Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Tohoku Electric Power Company, Inc.

Mitsubishi Power, Ltd.

Mitsubishi Denki Kabushiki Kaisha

Ricoh Company, Ltd.

Satoshi Mizukami

Masaki Kato

Junichiro Masada

Kazumasa Takata

Tatsuo Ishiguro

Tetsu Konishi

Yuya Fukunaga

Yoshiaki Nishimura

Satoshi Hada

Masaki Satoh

Hiroki Takahashi

Norio Oogai

Souji Hasegawa

Masato Hayashi

Hiroyuki Yamazaki

Taiki Kinoshita

Saki Matsuo

Yoshiaki Yamaguchi

Satoshi Tanimura

Shinji Akamatsu

Satoshi Takiguchi

Shinya Ishikawa

Shunsuke Torii

Yoshitaka Uemura

Yasumasa Kunisada

Ryozo Tamura

Kenji Sato

Shigemi Mandai

Masaru Shinkai

Yoshikazu Akiyama

Masamitsu Kuwabara

Keisuke Matsuyama

Yoshinori Wakita

Kiyoshi Fujimoto

Kenta Taniguchi

Sosuke Nakamura

Masanori Yuri

Kiyoshi Yamaguchi

Takahiko Kuroda

Kotaro Miyauchi

Yasuro Sakamoto

Hiroaki Kishida

Hikaru Kurosaki

Tomoyuki Hirata

Yasuo Miyahisa

Hikaru Katano

Masaki Mitani

Takaaki Hase

Hiroshi Makigano

Wataru Kugimiya

David Allen Flodman

Yuichiro Kimura

Osamu Machida

Takuya Suzuki

Yoshiaki Igarashi

Tomoharu Fujita

Toshio Takanezawa

A tail pipe () comprises: a pipe (); an acoustic attenuator () that forms an acoustic space (Ss) on the outer peripheral side of the pipe (); and a cooling air jacket () that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (). The pipe () has: a first air flow path () that is formed between the outer peripheral surface () and the inner peripheral surface (); and an acoustic hole () that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (). The first air flow path () has: an inlet () that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (); and an outlet () that faces into the acoustic space (Ss) and guides the air passing through the first air flow path () into the acoustic space (Ss).

Transition piece, combustor, gas turbine, and gas turbine equipment

A stator blade including a blade body, a first insert, a second insert, and an end cover. The blade body has a first blade air passage and a second blade air passage extending in the blade height direction within the blade body. Each passage has an open end on a blade-height second side. The first insert and the second insert have tubular outer peripheral plate portions. A plurality of impinge holes are formed in the outer peripheral plate portion. The tube height opening side of the outer peripheral plate portion in the tube height direction is open. The outer peripheral plate portion of the first insert is disposed in the first blade air passage such that cooling air flows into the outer peripheral plate portion from the opening of the first insert. The outer peripheral plate portion of the second insert is disposed in the second wing air passage.

Stator blade and gas turbine comprising same

A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Turbine blade

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

Turbine blade and method for manufacturing the turbine blade

A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, a shroud disposed at an end of the airfoil, the end being a radial end along a radial direction of the turbine, the shroud comprising a shroud main body and a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein. A cooling air is caused to flow inside the shroud edge passage to cool the shroud edge, and after cooling the shroud edge, the shroud main body is cooled by using the cooling air which has flowed inside the shroud edge passage.

Cooling method and structure of vane of gas turbine

A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying: where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.

Resonant sound absorbing device of gas turbine combustor, gas turbine combustor including the same, and gas turbine

A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.

Gas turbine combustor transition piece including inclined surface at downstream end portions for reducing pressure fluctuations

A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.

Cylinder for combustor, combustor, and gas turbine

A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.

Combustor and gas turbine

A gas turbine combustor comprising a plurality of cooling air passages (A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (A) being disposed in a wall portion () side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (A) are divided via a passage transition groove portion () into upstream cooling air passages (A) disposed closer to bled pressurized air inlet holes () and downstream cooling air passages (A) disposed closer to bled pressurized air outlet holes (), and center lines (C) of the upstream cooling air passages are non-collinear with center lines (C) of the downstream cooling air passages.

Combustor cooling structure

A gas turbine equipped with a compressor, a combustion chamber and a turbine is further equipped with: a pressurizing device for taking a portion of the compressed air compressed by the compressor, and pressurizing the compressed air; a combustion chamber cooling line for cooling the combustion chamber using the pressurized compressed air; a temperature regulating line for regulating the temperature of a stationary member of a blade ring or the like of a turbine by using the pressurized compressed air; a combustion chamber supply line through which the compressed air flows from the pressurizing device to the combustion chamber cooling line; a turbine supply line through which the compressed air flows from the pressurizing device to the temperature regulating line; a heater for heating the compressed air, provided in the turbine supply line; and a control device capable of controlling the heater.

Gas turbine, gas-turbine control device, and gas turbine operation method

Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device () connected to a branching channel () branching from the discharge side of a compressor () and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (); a temperature-control-medium supply channel () that guides compressed air pressurized at the pressuring device () to a turbine-cooling-medium channel () provided in stationary components of a turbine (); and a temperature-control-medium return channel () that guides the compressed air that has passed through the turbine-cooling-medium channel () to the discharge side of the compressor () such that the flows are combined, and the pressurizing device () is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (). The pressurizing device () is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine ().

Gas turbine and operating method thereof

In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.

Cooling structure for recovery-type air-cooled gas turbine combustor

Growing community of inventors

Tokyo, Japan

Satoshi Mizukami