Hitachi, Ltd.

Hitachi Power Engineering Co., Ltd.

Haruo Urushidani

Isao Sato

Tetsuo Sasada

Seiichi Kirikami

Akira Shimura

Osamu Arai

Hajime Toriya

Michio Kuroda

Nobuyuki Iizuka

Katsukuni Hisano

Yoji Ishibashi

Kazuhiko Kumata

Tsuguo Hashimoto

Norihisa Wada

Shigeru Azuhata

Isao Takehara

Fumiyuki Hirose

Ryoichi Kaneko

Takashi Ohmori

Hiroshi Inose

Yasuyuki Watanabe

Takeshi Sato

Kazuhiko Kawaike

Koji Takahashi

Nariyoshi Kobayashi

Masami Noda

Takashi Ikeguchi

Hiraku Ikeda

Shunichi Anzai

Kazuo Ikeuchi

Kazuyuki Ito

Yasutaka Komatsu

Yoshikazu Moritomo

Nobuo Shimizu

Masaya Ohtsuka

Tsuguaki Koga

Akira Okabe

Seisaku Takihana

Hideaki Kaneda

Katsuto Kashiwahara

Naoaki Shibashita

Takeshi Iwamiya

Kunio Tsuji

Mitsuo Teranishi

Tomo Sato

Kiyoshi Shimomura

Tadashi Kurokawa

Hiroyuki Arai

Shoji Ebine

A system configuration and operating method for a single shaft combined cycle plant includes a gas turbine, an exhaust heat recovery boiler for generating steam using exhaust heat discharged from the gas turbine, and a steam turbine driven by steam generated from the exhaust heat recovery boiler. Rotors of the gas turbine and rotors of the steam turbine are coupled. The steam turbine includes a high pressure turbine being supplied with and driven by high pressure steam generated at a superheater of the exhaust heat recovery boiler and a reheating turbine supplied with and driven by steam that passes through the high pressure turbine and is reheated by a reheater of the exhaust heat recovery boiler. The gas turbine operates independently and a regulated amount of cooling steam is supplied to the steam turbine in order to prevent superheating due to windage loss of the steam turbine rotating in an unventilated state. A bypass path is provided in parallel with the exhaust heat recovery boiler as a path through which cooling steam flows in order to further raise the cooling effect, and each turbine and a condenser are made to communicate so as to make pressure within the turbines low.

Single shaft combined cycle plant and operating thereof

Single shaft combined cycle plant and method for operating the same

In a system configuration and operating method for a single shaft combined cycle plant comprising a gas turbine (,), an exhaust heat recovery boiler (,) for generating steam using exhaust heat discharged from the gas turbine; and a steam turbine (,) driven by steam generated from the exhaust heat recovery boiler (,), rotors of the gas turbine (,) and rotors of the steam turbine (,) being coupled, and the steam turbine comprising a high pressure turbine (,) being supplied with and driven by high pressure steam generated at a superheater of the exhaust heat recovery boiler (,) and a reheating turbine (,) supplied with and driven by steam that passes through the high pressure turbine (,) and is reheated by a reheater of the exhaust heat recovery boiler (,), the gas turbine (,) operates independently, a regulated amount of cooling steam is supplied to the steam turbine (,) in order to prevent superheating due to windage loss of the steam turbine (,) rotating in an unventilated state, a bypass path (,) is provided in parallel with the exhaust heat recovery boiler (,) as a path through which cooling steam flows in order to further raise the cooling effect, and each turbine and a condenser (,) are made to communicate so as to make pressure within the turbines low.

Single shaft combined cycle plant and operating method thereof

A gas turbine combustor having a fuel injection nozzle for diffusion combustion disposed in a central portion of the combustor and an annular premixed nozzle disposed in an outer peripheral portion of the fuel injection nozzle for injecting a mixed gas of fuel and air. The annular premixed nozzle includes an annular premixing chamber and a plurality of premixed fuel nozzles for injecting fuel into the annular premixing chamber. The annular premix nozzle is divided by a partition (108) to form a plurality of premixing chambers each adjacent to the fuel injection nozzle for diffusion combustion. Each of the premixing chambers includes at least one of the premixed fuel nozzles. A mechanism is provided for supplying fuel to a predetermined number of the premixing chambers in a low load operation of the gas turbine and for supplying fuel to all of the premixing chambers in a high load operation.

