Hitachi, Ltd.

Hitachi Kizai Kogyo Co. Ltd.

Michio Kuroda

Yoji Ishibashi

Isao Sato

Shigeru Azuhata

Nobuyuki Iizuka

Tadayoshi Murakami

Takashi Ohmori

Masayuki Taniguchi

Hironobu Kobayashi

Fumio Kato

Katsukuni Hisano

Kenichi Sohma

Kiyoshi Narato

Norio Arashi

Seiichi Kirikami

Shozo Nakamura

Hiroshi Inoue

Ryoichiro Oshima

Noriyuki Hayashi

Shigeyuki Akatsu

Takashi Hashimoto

Fumiyuki Hirose

Hiraku Ikeda

Yoshihiro Uchiyama

Haruo Urushidani

Tooru Inada

Kazuhiko Kumata

Satoshi Tsukahara

Yasuo Yoshii

Osamu Arai

Kazuhiko Kawaike

Kazuhito Koyama

Akira Arai

Shigehisa Sugita

Katsuo Wada

Kiyoshi Namura

Kazuyuki Ito

Seiichiro Sakaguchi

Yoshiaki Yamazaki

Akira Shimura

Yasutaka Komatsu

Nobuo Shimizu

Yoshimitsu Minakawa

Hiroshi Inose

Stephen M Masutani

Yasuo Iwai

Yasuhiko Ootawara

Kazuyuki Itoh

Tetsuo Sasada

Hajime Toriya

Yoshiki Noguchi

Hidekazu Fujimura

Zensuke Tamura

Kazumi Iwai

Yoshikazu Moritomo

Yasuaki Akatsu

Tsuguaki Koga

Yasuhiko Otawara

Hideo Kikuchi

Satoshi Ninomiya

Shoei Takahashi

Isao Saito

Minoru Takaba

Tamio Innami

Yoshiharu Nakayama

Yorihide Segawa

Tetsu Imai

Akira Ishida

Akio Sohma

Takamitsu Taki

Koji Shiina

Tutomu Iwasaki

Daizo Morimoto

Kojiro Kaneko

Yasuaki Akatu

Tadashi Kurokawa

A gas turbine combustor has a premixing burner for jetting out a premixed gas of fuel and air. A stabilizer forms a circulation of combustion gas generated by combustion of the premixed gas at the downstream side of the stabilizer to stabilize flame formed by the combustion of the premixed gas. Before the operation of the combustor, a relationship between a temperature of the stabilizer and combustion conditions of the premixed gas is checked. Thereafter during operation of the combustor, the temperature of the stabilizer is measured during combustion and the combustion conditions are checked according to only the measured temperature of the stabilizer and the aforesaid relationship. The stabilizer has a heat receiving surface at the most downstream side thereof. The temperature of a portion of the stabilizer around the heat receiving surfaces measured to allow an accurate assessment of the combustion conditions.

Stabilizer for gas turbine combustors and gas turbine combustor equipped

A plurality of turbulence promotors (11) are arranged on a surface of a stabilizer (11) comprising a stabilizer portion (14) contacting combustion gas and support portion (15) for rectifying flow except for a heat receiving surface (13) contacting with combustion gas to promote heat transfer from the stabilizer to an air fuel flow. The distance between the turbulence promotor closest to the heat receiving surface (13) and the heat receiving surface is at least 4 times the height of said turbulence promotor to prevent back fire due to provision of the turbulence promotor.

A camera includes a plurality of photosensors disposed on an imaging surface. The photosensors separately output respective photodetection signals, and are grouped into a plurality of photosensitive units each including at least two of the photosensors. The photosensors of each of the photosensitive units have respective detection wavelength ranges which do not overlap one another. The photodetection signals outputted from selected ones of the photosensors of each of the photosensitive units are used in performing spectrum analysis. R (red), G (green), and B (blue) signals are synthesized from the photodetection signals outputted from the photosensors of each of the photosensitive units and are used in displaying an ordinary color image.

Camera, spectrum analysis system, and combustion evaluation apparatus

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 gas turbine combustor of the pre-mixed combustion system in which the pre-mixed fuel and the air are combusted. The gas turbine combustor comprises main cylindrical nozzles provided in the end wall on the upstream side of a cylindrical combustion chamber, auxiliary nozzles formed to surround the main nozzles, a main pre-mixed gas supply for supplying a pre-mixed gas to the main nozzles, and an auxiliary pre-mixed gas supply for supplying a pre-mixed gas having an fuel/air ratio smaller than that of the main pre-mixed gas to the auxiliary nozzles, and wherein it is allowed to stably burn a lean pre-mixed gas having an fuel/air ratio of greater than 1 from a low-load condition through and up to a high-load condition of the gas turbine.

Gas turbine combustor of the completely premixed combustion type

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

Method of burning a premixed gas and a combustor for practicing the method. A jet of the premixed gas is burnt from an inside to an outside of the jet to form a premix flame. A burned gas is mixed into the premixed gas from the outside of the jet. The burned gas is produced when premixed gas is burned.

Method of burning a premixed gas in a combustor cap

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 method for controlling a gas turbine combustor which comprises nozzles for injecting fuel into a combustor and which serves to combust the fuel with air in a combustion chamber so as to rotatively drive a gas turbine by combustion gas compressed as a result of combustion of a fuel, wherein the ratio of a flow rate of fuel supplied into the combustor to a flow rate of air supplied into the combustor is changed in accordance with at least one of the states of fuel, air and rotational frequency of the turbine.

Method for controlling gas turbine combustor

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

Combustor for burning a premixed gas

A combustor includes a first premixture supply device provided in a central portion of a combustion chamber disposed generally concentric with a combustion cylinder, and a second premixture supply means provided adjacent to an outer periphery of the first premixture supply device. The first premixture supply device is operable when the combustor is under a high load, and the second premixture supply device is operable when the combustor is under a low load. A method of operating a combustor is also proposed wherein the combustor comprises a combustion cylinder having a combustion chamber therein and a premixture supply device provided on one side of the combustion cylinder for supplying a combustible mixture to the combustion chamber. The premixture supply device comprising at least two inner and outer premixture supply devices. The outer premixture supply device is operable in a low-load range of the combustor while the inner and outer premixture supply devices are operable in a high-load range of the combustor at above a predetermined load. The first and second premixture supply devices include first and second burners, respectively. The first and second burners are operated in such a manner that the ratio of the load borne by the first burner to the load borne by the second burner is 1:1 in the high-load range.

Combustor and method of operating same

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

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Hitachi, Japan

Michio Kuroda