Tohoku Electric Power Company, Inc.

Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Kazumasa Takata

Junichiro Masada

Satoshi Mizukami

Yoshiaki Nishimura

Tatsuo Ishiguro

Yuya Fukunaga

Masaki Satoh

Hiroki Takahashi

Norio Oogai

Souji Hasegawa

Masato Hayashi

Shinya Ishikawa

Hiroyuki Yamazaki

Tetsu Konishi

Ikuo Okada

Shunsuke Torii

Keita Takamura

Keizo Tsukagoshi

Masaki Taneike

Tomoyuki Hirata

Yoshiaki Yamaguchi

Yoshiaki Igarashi

Takuya Suzuki

Provided is a high-strength, heat-resistant, Ni-base alloy comprising Co: from 5 to 12%, Cr: from 5 to 12%, Mo: from 0.5 to 3.0%, W: from 3.0 to 6.0%, Al: from 5.5 to 7.2%, Ti: from 1.0 to 3.0%, Ta: from 1.5 to 6.0%, Re: from 0 to 2.0%, and C: from 0.01 to 0.20%. The high-strength, heat-resistant, Ni-base alloy is constituted of a Ni-based alloy, the balance of the Ni-based alloy comprising Ni and inevitable impurities. The density of the high-strength, heat-resistant Ni-base alloy is less than 8.5 g/cm.

High-strength, heat-resistant Ni-base alloy, method for producing same, and gas turbine blade

A gas turbine includes a compressor, a turbine, an extraction line, and a component introduction line. A compressed air from an intermediate compression stage of the compressor, as an extraction air, is extracted through the extraction line and is introduced to a first component configuring a portion of the turbine casing through the extraction line. The extraction air, which has passed through the first component, is introduced to a second component serving as a component configuring the turbine through the component introduction line. The second component is a low-pressure component, which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage.

Gas turbine and component-temperature adjustment method therefor

A cooling device includes a hot-part cooling system configured to guide air to a hot part of a gas turbine. The hot-part cooling system includes a compressor capable of operating independently of the gas turbine, and is configured to extract air inside a casing of the gas turbine to pressurize the air with the compressor and guide the air to the hot part of the gas turbine. The cooling device further includes a rotor cooling system configured to extract the air inside the casing of the gas turbine and guide the air to a turbine rotor, and a connecting system configured to guide the air pressurized by the compressor to the rotor cooling system while a fuel supply to the gas turbine is stopped.

Cooling device, gas turbine installation provided with same, and method for operating cooling device

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

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

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Yokohama, Japan

Kazumasa Takata