Hitachi, Ltd.

Hitachi Power Engineering Co., Ltd.

Hajime Toriya

Tetsuo Sasada

Yutaka Fukui

Hiroyuki Doi

Yoshitaka Kojima

Masao Siga

Haruo Urushidani

Hideyuki Arikawa

Akira Mebata

Kenjiro Narita

Toshio Fujita

Isao Takehara

Kishio Hidaka

Shigeyoshi Nakamura

Yasushi Hayasaka

Ryo Hiraga

Ryoichi Kaneko

Masao Shiga

Mitsuo Haginoya

Haruyuki Yamazaki

Kei Kobayashi

Kenichi Murata

Shigeru Azuhata

Michio Kuroda

Nobuyuki Iizuka

Isao Sato

Yoji Ishibashi

Masahiko Arai

Kenta Suzuki

Yasuhiro Katoh

Makoto Hemmi

Kuniyoshi Tsubouchi

Tomoaki Inoue

Shunichi Anzai

Takashi Ohmori

Keizou Ohtsuka

Kazuhiko Kumata

Hirotsugu Kawanaka

Yoshikazu Moritomo

Saburo Usami

Shigeo Sakurai

Sadao Umezawa

Mitsuo Teranishi

Naoaki Shibashita

Hiroshi Miyata

Nobuhiro Isobe

Akio Sohma

Kiyoshi Shimomura

Katsuhiro Murakami

Koji Kawai

Shuuhei Nogami

Kuzuhiko Kawaike

Yoshihiro Tsuda

Mitsuaki Yanagida

Kiyoshi Otake

Shoji Ebine

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

The present invention is a steam turbine rotor blade assembly including: an airfoil; a shroud provided at a tip of the airfoil; a blade root (dovetail) projecting toward a radially internal circumferential side of a turbine rotor and fitted to a root attachment provided on an outer circumferential portion of the turbine rotor; a platform provided between the airfoil and the blade root; a pin provided between the blade root and the root attachment; a bore formed between respective surfaces of the shrouds facing each other and included in the respective adjacent rotor blades; and a bar-like member provided in the bore.

Steam turbine rotor blade assembly

A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device.

Seals in steam turbine

An increase in the temperature of a sliding bearing can be suppressed, and it is possible to reduce the temperature of the bearing and prevent burning and damage. The bearing is divided in two and composed of a liner and a base metal. The liner is disposed on an inner circumferential side of the bearing, and the base metal is disposed on an outer circumferential side of the bearing. A lower liner of the bearing liner, which is located on a load-receiving side, has a cooling groove formed in an outer circumferential surface thereof and extending along a circumferential direction thereof. A lubricant is cooled in the cooling groove and supplied to reduce the temperature of a shaft-sliding surface of the bearing. The lubricant is supplied to the bearing, increases in temperature due to the cooling and has low viscosity.

Journal bearing device

A steam turbine blade includes a blade; a shroud attached to a tip of the blade; a blade root projecting toward the radial inner circumferential side of a turbine rotor so as to be fitted into a blade groove provided in an outer circumferential portion of a turbine rotor; and a platform disposed between the blade and the blade root. The blade root is inserted into the blade groove along the axial direction of the turbine rotor. The blade, the shroud, the blade root and the platform are integrally molded. The number of the blade roots is larger than that of the blades.

Steam turbine blade, and steam turbine and steam turbine power plant using the blade

A pipe for a steam turbine is formed of a centrifugal casting material to achieve resistance against higher temperatures and improve reliability of the pipe by employing, as a pipe material, a centrifugal casting material normalized to contain uniform and finer crystal grains. The centrifugal casting material is made of steel having a columnar structure in the radial direction with the crystal grain size number of 5 or more in a plane perpendicular to the radial direction. The steel includes 0.05-0.5% by mass C, not more than 1.0% Si, 0.05-1.5% Mn, 0.01-2.5% Ni, 8.0-13.0% Cr, 0.05-2.5% Mo, not more than 3.0% W, 0.05-0.35% V, 0.01-0.5% Nb, not more than 5% Co, 0.01-0.1% N, not more than 0.03% B, and not more than 0.05% Al.

Pipe for steam turbine, manufacturing process of same, main stream pipe and reheat pipe for steam turbine, and steam turbine power plant using those pipes

Gas turbine for power generation

Gas turbine for power generation, and combined power generation system

A compressor for a gas turbine, comprises a rotor including a plurality of rotor parts, and blades for a plurality of stages implanted in the rotor parts, the rotor part in which the blades for at least two of the stages are implanted is made of a Ni--Cr--Mo--V low alloy steel, and the Ni--Cr--Mo--V low alloy steel has substantially an entire bainite microstructure comprising, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35% and the balance being substantially Fe.

Compressor for turbine and gas turbine

A compressor for a gas turbine, comprises a rotor including a plurality of rotor parts, and blades for a plurality of stages, e.g., twelve stages, implanted in the rotor parts, the rotor part in which the blades for at least two of the stages are implanted is made of a Ni--Cr--Mo--V low alloy steel, and the Ni--Cr--Mo--V low alloy steel has substantially an entire bainite microstructure comprising, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35% and the balance being substantially Fe. Blades for at least two of the stages are implanted in one of the rotor parts.

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

The present invention provides ceramic coated heat-resistant elements which suffer no damages even under high heat load conditions and can afford a thermal barrier effect stably for a long period of time and can be used, for example, as buckets and stationary blades of turbines. A method for making the elements is also provided. The 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 and cracks are present only in said 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

An axial flow compressor for use in a gas turbine or other industrial application having an improved efficiency is provided through modification of the blade shape and profile of the blades subject to a subsonic high velocity inlet flow so as to avoid shock losses in the blade rows, and improve the total efficiency. The curvature distribution on the suction surface of the stator blade rows or rotor blade rows of the axial flow compressor is adapted to have a local minimum in a region toward the leading edge of the blade, and then a local maximum. Thereby, an excessive increment in velocity on the suction surface from the leading edge to the position of the maximum velocity can be suppressed, and the occurrence of a shock wave can be avoided so as to minimize pressure loss in the blade rows, thus increasing the total efficiency of the axial compressor.

Blade profile for axial flow compressor

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Hitachi, Japan

Hajime Toriya