Hitachi, Ltd.

Noriyuki Hayashi

Michio Kuroda

Masayuki Taniguchi

Isao Sato

Nobuyuki Iizuka

Yoji Ishibashi

Hiraku Ikeda

Yasutaka Komatsu

Yasuhiko Ootawara

Shozo Nakamura

Shigeru Azuhata

Hiroshi Inoue

Hironobu Kobayashi

Kazuhito Koyama

Kiyoshi Narato

Akira Nishimizu

Hidekazu Fujimura

Tadayoshi Murakami

Takashi Ohmori

Kazumi Iwai

Fumio Kato

Satoshi Tsukahara

Yasuhiko Otawara

Takahide Matsuo

Takashi Shirone

Tamio Innami

Youichi Amako

Kazuyuki Itoh

A gas insulation transformer, in the tank of which transformer an apparatus including an iron core and a coil is received and a gas is filled as an insulating and cooling medium, is provided, wherein the iron core and coil are possessed with the loss characteristics equivalent to that of a high-efficient transformer and an inert gas, the global warming coefficient of which gas is rated 1 or below, is filled in the tank as an insulating and cooling medium.

Gas insulation transformer

A gas turbine combustor is capable of reducing NOx over a whole load range of a gas turbine. The combustor comprises two burner systems. It is possible to independently control a flow rate of combustion air supplied to a burner of the respective systems and a flow rate of bypass air jetted from through a bypass air port. The air supplied to the burners is mixed with fuel in a mixing chamber and then ejected into a combustion chamber so as to form a flame. The amount of bypass air is controlled in accordance with an operation load, a humidity of air and a heating value of fuel. It is therefore possible to prevent any blow off and reduce NOx over the whole load range of the gas turbine.

Gas turbine combustor and gas turbine generating apparatus

A combustor comprises a passage area changing mechanism which relatively moves a flame holder relative to a premixed combustion nozzle in an axial direction so that the area of passage for premixed gas between an injection edge of the premixed combustion nozzle and a peripheral edge of the flame holder can be changed. Stable combustion can be maintained over a wide load range and reduction in NOx can be achieved.

Combustor and method of operating the same

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

First and second premixed burners having annular injection slots are concentrically adjacent and the injection slots are substantially aligned with each other in a longitudinal direction of the burners. A pilot burner is provided substantially in the center of the annular first premixed burner so that the injection slot of the pilot burner is substantially aligned with the injection slot of the first premixed burner in a longitudinal direction of the burner. A flame holder which forms a circulating flow of combusted gas Gh downstream of the flame holder is disposed at the downstream end of a boundary wall between the premixed burners so that the flame holder is co-used by the premixed burners. Flow rate adjusting means for adjusting the flow rate of fuel supplied to the first, second premixed burner and the pilot burner, respectively are provided. The fuel can be substantially uniformly mixed with a combustion gas. Reduction in NOx and stabilization of premixed flame can be achieved.

Combustor system for stabilizing a premixed flame and a turbine system

A fuel supply method for a gas turbine combustor having first and second stage combustion chambers. The method comprises supplying the fuel from only first stage fuel supply from the start of the gas turbine until its low output range so as to operate only the first stage combustion chamber, supplying the fuel from both first and second stage fuel supply in a high output range of the gas turbine including its maximum output so as to operate both first and second stage combustion chambers. The method makes it possible to reduce NO.sub.x without deteriorating the combustion performance by step-wise supplying a predetermined flow rate of the fuel when the second stage fuel is to be supplied and at the same time, step-wise reducing the same quantity of the fuel that is being supplied from the first stage fuel supply.

Method of supplying fuel into gas turbine combustor

Growing community of inventors

Hitachi, Japan

Noriyuki Hayashi