Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Tetsuma Tatsumi

Masayuki Taniguchi

Osami Yokota

Shohei Numata

Akinori Hayashi

Tomomi Koganezawa

Shohei Yoshida

Hirofumi Okazaki

Yasuhiro Wada

Kazuki Abe

Akihito Orii

Masataka Hidaka

Tsuyoshi Shibata

Yoshiharu Hayashi

A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed. In a gas turbine combustor including a diffusion burner and a premixed burner, the premixed burner is configured with a burner liner that surrounds the diffusion burner; a burner casing that surrounds the burner liner; a plurality of vanes that separate a cylindrical space between the burner liner and the burner casing into a plurality of premixers arranged side by side in a circumferential direction; a plurality of premixed fuel nozzles that inject a premixed fuel to the premixers; at least one thermometer installed to be buried in one of the vanes, and the like, and in a case in which a detection value of the thermometer exceeds a corresponding set value, an opening of each of premixed gas control valves is reduced and an opening of a diffusion gas control valve is increased in such a manner that a sum of flow rates of fuels supplied to the diffusion burner and the premixed burner remains unchanged.

Gas turbine combustor, gas turbine, and control method for gas turbine combustor

Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object. The heat-transfer device for facilitating heat exchange between combustion air (heat transfer medium) flowing along an outer surface of a combustor liner (heat transfer object), and the combustor liner, the heat-transfer device including at least one longitudinal vortex generating device protruding toward a annular passage (flow passage) of the combustion air and formed to generate a longitudinal vortex E with a central axis in a flow direction of the combustion air, and stir the combustion air flowing in the annular passage; and at least one radiator fin provided in a region A on the outer surface of the combustor liner, the region A being where a flow of the vortex E, on a swirling plane thereof, that are generated by the vortex generating device is directed from a side of the combustor liner, toward a side of a flow sleeve, the fin exchanging heat with the combustion air stirred by the vortex generating device.

Heat-transfer device and gas turbine combustor with same

A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.

Gas turbine combustor

A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.

Gas turbine combustion liner with triangular heat transfer element

A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).

Cooling structure for gas turbine combustor liner

Provided are a device and a method for manufacturing a semi-carbonized fuel of a biomass that does not require an external heat source and is capable of suppressing adhesion of tar, condensed water, or the like to a pipe. The device includes a drying device for heating and drying a biomass, a pyrolysis device for decomposing the dried biomass, and a combustion device for supplying heat to the drying device and the pyrolysis device. The pyrolysis device is supplied with a part of a combustion exhaust gas generated in the combustion device, directly mixes the supplied combustion exhaust gas and the biomass to heat and pyrolytically decompose the biomass, and supplies a mixed gas of a generated pyrolysis gas and the combustion exhaust gas to the combustion device. The combustion device is supplied with an air for combustion, combust the supplied mixed gas, and generate the combustion exhaust gas.

Growing community of inventors

Yokohama, Japan

Tetsuma Tatsumi