Kabushiki Kaisha Toshiba

Fukuo Maeda

Yasunori Iwai

Hiroaki Okamoto

Yuzo Sato

Takeshi Takahara

Masao Itoh

Atsushi Narabe

Michio Watanabe

Hiroya Sato

A gas turbine combustion system includes a cylindrical combustor, a plurality of combustion sections in an arrangement spaced apart in an axial direction of the combustor, a plurality of fuel supply lines independently connected to the combustion sections, respectively, premixed fuel supply sections respectively provided for the fuel supply lines for supplying a premixed fuel, a diffusion combustion fuel supply section for supplying a diffusion combustion fuel to the combustion sections, and a control switching over the fuel supply sections to selectively supply either one of the premixed fuel and the diffusion combustion fuel. The premixed fuel at a first combustion stage is burned while the premixed fuel of subsequent stage is ignited by a high-temperature gas generated from combustion of the premixed fuel of a preceding combustion stage.

Gas turbine staged control method

A gas turbine combustor comprises: an outer casing; a combustor inner cylinder disposed inside the outer casing; a combustion chamber formed in the combustor inner cylinder; a pilot fuel injection unit disposed to a head side portion of the combustion chamber, the pilot fuel injection unit comprising a first premixing combustion nozzle unit, a diffusing combustion nozzle unit and a second premixing combustion nozzle unit, the first premixing combustion nozzle unit being arranged at a central portion of the head side portion of the combustion chamber, the diffusing combustion nozzle unit being arranged so as to coaxially surround an outside of the first premixing combustion nozzle unit and the second premixing combustion nozzle unit being arranged so as to coaxially surround an outside of the diffusing combustion nozzle unit, respectively; and a premixing combustion chamber disposed to an outlet side of the first premixing combustion nozzle unit so as to be communicated with the combustion chamber. There may be further disposed a main premixing fuel injection unit to an outside of the second premixing combustion nozzle unit.

Gas turbine combustor with premixing and diffusing fuel nozzles

A gas turbine plant comprises a gas turbine system provided with a compressor, a gas turbine and a generator which are mounted on a common shaft and operatively connected in series to each other, a gas turbine combustor system including a gas turbine combustor composed of an outer casing and an inner cylinder accommodated in the casing, and a cooling air circulation system operatively connected to the gas turbine combustor system for circulating cooling air. A cooling passage structure is disposed along an outer peripheral surface of the inner cylinder and a circulation line is disposed for circulating cooling air in the cooling passage structure and balancing the inner pressure of the casing of the gas turbine combustor. The cooling air circulation system includes an equalizer header unit for supplying the cooling air in the cooling passage structure to the circulation line, a heat exchanger unit for re-cooling the cooling air from the equalizer header unit and a blower unit for returning the cooling air to the cooling passage structure after the re-cooling.

Gas turbine cooling system

Gas turbine multi-stage combustion system

A gas turbine combustor for a gas turbine plant comprises an outer casing and a combustor liner disposed in the outer casing, the interior of the combustor liner constituting a combustor chamber divided into a first stage of combustion area and a second stage of combustion area, disposed downstream of the first stage combustion area. The gas turbine combustor further comprises a nozzle member for supplying a first stage fuel into the first stage combustion area, a header for supplying a second stage fuel into the second stage combustion area, and a header for further supplying water or water vapor into the first stage combustion area. The nozzle member and both the headers are disposed in an end plate closing one end of the outer casing in a concentrical fashion. The flow rates of the first and second stage fuels and the water vapor are controlled by a control unit equipped with the gas turbine combustor.

Combustor for gas turbine

In a gas turbine apparatus of a premixed gas combustion type, a plurality of fuel supply systems are provided for supplying fuels to a combustion chamber of the gas turbine apparatus after the fuels are mixed with a high-pressure air, and the supply of fuels from the plurality of fuel supply systems is controlled according to programmed patterns which are predetermined for the fuel supply systems. According to a variation of the turbine load, the patterns of fuel supplies are executed in a transferred manner at a number of transfer points along a variation of the turbine load, with equal amounts of fuel reduced and increased stepwisely in the precedingly and subsequently executed patterns at each of the transfer points.

Growing community of inventors

Machida, Japan

Fukuo Maeda