoshikazu Moritomo

Takashi Haramaki

Hideki Tamaki

Fumio Sato

Hironori Kamoshida

Noboru Fujimoto

Hitoshi Okabe

Tohru Hisamatsu

Keiji Arai

Hiroshi Obara

Hiroshi Ishihama

Shunkichi Endoo

Izumi Sakurai

Takayuki Yoshioka

Yukihiko Wada

Kyozo Iwao

Kiyoshi Otake

Yoshinori Negishi

Haijime Toriya

Mitsutoshi Okada

Takeshi Izumi

A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.

High-reliability turbine metal sealing material

An operation control method for a gas turbine includes making a molten salt map of molten salt for causing high-temperature corrosion on high-temperature components of the turbine due to impurities using a thermodynamic equilibrium calculation on the basis of the impurities contained in low-quality fuel and operation data of the gas turbine, indicating a surface temperature and a pressure of the high-temperature components of the turbine on the molten salt map , predicting a lifetime of the high-temperature components of the gas turbine by estimating a corrosion rate thereof, and controlling the flow rate of the low-quality fuel supplied to a combustor so that an area of surface temperature and pressure regions of the high-temperature components superposing on the region of molten salt in the liquid phase on the molten salt map is reduced.

Operation control method for gas turbine and operation controller for gas turbine

A steam turbine rotor shaft and method of manufacturing the same are provided wherein the sliding characteristics of a journal are improved, and the journal is free from welding cracks and does not need a post heat treatment. The low alloy steel coating layer having better sliding characteristics than 9 to 13% Cr heat resisting steel and an area rate of defects including pores and oxides in a range of 3 to 15% is formed by a high velocity flame spray coating method on a sliding surface of the journal.

Rotor for steam turbine and method of manufacturing the same

A high-temperature resistant component for, e.g., a gas turbine hot part, includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.

High-temperature resistant component and gas turbine hot part

There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.

High temperature component with thermal barrier coating and gas turbine using the same

A thermal barrier coating comprises a bond coatingmade of high temperature corrosion resistance superior to a substrateand a thermal barrier coatingmade of ZrO2 series ceramics formed on the bond coating. The thermal barrier coating has cracks extending in the direction of the thickness of the barrier coat. Substantially all of the tips of the cracks have a distance between the tips and the boundary at the substrate side.

Heat resistant article having thermal barrier coating

An apparatus or system is used for planning the rotation of part usage between shafts or plants based at least on schedule information relating to operation and inspection-purpose shutdown, attribute information relating to part life, part maintenance periods, and other part attributes, and part information relating to the parts to be used in the rotation.

Rotation planning apparatus and rotation planning system

A gas turbine washing-date determination apparatus of the present invention is equipped with a sum cost calculation means for calculating a sum of loss cost due to not washing a compressor from a compressor efficiency calculated, and determines a gas turbine washing-date with using the sum of the loss cost. Meanwhile, in the gas turbine washing-date determination apparatus the compressor efficiency is calculated from process data of a gas turbine plant, and a compressor washing-date is determined, based on the compressor efficiency.

Apparatus and method for determining date of gas turbine washing

A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al O layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co&mdash;32%Ni&mdash;21%Cr&mdash;8%Al&mdash;0.5%Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO &mdash;8wt. %Y O ceramic and insulative ceramic (e.g. Al O ), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.

Method for producing a ceramic-coated blade of gas turbine

Multi-core conductive wire and a method of manufacturing the same

Disclosed is a vacuum circuit breaker including a small-sized electrode structure capable of reducing deformation with age thereby enhancing the reliability and a vacuum bulb and a vacuum bulb electrode used for the breaker. In the vacuum circuit breaker, each of a fixed electrode and a movable side electrode includes an arc electrode made from particles of a refractory metal material, a high conductive metal material and a low melting point metal; an electrode supporting portion, made from the high conductive metal material, for supporting the arc electrode; a back conductor having a diameter smaller than the electrode supporting portion; and an external side connecting portion having a diameter larger than that of the back conductor. The arc electrode is integrated with the electrode supporting portion, back conductor, and external side connecting portion by the high conductive metal material, preferably, by melting of the highly conductive metal material.

Vacuum circuit breaker, and vacuum bulb and vacuum bulb electrode used therefor

According to the present invention there are provided a highly reliable electrode of high strength which undergoes little change even with the lapse of time, and a method for making the same, as well as a vacuum valve using such electrode and a vacuum circuit breaker using such vacuum valve. The vacuum circuit breaker has a fixed electrode and a movable electrode, each comprising an arc electrode, an arc electrode support member for supporting the arc electrode, and a coil electrode contiguous to the arc electrode support member, the arc electrode, the arc electrode support member and the coil electrode being formed as an integral structure by melting, not by bonding, particularly the arc electrode support member and the coil electrode being constituted by a Cu alloy containing 0.05-2.5% by weight of at least one of Cr, Ag, W, V and Zr.

Vacuum circuit breaker as well as vacuum valve and electric contact used

A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al.sub.2 O.sub.3 layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co-32% Ni-21% Cr-8% Al-0.5% Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO.sub.2 -8 wt. % Y.sub.2 O.sub.3 ceramic and insulative ceramic (e.g. Al.sub.2 O.sub.3), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.

Ceramic-coated blade of gas turbine and method of producing same

A ceramic coated heat-resistant element comprises a heat resisting alloy base mainly composed of Ni and/or Co and a heat-resistant coating layer provided on the surface of the base and is characterized in that said heat-resistant coating layer comprises a metal layer of an alloy superior to the base in high-temperature corrosion and oxidation resistance and provided on the base, an Al.sub.2 O.sub.3 ceramic thin film layer provided on the metal layer, a ZrO.sub.2 ceramic coating layer having dense texture provided on the Al.sub.2 O.sub.3 ceramic thin film layer and a ZrO.sub.2 ceramic coating layer having columnar texture provided on the ZrO.sub.2 ceramic coating layer having dense texture cracks are present only in the ZrO.sub.2 ceramic coating layer having columnar texture in the direction of thickness along the boundary of the columns. A mixed layer composed of a metal superior to the base in high-temperature corrosion and oxidation resistance and a ZrO.sub.2 ceramic may be provided between the base and the metal layer.

Thermal stress relaxation type ceramic coated heat-resistant element and

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Hitachi, Japan

Yoshitaka Kojima