Hitachi, Ltd.

Katsukuni Hisano

Yoji Ishibashi

Michio Kuroda

Nobuyuki Iizuka

Isao Sato

Toshimi Tan

Fumiyuki Hirose

Katsuo Wada

Seishin Kirihara

Takatoshi Yoshioka

Osamu Arai

Haruo Urushidani

Seiichi Kirikami

Kazuo Ikeuchi

Takashi Ohmori

Fumio Kato

Hiroshi Inose

Takashi Hashimoto

Takeshi Sato

Hiroshi Inoue

Masao Siga

Yoshihiro Uchiyama

Ryoichi Kaneko

Masao Shiga

Akira Arai

Tsuguaki Koga

Yasuhiko Otawara

Satoshi Ninomiya

Kei Kobayashi

Masahiro Kobayashi

Katsuto Kashiwahara

Shigeyuki Akatsu

Kunio Tsuji

Hazime Sibaoka

Hiroshi Matsumoto

Kazuo Sato

Makoto Nishimura

Shozo Nakamura

Yoshio Sato

Tetsuo Sasada

Akira Sakai

Shigeyoshi Kawano

Kiyoshi Namura

Yoshiyuki Nakano

Akira Shimura

Katsumi Iijima

Nobuo Shimizu

Ryoichiro Oshima

Fumio Fujisawa

Ichiya Sato

Takao Yoneyama

Yoji Akutsu

Yasuhiro Tennichi

Sho Kusumoto

Akira Uenishi

Toshihiko Higashi

Norio Yasugahira

Hidesumi Kuwashima

Koki Shiohata

Takehiko Yoshida

Jube Matsumura

Katsumi Oyabu

Keiichi Tsuchiya

Ryosuke Arie

Masashi Kunihiro

Hitoshi Isa

Akira Isida

Kazuhiko Ueda

Osamu Sakuda

Tadashi Kurokawa

Koichiro Fukushima

Masaharu Ohno

Takao Mizoi

Yasuhiro Yamachi

A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber.

Gas turbine combustor

A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.

Gas turbine combustor and methodd of operating the same

A gas turbine combustor comprising a head combustion chamber and a rear combustion chamber connected to a downstream side of the head combustion chamber, a first stage burner for premixing first stage fuel and air and supplying the resultant fuel and air premixture into the head combustion chamber to effect first stage premix combution, a second stage burner for premixing second stage fuel and air and the resultant fuel and air premixture into the rear combustion chamber to effect premix combustion in addition to the first stage premix combustion, and a device for regulating flow rates of combustion air to be premixed with first and second stage fuel. The combustor is further provided with a pilot burner in the head combustion chamber to form pilot flame and stabilize the first stage premix combustion.

Gas turbine combustor and combustion method therefor

A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Gas turbine combustor and method of running the same

In a combustion air flow rate adjusting device in which a cylindrical regulating ring fitted about an outer peripheral surface of an inner cylinder of a gas turbine combustor is translated along the outer peripheral surface of the inner cylinder in order to vary an opening area of air intake ports formed in the peripheral wall of the inner cylinder, an arcuately moving part at a forward end of a lever fixedly connected to a forward end of a shaft extending inwardly through a peripheral wall of an outer cylinder of the gas turbine combustor is connected to a part reciprocating together with the regulating ring, by leaf springs.

Combustion air flow rate adjusting device for gas turbine combustor

A combustor of two-stage combustion type in which fuel is supplied only from primary fuel nozzles for combustion only in primary combustion chamber under the operating condition where gas turbine load is low, and premixed mixture is supplied into a secondary combustion chamber provided on the downstream side of the primary combustion chamber for combustion in both the primary and secondary combustion chambers under the operating condition where the load is high. An air-bleed passageway opens on a downstream side of air holes for intaking secondary combustion air to be mixed with secondary fuel and communicates with the outside of the combustor. The air-bleed passageway is provided with a regulating valve and the secondary combustion air is bled at the minimum point of the load where the secondary fuel is supplied so that the fuel to air ratio of secondary premixed mixture may not be excessively lean, thereby reducing the production of non-burned components.

Combustor for gas turbine

A method of starting a gas turbine plant, which plant has at least one combustor including a primary combustion chamber into which primary fuel nozzles open and a secondary combustion chamber into which secondary fuel nozzles open, a compressor for supplying the combustor with compressed combustion air, and a gas turbine driven by the combustion gas generated in the combustor and adapted to drive a load such as an electric power generator. When the gas turbine is being accelerated to a rated speed or while the load is still below a normal load range, a fuel is supplied only to the primary fuel nozzle, whereas, in other loaded operation range, the fuel is supplied to both the primary and secondary fuel nozzles. Before the fuel supply to the secondary fuel nozzles is commenced, a part of the compressed air is bled through at least one air bleed pipe leading from the compressor and having an air bleed valve. The air bleed valve is controlled in such a manner that the opening degree thereof is maximized when the fuel supply to the secondary fuel nozzles is commenced and is progressively decreased in accordance with the increase of the load such as to become substantially zero when the load has been increased to the normal load range.

