Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Petroleum Energy Center

Toshifumi Sasao

Hirokazu Takahashi

Hiroshi Inoue

Akinori Hayashi

Yoshitaka Hirata

Isao Takehara

Shouhei Yoshida

Tomoya Murota

Shohei Yoshida

Nariyoshi Kobayashi

Kazuyuki Ito

Shinichi Inage

Yasuhiro Wada

Tetsuo Sasada

Hidetaro Murata

Koji Nishida

Hiromi Koizumi

Tatsuya Sekiguchi

Nobuyuki Hokari

Osami Yokota

Takeo Saito

Tsunemasa Nishijima

Takeo Saitou

Shinsuke Kokubo

Youtarou Kimura

A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.

Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages

A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.

Gas turbine combustor including burner having plural gaseous fuel manifolds

An object of the invention is to provide a reliable gas turbine combustor that can provide lowered NOx and combustion stability. The gas turbine combustor includes a combustion chamber to which fuel and air are supplied; a first burner located on the upstream side of the combustion chamber, the first burner jetting fuel into the combustion chamber and jetting air into the combustion chamber in a swirling manner; a plurality of second burners arranged around the first burner and supplying a premixed gas of air and fuel to the combustion chamber; an annular bulkhead disposed between the first burner and the second burners and having an inclined surface formed to broaden toward the downstream side of the combustion chamber; and a plurality of air jet ports formed in the inclined surface of the annular bulkhead and adapted to jet air into the combustion chamber.

Gas turbine combustor and fuel supply method used for the same

A combustor and a combustion method for the combustor, which can suppress backfire and ensure stable combustion. The combustor comprises a mixing-chamber forming member for forming therein a mixing chamber in which air for combustion and fuel are mixed with each other, and a combustion chamber for burning a gas mixture mixed in the mixing chamber and producing combustion gases. A channel for supplying the air for combustion to the mixing chamber from the outer peripheral side of the mixing-chamber forming member is provided inside the mixing-chamber forming member. The fuel and the air are premixed in the channel, and a resulting premixed gas mixture is supplied to the mixing chamber.

Combustor comprising a member including a plurality of air channels and fuel nozzles for supplying fuel into said channels

A combustor comprises a liquid fuel nozzle for injecting liquid fuel to a combustion chamber, and an air supply nozzle disposed around the liquid fuel nozzle and injecting air. The air supply nozzle is disposed such that air is injected from the air supply nozzle in a direction toward an axis of the liquid fuel nozzle. A space is formed around an outlet of the liquid fuel nozzle, through which the liquid fuel is injected from the liquid fuel nozzle to the combustion chamber, upstream of a distal end of the outlet in a direction in which the liquid fuel is injected. Carbonaceous deposits on surrounding surfaces of the outlet of the liquid fuel nozzle can be suppressed regardless of the operating conditions of a combustor.

Combustor, gas turbine combustor, and air supply method for same

Combustor and combustion method for combustor

In a method for producing gas turbine fuel through the step of modifying heavy fuel oil with the use of an asphaltene-insoluble solvent, the utilization factor of the heavy fuel oil usable as gas turbine fuel is increased by making asphaltene selectively removable. A solvent having a specific inductive capacity in the range of 1.4 to 2.0 is used as the asphaltene-insoluble solvent. In particular, water controlled in temperature and pressure so as to have a specific inductive capacity in the above range is used as the asphaltene-insoluble solvent. By using such a solvent, an asphaltene component contained in the heavy fuel oil can be selectively removed and power generation can be performed while utilizing 95% or more of the heavy fuel oil.

Method for producing gas turbine fuel, and method and system for generating electric power by gas turbine

A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular time before outputting of an ignition command for a combustor and the exhaust temperature detected after the outputting of the ignition command, and determining that the combustor is ignited, when the calculated difference is not less than a predetermined value. As an alternative, the method includes a step of determining that the combustor is ignited, when a change amount or rate of the exhaust temperature exceeds a predetermined value in a predetermined period from the outputting time of the ignition command.

Ignition detecting system and method for gas turbine

A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.

Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor

Growing community of inventors

Mito, Japan

Toshifumi Sasao