Hitachi, Ltd.

Babcock-hitachi Kabushiki Kaisha

The Tokyo Electric Power Company, Incorporated

Babcock-hitachi K.k.

Hitachi Babcock Kabushiki-kaisha

Tadayoshi Murakami

Shigeru Azuhata

Michio Kuroda

Hironobu Kobayashi

Norio Arashi

Kiyoshi Narato

Kenichi Sohma

Masayuki Taniguchi

Yoji Ishibashi

Yasuo Yoshii

Tooru Inada

Kazuyuki Ito

Kazuhiko Kawaike

Hideo Kikuchi

Stephen M Masutani

Yasuo Iwai

Nariyoshi Kobayashi

Yukio Hishinuma

Kazutoshi Higashiyama

Hiroshi Miyadera

Susumu Yoshioka

Tomihisa Ishikawa

Yoshikazu Moritomo

Satoshi Tsukahara

Noriyuki Hayashi

Shigekazu Nishimoto

Fumio Koda

Kazuyuki Itoh

Masaaki Shiga

Tooru Inata

Isao Koyama

Tatsuzou Enomoto

Kenshi Kobayashi

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

The present invention has an object to provide a gas turbine combustor which is able to effect stable combustion in a wide range of fuel flow rate. A burner 1 is provided with fuel nozzles 31 and 32. When a fuel flow rate is small, diffusion flame is formed with fuel supplied from the nozzle 31 with a ring-shaped flame stabilizer 11. Next, fuel is supplied from the nozzle 32 to mix with air, reach to the flame stabilizer 11 and be held by the diffusion flame already formed, whereby stable premixed flames are formed in the flame stabilizer 11 from a range of low fuel air ratio. Further, when flame is propagated from the burner 1 to the burner 2, a fuel air ratio at the outer periphery side of the burner 1 is locally raised by the fuel supplied from the nozzle 31, whereby the combustion stability can be raised in a wide range of fuel flow rate and propagation of flame to adjacent burners becomes easy.

Gas turbine combustor and gas turbine

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 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 lithium aluminate powder having a large specific surface area can be produced by contacting a raw material powder of lithium aluminate with water singly or in the presence of an organic solvent having one or more hydroxyl groups to form a hydrate, followed by dehydration with heating.

Process for producing lithium aluminate powder having large specific

Combustor for burning a premixed gas

A low-NOx boiler comprises a burner for burning gaseous fuel, heat transfer pipes heating water by combustion heat of the burner to generate steam and having a passage through which water flows, a steam drum communicating with the heat transfer pipe and accumulating the steam from the heat transfer pipe, and an exhaust gas duct located in the furnace to exhaust combustion gas generated by combustion of gaseous fuel outside of the boiler. The boiler further comprises unburnt gas burner in the exhaust gas duct for burning unburnt content in the combustion gas flowing in the duct. The unburnt gas burner includes a nozzle for injecting premixture flow of fuel and combustion air and flame holding plate located near the downstream side of the outlet of the nozzle to interrupt the premixture flow to form a circulating flow on downstream side of the flame holding plate. As gaseous fuel and air are mixed in advance and a flame is formed, the flame length can be shortened. Furthermore, the flame holding plate enables to reduce NOx generated. Unburnt gas burner provided in the exhaust gas duct makes it possible to notably reduce the concentration of NOx discharged to the outside of the system.

Low NOx boiler

A gas turbine combustor comprises a combustion chamber, a premixing chamber in which hydrocarbon fuel and air are premixed, a nozzle with swirler for swirling and injecting the premixed fuel and air into the combustion chamber, to effect premixed combustion, and a fuel nozzle projecting into the combustion chamber and adapted to inject fuel at region wherein the premixed combustion is completed, so as to effect low air-ratio diffusion combustion thereby to produce reducing substance. NOx produced by the premixed combustion is reduced by reducing reaction with the reducing substances, so that the NOx concentration in the combustion gas is reduced. The combustor further includes an after-air ports on a peripheral wall defining the combustion chamber to effect combustion of unburnt substances.

Gas turbine combustor and a method of combustion thereby

A low NOx burning method and apparatus wherein a low air ratio flame burned with an amount of air less than an amount of air in a theoretical air ratio required for burning fuel perfectly is formed, and combustibles discharged from the low air ratio flame are burned at a trailing stream of the low air ratio flame while supplying air. The low air ratio flame is a premixing flame burned by premixing the fuel and air, and combustion of the premixing flames is maintained in the vicinity of the premixing flame. In this way, the generation of the NOx during the burning can be greatly decreased, and the required apparatus can be small-sized.

Low NOx burning method and low NOx burner apparatus

A plurality of catalyst assemblies each have a plurality of sheet catalysts which are arranged in parallel to each other with distances thereby to define a plurality of gas passages. The catalyst assemblies are stacked in a catalytic reactor so that the width direction of the sheet catalysts of one of the catalyst assemblies will traverse the width direction of the sheet catalysts of each of the immediately adjacent assemblies, whereby leading edges of the sheet catalysts of each assembly are exposed to a gas to be treated rising upward in the gas passages.

Catalytic reactor

A catalytic reaction apparatus for carrying out a gaseous reaction of a mixture of a gas to be treated, and a gaseous substance with which it reacts at an accelerated rate of reaction, which comprises a catalyst packed bed provided in a vertical plane at a predetermined angle of turning from the flow direction of the gaseous mixture in the catalytic reaction apparatus. Deviation of flow of the gaseous mixture can be effectively prevented by the present arrangement of the catalyst packed bed.

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Hitachi, Japan

Tadayoshi Murakami