Hitachi, Ltd.

Satoshi Tsukahara

Michio Kuroda

Yoshihiro Uchiyama

Kazumi Iwai

Shozo Nakamura

Hiroshi Inoue

Isao Sato

Shigehisa Sugita

Ryoichiro Oshima

Masayuki Taniguchi

Shigeru Azuhata

Shohei Yoshida

Hironobu Kobayashi

Yoji Ishibashi

Kazuhito Koyama

Yukio Hishinuma

Kiyoshi Narato

Hiraku Ikeda

Masahiko Yamagishi

Hiromi Koizumi

Hidekazu Fujimura

Tadayoshi Murakami

Zensuke Tamura

Seiichiro Sakaguchi

Yasuhiko Otawara

Noriyuki Hayashi

Yoichi Yoshinaga

Tamio Innami

Youji Ishibashi

Kazuyuki Itoh

Masanobu Kusaba

Kojiro Kaneko

Yasuaki Akatu

A gas turbine combustor includes a diffusion combustor arranged at an axis portion of a combustion chamber for effecting diffusion combustion, a plurality of first premixing combustors arranged at an outer periphery of the diffusion combustor for effecting premixed combustion, each of the plurality of first premixing combustors being formed so that a mixture outlet end thereof projects more downstream than a fuel outlet end of the diffusion combustor, and a plurality of second premixing combustors each formed so that a mixture outlet thereof projects more downstream than the mixture outlet end of the first combustor, wherein the first premixing combustors and the second premixing combustors are arranged alternately at the outer periphery of the diffusion combustor, and wherein a swirler is provided on the first premixing combustor in the vicinity of the mixture outlet end thereof for swirling mixture.

Gas turbine combustor

A method for controlling a plurality of combustors supplying a pressurized gas to a gas turbine, with each of the combustors including a first air supply for supplying a combustion air into the combustor and a second air supply for adjusting an amount of air supplied into the combustor to change a combustion condition in the combustor. The method comprises the steps of measuring the combustion condition of each of the combustors, measuring a difference between the measured combustion condition of each of the combustors and a desired combustion condition, and changing a rate of the amount of air supplied into the combustor by the second air supply means in relation to an amount of combustion air supplied into the combustor by the first air supply in each of the combustors according to the measured difference of each of the combustors to change the combustion condition of each of the combustors so that the combustion conditions of the combustors are changed to the desired combustion condition.

Method and device for controlling combustors for gasturbine

In a combustor including a premixing type combustion burner which has an atomizer for ejecting a liquid fuel together with combustion air to atomize the liquid fuel, the atomizer is comprised of an inner shell to an inner peripheral surface of which the liquid fuel is supplied, an outer shell defining a passage for the combustion air running substantially straightly between the outer shell itself and an outer peripheral surface of the inner shell, and a swirling-flow guide plate for swirling the combustion air passed into the inner shell, while directing it in a downstream direction. The combustor further includes a resistor abruptly decreased in sectional area downstream and provided substantially downstream of the center of the swirling flow and in the vicinity of an outlet of the premixing type combustion burner for providing a resistance to a premixture ejected from the premixing type combustion burner.

Combustor and combustion apparatus

A premixed combustor for a gas turbine, comprises, a combustion chamber for burning a fuel with an air therein, at least two premixed fuel/air mixture outlets which are juxtaposed with each other, and through each of which a premixed fuel/air mixture flows out into the combustion chamber, and a flow deflection member arranged between the premixed fuel/air mixture outlets, urging the permixed fuel/air mixture from one of the premixed fuel/air mixture outlets to go away from another one of the premixed fuel/air mixture outlets, and terminating in the combustion chamber so that the premixed fuel/air mixture from the one of the premixed fuel/air mixture outlets is permitted to move toward the premixed fuel/air mixture flowing out from the another one of the premixed fuel/air mixture outlets after going away from the another one of the premixed fuel/air mixture outlets.

Combustor for gas turbine

In combustion of gasified fuel by gasifying a low quality fuel and combusting the gasified fuel in a combustor, combustion of gasified fuel is controlled by sampling the gasified fuel at a constant flow rate at the upstream side of the combustor, combusting the sampled gasified fuel, detecting an overall energy level of sensible heat and heating value possessed per unit weight of the gasified fuel on the basis of the combustion temperature of the sampled gasified fuel, and controlling the flow rate of gasified fuel to be led to the combustor in accordance with a fluctuation in the detected overall energy level. Unstable combustion due to a fluctuation in the heating value of the gasified fuel and blow-out due to deficiency of the heating value can be prevented.

Method and apparatus for controlling combustion of gasified fuel

A power generating plant which includes a direct contact-type heat exchanger. A low-boiling point medium such as freon and a heat-source medium such as heated oil, are injected from a lower portion of the heat exchanger so that the two media are brought into direct contact with each other thereby vaporizing the gaseous low-boiling point medium. The low-boiling medium acts as a working fluid while it circulates through a closed cycle of the plant which includes a turbine and a condenser. The heat-source medium, circulates in a closed cycle of the plant which includes a heating unit.

Power-generating plant having increased circulating force of working

A combustor for gas turbines includes a stepped cylindrical tube defining first, second and main combustion spaces. Primary air supply openings are formed in the tube portion defining the first combustion space, secondary air supply openings in the tube portion defining the second combustion space, and diluting air supply openings in the tube portion defining the main combustion space. To achieve effective cooling of the combustion gas within the combustion chamber, particularly in the second combustion space, and especially in the central portion thereof, and at the same time to maintain a stable combustion, the tube is formed so, and the cross-sectional areas of the primary, secondary and diluting air supply openings are dimensioned so, that 25 to 32% of the total amount of air supplied to the combustion chamber are used as primary air in the first combustion space, 38 to 50% as secondary air in the second combustion space, and less than 30% as diluting air in the main combustion space.

A reducing agent such as ammonia, urea or hydrazine effecting selective reduction reaction with an exhaust gas from a gas turbine is injected into a duct of the turbine along with water, and at the same time compressed air from a compressor for the turbine is jetted in the duct to atomize the reducing agent. An amount of the water is controlled so that the surrounding temperature will be suitable for reduction of nitrogen oxides of the exhaust gas. The atomized reducing agent flowing in the duct is decelerated by silencers disposed in the duct, especially by a particular arrangement thereof, so that the reducing agent will be in good contact with the exhaust gas to sufficiently reduce the nitrogen oxides. Catalyst layers are used according to kinds of the reducing agent. The catalyst layers are disposed in the silencers or at the positions that the silencers are disposed.

Apparatus for the treatment of gas turbine exhaust gas

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Hitachi, Japan

Satoshi Tsukahara