Method of starting gas turbine plant

A gas turbine combustor having a head combustion chamber and a rear combustion chamber, with a plurality of air supply ports arranged in a circumferential wall of the rear combustion chamber, and a fuel nozzle. An outer cylinder forms a cylindrical air flow passage between the inner cylinder and the outer cylinder. A cylindrical control member is provided which is adapted to be movable in an axial direction for regulating an opening of the air supply ports. The control member is supported by a supporting means which is adapted to maintain a gap between the control member and the wall of the rear combustion chamber. The supporting member includes a flexible member for absorbing a deformation of the control member during the axial movement of the control member so that it is possible to prevent, if not avoid, mechanical wear on the control member and to reduce the No.sub.x concentration as well as obtain a highly reliable operation of the gas turbine combustor.

A stage structure of an axial turbine includes a stationary inner ring, a stationary outer wall, a row of stationary blades mounted on the stationary inner ring and outer wall, a row of moving blades, and a shroud ring mounted on the tips of the moving blades. An annular solid substance, disposed immediately downstream of an axial gap formed between an axial end of the shroud ring and surface of the outer wall axially facing the axial end of the shroud ring, reduces an expansion space provided immediately downstream of the axial gap, whereby circulation of an ejection flow from a main stream through the axial gap is reduced so that the turbine stage efficiency is improved. The annular solid substance may be a ring fixed to the stationary outer wall, a protrusion or a cylinder formed by a portion of the outer wall.

Turbine stage structure

A turbine blade of a low blade profile loss with a crossing point of an inlet angle .alpha..sub.1 an outlet angle .alpha..sub.2 being located in a position in which a distance between a crossing point of the outlet end of the blade is greater than one-half of the blade width L.sub.ax, with the inlet angle .alpha..sub.1 being in the range of 35.degree.-40.degree. and the outlet angle .alpha..sub.2 being in the range of 25.degree.-28.degree.. A ratio of a narrowest width S.sub.2 of the flow channel at the blade outlet end to a narrowest width S.sub.1 of a flow channel defined between a backside of the blade in an area of the crossing point and a front side of adjacent blade lies in the range of 0.81-0.96. A ratio of a distance L.sub.ax to a blade width L.sub.ax is in the range of 0.5-0.54, with a ratio of a distance L.sub.m from an outlet end of the blade to the blade width L.sub.ax being in a range of 0.75-0.89. A ratio of a distance from the maximum projecting point to a line connecting to the outlet end of adjacent blades is in a range of 0.6-0.66. By virtue of the blade profile, the flow velocity differential between the fluid flowing along the front side of the blade and the fluid flowing along the backside of the blade can thereby be reduced.

Turbine blade

A steam turbine rotor shaft made of precipitation-hardened forged austenite steel, comprising first, second and succeeding layers of build-up welding provided on an outer surface of a bearing portion of a journal section in the rotor shaft, the first layer being provided by use of a welding rod of Ni base alloy, the second and succeeding layers being provided by use of a welding rod of low alloy steel which layers have better bearing characteristics than those of the austenite steel.

Steam turbine rotor shaft

A steam turbine rotor shaft comprising the main body of the rotor shaft made of a high Cr steel of martensite structure, and a journal having a plurality of built-up welding layers formed successively said main body, the outer surface portion of the journal being made of steel containing 0.5 to 3 wt % of Cr, and a method of producing same.

Rotor shaft of steam turbine

A rotor shaft for steam turbines has a journal portion to be supported by a bearing. The journal portion is provided with a sleeve for a bearing made of an alloy of bainite structure comprising 0.04 to 0.35% C, 0.2 to 2% Mn, less than 1% Si, 0.5 to 3% Cr, less than 5% Ni, and less than 0.5% V, having yield strength of more than 50 kg/mm.sup.2 and Lt of less than 24. The sleeve is divided into two semicylindrical segments, and they are arranged on a small diameter portion of the shaft adjacent to said journal portion, welded into one piece, and subjected to stress relief treatment at a temperature higher than a temperature of tempering conducted to the sleeve before welding. The welded sleeve is fitted on the journal portion by shrink-fit so that the sleeve can be served as a superior bearing.

Rotor shaft and manufacturing method thereof

A method and apparatus for detecting the occurrence of rubbing in a rotary machine, in which at least one acoustic sensor is mounted on at least the rotor part or the stator part of the rotary machine, and the output signal from the acoustic sensor is detected and then filtered to extract a frequency component having a frequency substantially equal to the rotational frequency of the rotary machine, so as to detect the occurrence of rubbing in the rotary machine as early as possible and also to locate the source of the rubbing. Even when the occurrence of abnormal metal-to-metal contact at a bearing of the rotary machine is detected, it is discriminated from rubbing so that the occurrence of the rubbing can be reliably detected.

Method and apparatus for detecting rubbing in a rotary machine

A rotor shaft suitable for use as the rotor shaft of a steam turbine. The rotor shaft has a rotor shaft portion made of a Cr alloy steel having martensite structure and containing 8 to 13% Cr. The rotor shaft body is provided with at least one journal portion at which the rotor shaft is rotatably supported by a bearing. The rotor shaft further has a sleeve fitted around each journal portion. The sleeve is divided in the circumferential direction into a plurality of segments which are assembled together by welding or fitting into the sleeve having a circular cross-section. Due to the provision of the sleeve around the journal portion, the rotor shaft made of Cr alloy steel can have improved bearing properties.

Rotor shaft

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Hitachi, Japan

Katsukuni Hisano