Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Masanori Yuri

Vincent Laurello

Keita Takamura

Satoshi Hada

Shinya Hashimoto

Tanehiro Shinohara

Kouichi Akagi

Hidekazu Uehara

Shunsuke Torii

Takashi Nakano

Shin Nishimoto

Susumu Wakazono

Toshishige Ai

Tomoko Hashimoto

Kouichi Ishizaka

Ronald Takahashi

Yasuoki Tomita

Kiyoshi Suenaga

Satoshi Tanimura

Eisaku Ito

Masamitsu Kuwabara

Keisuke Matsuyama

Sunao Aoki

Hiroki Fukuno

Junichiro Masada

Keizo Tsukagoshi

Satoshi Mizukami

Yasuro Sakamoto

Hiroaki Kishida

Yutaka Ozawa

Zenichi Yoshida

Masato Araki

Tetsuya Shimmyo

Yutaka Kawata

Nobuhiro Kunitake

Naoya Tatsumi

Shingo Yamasue

Masahiko Toyoda

Takahiro Ohta

Charles Ellis

Yuji Komagome

Shin Koga

Koji Takeshita

Keita Fujii

Mitsuhiro Noguchi

Akihiro Kawaguchi

Setunori Sakakibara

Hidehiko Nakane

Hada Satoshi

According to an embodiment, a turbine casing comprises a cooling air supply unit configured to supply a cooling air to an interior space of a casing of a gas turbine, and the cooling air supply unit includes: a first supply unit disposed in an upper half of the casing so as to face a first region and configured to supply the cooling air to the first region, where the first region is a region on a radially outer side of a plurality of combustors arranged annularly around a rotor; and a second supply unit disposed so as to face a second region and configured to supply the cooling air to the second region, where the second region is a region on a radially inner side of the plurality of combustors.

Turbine casing, gas turbine, and method for preventing deformation of turbine casing

An axial-direction passage, a forced vortex passage, a first blade array passage, and a second blade array passage are formed in a rotor shaft of a turbine. Cooling air from an air extraction port of a compressor flows through the axial-direction passage which extends in an axial direction. The forced vortex passage is connected to the axial-direction passage and extends outwards in the radial direction relative to an axial line from a connecting portion between the forced vortex passage and the axial-direction passage. The first blade array passage is connected to an end portion on the outer side in the radial direction of the forced vortex passage and guides cooling air to a first blade row among a plurality of blade rows. The second blade array passage is connected to an end portion of the forced vortex passage and guides cooling air to a second blade row.

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 rotor shaft has: an inlet flow passage through which gas inside a gas compression flow passage flows into an outer cavity of a downstream-side cavity group; a radial flow passage that provides communication between the outer cavity and an axial communication cavity of the downstream-side cavity group; an axial flow passage that provides communication between the axial communication cavity of the downstream-side cavity group and the axial communication cavity of an upstream-side cavity group; another radial flow passage that provides communication between the axial communication cavity and the outer cavity of the upstream-side cavity group; and an outlet flow passage through which the gas inside the outer cavity of the upstream-side cavity group flows out into the gas compression flow passage.

Compressor rotor, compressor, and gas turbine

A turbine vane () includes: a vane body (); a plate-like inner shroud () provided at a radially inner end of the vane body (); and a plate-like outer shroud () provided at a radially outer end of the vane body (). The vane body () includes a serpentine channel () which is formed so as to meander inside the vane body () in the radial direction and through which a cooling medium flows. The inner shroud () includes a cooling path () which has one end open at the downstream end side of the serpentine channel () and the other end open at a trailing edge (D) of the inner shroud () and through which the serpentine channel () communicates with the outside of the inner shroud ().

Turbine vane, turbine, and turbine vane modification method

The amount of cooling air (cooling medium) can be reduced, and low-temperature cooling air is prevented from being blown out through film cooling holes. Part of a cooling medium impingement-cooling an inner circumferential surface of a blade main body located on a ventral side further impingement-cools the inner circumferential surface of the blade main body located on a dorsal side and is blown out through film cooling holes in the blade main body that are located on the dorsal side.

Turbine blade

Provided is a gas turbine blade capable of improving the heat-conducting capacity of a serpentine channel. In a gas turbine blade including a serpentine channel in which a plurality of cooling channels, extending from the base end side to the distal end side of the blade, are provided from the leading edge to the trailing edge of the blade, at least two of these cooling channels being connected in a folded manner at the base end or distal end, the serpentine channel is formed such that the channel cross-sectional area becomes sequentially smaller from the cooling channel provided at the extreme upstream side of the serpentine channel to the cooling channel provided at the extreme downstream side.

