Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Shohei Numata

Osami Yokota

Tetsuma Tatsumi

Tomomi Koganezawa

Yoshitaka Hirata

Kenji Miyamoto

Takanori Shibata

Koichi Nishida

Shohei Yoshida

Satoshi Takiguchi

Yasuhiro Wada

Akinori Hayashi

Susumu Nakano

Hidefumi Araki

Yoshitaka Terada

Yasuhiro Akiyama

Keita Yunoki

Tomoki Uruno

Shota Igarashi

Masataka Hidaka

Naoto Fujiwara

Hiroaki Nagahashi

Testuma Tatsumi

Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path. An installation area of the first flow path group and an installation area of the second flow path group partially overlap in the flow direction of the combustion gas by a predetermined overlap amount, and the overlap amount is set large for a portion where a shape change of the transition piece is relatively large, as compared with a portion where the shape change of the transition piece is relatively small.

Transition piece, combustor, and gas turbine engine

A transition piece includes a first flow passage group formed by arranging a plurality of intra-wall flow passages, a second flow passage group, and a plurality of dilution holes that penetrate a plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the second flow passage group.

A combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.

Combustor, gas turbine

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

A thermal power generation system includes a combustor burning oxygen and fuel with supercritical CO, a turbine driven by the supercritical COand water vapor fed from the combustor, a low-pressure supercritical COstorage storing low-pressure supercritical COfrom the turbine, a compressor compressing the low-pressure supercritical CO, a high-pressure supercritical COstorage storing high-pressure supercritical COfrom the compressor, and a high-pressure supercritical COfeeder supplying between the high-pressure supercritical COstorage and the combustor, in which the high-pressure supercritical COfeeder supplies the high-pressure supercritical COto the combustor at a constant pressure. Thus, the thermal power generation system can perform adjustment of an electric power supply required to use unstable renewable energy sources such as solar and wind power, can achieve high efficiency power generation with high temperature working fluid, and can reduce emissions of environmental load substances such as NOand CO.

Thermal power generation system and method using supercritical carbon dioxide as working fluid

An object of the present invention is to provide a gas turbine combustor that can suppress an increase in pressure loss while improving product reliability. The gas turbine combustor includes a combustor liner, an air transfer casing installed on the outer circumference of the combustor liner, the combustor liner and the air transfer casing defining an annular passage therebetween adapted to allow a heat-transfer medium to flow therethrough, and a plurality of vortex generating devices disposed on an inside surface of the air transfer casing, the vortex generating devices generating longitudinal vortices each having a rotational axis extending in a flow direction of a heat-transfer medium. The plurality of vortex generating devices are arranged in paired manner, with each pair of devices generating vortices having rotational directions opposed to each other.

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Yokohama, Japan

Shohei Numata