Hitachi, Ltd.

The Kansai Electric Power Co., Inc.

Kazuhiko Kawaike

Takashi Ikeguchi

Shinya Marushima

Manabu Matsumoto

Katsutoshi Nii

Masaru Sekihara

Takashi Machida

Shunichi Anzai

Satosi Uno

Isao Takehara

Masami Noda

Hiroo Hiroyama

Shigeru Azuhata

Michio Kuroda

Tetsuo Sasada

Tomoaki Inoue

Tadayoshi Murakami

Kazuyuki Ito

Masaaki Nakano

Kosho Ishizaki

Sueo Akashi

Jun Matsubayashi

Hiroshi Inoue

Tomomi Koganezawa

Nobuyuki Iizuka

Takeshi Kudo

Yuji Yamamoto

Haruo Urushidani

Nobuaki Kizuka

Katsuo Wada

Masayuki Urashin

Kengo Hasegawa

Akira Saruta

Seishi Watahiki

Mitsutaka Shizuya

Minetoshi Izushi

Hisao Inoue

Shinji Sonoda

Osamu Sugimoto

Kooji Aizawa

Kenzo Kajiwara

Ichiro Hitomi

Sadao Umezawa

Motomichi Doi

Yoshiaki Chiba

Teiji Horita

Ryoichi Nakashima

Eiichi Okuyama

Tomo Sato

Shin'ichi Higuchi

Koozi Aizawa

Motoyuki Ishikawa

Satoshi Uno

The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed at ends of the transition outer duct on both sides nearer to the combustor liner and the turbine, and the transition outer duct is formed as an extraction flow passage for extracting the cooling fluid having flown in through the inlet openings to a recuperator. A partition member is also provided to prevent the fluid in the main housing and the fluid in the combustor outer casing from mixing with each other.

Gas turbine combustor

An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Coolant recovery type gas turbine

A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.

Operational reliability of a gas turbine is improved by suppressing the thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs. Gap portions are formed between a region on the rotor shaft center portion side of the discs facing the spacers and spacers adjacent thereof. Contact surfaces are formed which contact on both a region on the rotor peripheral side of the discs facing the spacers and adjacent spacers thereto. Furthermore, a third flow path leading fluid to the above-mentioned gap portions is provided.

A high efficiency coolant collection type gas turbine is obtained by forming coolant supply and collection flow paths for moving blades in a more outer peripheral side of a gas turbine rotor than a hub, supplying the coolant supplied from a shaft end into the moving blades through the supply flow path, collecting the coolant after cooling into a combustion chamber side, supplying air extracted from a compressor to cool moving blades of a downstream side stage or a rotor outer wall through slits formed from a turbine rotor central portion to the hub, reducing rotor thermal stress and a pressure loss of the coolant flow paths and cooling a high stage side of a compressor rotor.

Gas turbine with turbine blade cooling

A gas turbine combustor has a premixing burner for jetting out a premixed gas of fuel and air. A stabilizer forms a circulation of combustion gas generated by combustion of the premixed gas at the downstream side of the stabilizer to stabilize flame formed by the combustion of the premixed gas. Before the operation of the combustor, a relationship between a temperature of the stabilizer and combustion conditions of the premixed gas is checked. Thereafter during operation of the combustor, the temperature of the stabilizer is measured during combustion and the combustion conditions are checked according to only the measured temperature of the stabilizer and the aforesaid relationship. The stabilizer has a heat receiving surface at the most downstream side thereof. The temperature of a portion of the stabilizer around the heat receiving surfaces measured to allow an accurate assessment of the combustion conditions.

Stabilizer for gas turbine combustors and gas turbine combustor equipped

A vapor cooled gas turbine has a cooling system including a vapor supply port and a vapor recovery port, and the cooling system is formed so that vapor from the supply port is supplied to blades through a central supply passage in a rotor and the vapor having cooled the blades is recovered from the recovery port through a recovery passage spaced outwardly from the supply passage.

Gas turbine

A plurality of turbulence promotors (11) are arranged on a surface of a stabilizer (11) comprising a stabilizer portion (14) contacting combustion gas and support portion (15) for rectifying flow except for a heat receiving surface (13) contacting with combustion gas to promote heat transfer from the stabilizer to an air fuel flow. The distance between the turbulence promotor closest to the heat receiving surface (13) and the heat receiving surface is at least 4 times the height of said turbulence promotor to prevent back fire due to provision of the turbulence promotor.

A motor provided with a magnetic fluid bearing device for suppressing vibration and irregular rotation as well as preventing the magnetic fluid from being scattered from a bearing portion and the inside of the motor. The motor includes a rotor having a polygon mirror mounted thereon, a stator unit having driving coils, a rotor position detector and a rotor revolution detector attached thereto, a magnetic fluid bearing unit having a magnetic seal and a dynamic pressure seal attached thereto and a magnetic bearing. A triple seal structure for magnetic fluid which includes a first fluid seal constituted by the seals of the bearing unit, a second fluid seal constituted by a magnet of the rotor and a third fluid seal constituted by a magnet of the seal magnet is provided in the motor.

Sealed magnetic fluid bearing for polygon mirror drive motor

There is disclosed a polygon mirror motor in which an annular projection is formed on an upper surface of a rotor support member supporting a polygon mirror, and the annular projection supports a part of a lower surface of the polygon mirror. Radial bearings supporting a shaft of the motor have a plurality of oil grooves extending over about a half of the dimension of the radial bearing in a thrust direction. A magnetic fluid is filled in a space defined by the shaft, a support tube of a bearing support member and the radial bearings.

Vertical motor, method of manufacturing same, polygon mirror motor using

In a cascade device for a gas turbine, cooling air which has passed through a trailing air cooling chamber of each stationary blade is discharged from a tip of the stationary blade toward a side surface of a base of a moving blade disposed adjacent to the stationary blade. With this arrangement, the cooling of the stationary blade as well as the sealing of a cascade portion is effected satisfactorily with a smaller amount of the air.

Improvements in cooling and sealing for a gas turbine cascade device

A blade for a gas turbine has a leading edge portion which has an arc-shaped cross-section, and a maximum thickness portion of the blade is located within this arc. With this blade configuration, an abrupt acceleration of hot gas at the leading edge portion of the blade is restrained, so that the velocity of the hot gas at the blade surface can be made low. Therefore, the heat transfer coefficient from the hot gas to the blade wall is lowered, so that the amount of cooling air required to be passed through the interior of the blade can be reduced.

Gas turbine and gas turbine blade

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Katsuta, Japan

Kazuhiko Kawaike