Gas turbine blade and gas turbine having the same

A gas turbine includes a shaft directional passage provided to a rotating member that rotates along a central axis of a rotor, which is a rotating axis of the rotating member, about the central axis, or a rotating axis of the rotating member, and in which cooling air flows along a direction of the rotating axis of the rotor, a plurality of radial directional passages provided in a circumferential direction of the rotating member, and compressing the cooling air by being provided outwardly from the center of the rotor, in which one end of each of the radial directional passages is communicated with the shaft directional passage and the other end is communicated with exterior of the rotating member.

The present invention includes an introducing passage that is provided within a turbine stationary blade fixed within a turbine casing and that communicates an interior of the turbine casing with an exterior thereof; a nozzle that is provided in an inner circumference of the turbine stationary blade in a manner that the nozzle communicates with the introducing passage and that includes an outlet facing the opening of the rotor cavity and a swirler at the outlet; and a pressurizing passage that communicates a cooling passage with a rotor cavity. In this arrangement, the outlet of the nozzle and the connecting opening of the pressurizing passage are arranged so that distances of the outlet and of the connecting opening from the central axis line in the radial direction of the rotor are the same distance r.

Gas turbine and cooling air supply structure thereof

In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.

An outer shape of a section in the longitudinal direction at a leading edge of the strut is an aerofoil whose thickness is gradually increased along a flow direction of the combustion gas to prevent reduction of turbine efficiency caused by a shock wave generated at the strut of the exhaust diffuser.

An object of the present invention is to provide a shaft seal which reduces the leakage of gas from the high pressure side to the low pressure side, and has excellent corrosion-resistance, and a gas turbine which is equipped with the shaft seal; in order to achieve the object, the present invention provide a shaft seal comprising a plurality of flexible thin plates having width in the axial direction of a rotary shaft, tips thereof sliding against a peripheral face of said rotary shaft, and outer peripheral bases thereof being secured to a casing side maintaining a gap therebetween, said thin plates being laminated in the peripheral direction of said rotary shaft, enabling the outer periphery of said rotary shaft to be sealed, an acute angle being formed between the thin plates and the peripheral face of said rotary shaft; and a low pressure side side-plate and a high pressure side side-plate which are provided on both sides of said thin plates in the axial direction of said rotary shaft, wherein it further comprises a gas pressure adjusting mechanism, which when said thin plates are viewed cross-sectionally along an imaginary plane which is perpendicular to the direction of their width, the face of each thin plate which faces the rotary shaft is deemed a bottom face and the rear side is deemed a top face, and gas pressure from said high pressure side side-plate to said low pressure side side-plate is applied to said thin plates, ensures that the gas pressure applied to said bottom faces is higher than the gas pressure applied to said top faces at a given point along said cross-sectional face of said thin plates, and a gas turbine comprising such shaft seal.

Shaft seal and gas turbine

Bleeding is operated by annularly providing plural stationary blades at an interior side of a vehicle; annularly providing plural moving blades around rotor disk adjacent to stationary blades; providing plural stage units comprising the stationary and moving blades; introducing bleed air into each stage unit from a compressor; supplying bleed air extracted from a final stage of the compressor into a first stage unit; and supplying bleed air extracted from compressed air which has not yet arrived at a final stage unit of the compressor.

Gas turbine and bleeding method thereof

The shaft seal structure is based on a leaf seal that includes springs, disposed between the stator blades and the leaf seal ring, to force the leaf seal ring away from the rotation shaft, and pressure guiding grooves for guiding the fluid pressure, through a boundary of planar plates, to a space between the outer peripheral surface of the leaf seal ring and the inner peripheral surface of the stator blade. Also, a turbine may be provided with the leaf seal so as to reduce gas leakage from the high-pressure-region to the low-pressure-region as well as to control the frictional wear between the planar plates and the rotation shaft.

Shaft seal structure and turbine

An axial-flow turbine has an exhaust diffuser including a hub-side tube and a tip-side tube. In the exhaust diffuser, front struts and rear struts are placed to cross a flow of working fluid. A wake generated behind the front strut diverts from the rear strut and passes through a gap between a pair of the rear struts. Otherwise, a wake generated behind the front strut hits against the front face of the rear strut. The front struts are equal to or multiple of the rear struts in number.

Exhaust diffuser for axial-flow turbine

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Takasago, Japan

Masanori Yuri