Gas turbine combustor and operation method thereof for a diffussion

To provide a combustion apparatus and a controlling method therefor which are capable of preventing the flame-out and backfire of the flame of a premix burner and the increase of the NOx concentration attributable to the change of the calorific value of the fuel, the amount of air supplied to the premix burner is so controlled as to achieve a low NOx within the range in which the premix burner effects a stable combustion in accordance with the calorie of the fuel supplied to the combustion apparatus, and a change of the output of the combustion apparatus attributable to this control of the amount of air is compensated by the control of the amount of the fuel supplied to the diffusion burner.

Combustion apparatus and control method therefor

A fuel supply amount is controlled while the load of a gas turbine is changed so that the fuel supply amount is shifted to a fuel supply amount in accordance with the changed load. A fuel supply control valve is operated at high speed during an initial stage and operated at a lower speed as the fuel supply amount necessary for the changed load is reached. Therefore flameout of a combustor is prevented without increasing the number of revolutions of the gas turbine over a certain upper limit.

Method and apparatus for controlling the supply of fuel to a gas turbine

A burner comprises at least one swirl member for mixing a fuel with an air previously to burning of the fuel, and at least one eddy generating device which is arranged in a flow of a mixture of the fuel and air to generate an eddy flow in the flow so that the eddy flow maintains a shape of a flame of the burned fuel. The at least one eddy generating device is arranged apart from a downstream end of the swirl member by a fixed sufficient distance so that the shape of the flame maintained by the eddy flow is prevented from moving toward the downstream end of the swirler member.

Burner having one or more eddy generating devices

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 method of starting wherein the gas turbine, a gas turbine is started while injecting a prescribed amount of moisture into a combustor or a path for combustion gas from start up of the gas turbine, and the amount of moisture is varied in dependence upon the feed quantity of fuel or the temperature of the combustion gas so that combustion temperature in the combustor or temperature variation rate of the surfaces of component parts of the gas path is approximately constant.

Method of starting gas turbine

A method for detecting combustion conditions in a plurality of combustors in a gas-turbine apparatus which includes the combustors and a gas turbine driven by combustion gas from the combustors, comprises a step for measuring concentration of unburnt component in the combustion gas by means of a plurality of sensors disposed on the downstream side of the gas turbine, a step for obtaining a distribution pattern of the measured concentration, and a step for investigating the distribution pattern to detect combustion conditions in the combustors.

Method for detecting combustion conditions in combustors

A cooling structure for a turbine blade. Comprising a hollow-structured main body and a cooling medium discharging device located in the inner cavity of the hollow-structured main body and formed to discharge a cooling medium from the surface thereof, so that the cooling medium discharged from the cooling medium discharging device impinges against the inner surface of the main body to remove the heat from the same. The turbine blade further includes a projection formed on the inner surface of the leading edge of the main body, extending along the spanwise direction of the blade, and the cooling medium discharging device is formed to allow at least part of the cooling medium to directly impinge against proximal portions of the projection. With this arrangement, a turbine blade is provided which allows a small amount of cooling air to cool the turbine blade and its leading edge in particular with great effectiveness.

Turbine blade

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 device for detecting combustion conditions in a plurality of combustors in a gas-turbine apparatus which includes the combustors and a gas turbine driven by combustion gas from the combustors, comprises a plurality of sensors for measuring concentration of unburnt component in the combustion gas, which is disposed on the downstream side of the gas turbine, a unit for obtaining a distribution pattern of the measured concentration and for investigating the obtained distribution pattern to detect combustion conditions in the combustors.

Device for detecting combustion conditions in combustors

A gas turbine rotor warming structure comprises a tubular member having an axially extending central through hole and a plurality of fine holes formed in a side wall thereof. The tubular member is inserted in central holes of rotor disks each having blades so as to form an annular gap between the inner surfaces of the central holes and the outer surface of the tubular member. The plurality of fine holes of the tubular member are formed so as to face the inner peripheral surface of the central holse of the rotor disks, so that gas extracted from a compressor is injected into the annular gap through the fine holes and impinges on the inner peripheral surfaces of the rotor disks, whereby inner peripheral portions of the rotor disks are warmed at the time of starting of the gas turbine. The extracted compressor gas which has warmed the inner peripheral portions of the rotor disks passes between the disks and cools the turbine blades.

Warming structure of gas turbine rotor

A method of starting a turbine having a shrinkage-fitted rotor provided by shrinkage-fitting discs onto a shaft comprises the steps of raising the temperature of the rotor above a predetermined temperature determined from a physical value of the material constituting the rotor and, thereafter, raising the rotational speed of the turbine from the turning speed to the rated speed, whereby the centrifugal stress on raising the speed acts on the discs in a state wherein the value of fracture toughness of the discs fitted on to the shaft has increased.

Method and an apparatus for starting a turbine having a shrinkage-fitted

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Hitachi, Japan

Haruo Urushidani