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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 3. Отображено 3.
13-06-2013 дата публикации

TURBINE ROTOR BLADE

Номер: WO2013084260A1
Автор: MIYOSHI, Ichiro, HIGUCHI, Shinichi, NODA, Masami
Принадлежит:

Provided is a turbine blade which makes it possible to reduce total pressure loss in the tip-side blade cross-section of a turbine rotor blade and suppress performance degradation even when cooling air is entrained therein. A turbine rotor blade which is attached to a rotor and forms a turbine cascade that rotates within a stationary member, wherein a platform part which forms a gas passage through which a mainstream gas flows, and an airfoil part which extends in a radial direction perpendicular to the rotating shaft of the rotor from a gas passage surface that is a surface forming the gas passage of the platform part are provided, the turbine rotor blade being formed such that a gap between a tip-side end surface that is an end surface on the leading end side of the airfoil part and the stationary member facing the tip-side end surface is smaller on the downstream side than the upstream side in the flow direction of the mainstream gas.

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Номер записи: 1
20-03-2014 дата публикации

GAS TURBINE

Номер: WO2014041619A1
Автор: MIYOSHI Ichiro, HIGUCHI Shinichi, NODA Masami
Принадлежит:

The purpose of the invention is to suppress the development of secondary currents near a rotor-blade front edge of a gas turbine even when cooling refrigerant is mixed in from the front edge of the end wall of a rotor blade. A gas-turbine rotor blade (4) comprising: a wing-shaped part (12) configured from a negative-pressure surface (12d) extending from a front edge (12a) to a rear edge (12b), a pressure surface (12c) facing the negative-pressure surface (12d) and extending from the front edge (12a) to the rear edge (12b), and a tip surface enclosed by the top end of the negative-pressure surface (12d) and the top end of the pressure surface (12c); and an end wall (10) connected to the bottom end of the negative-pressure surface (12d) and the bottom end of the pressure surface (12c); wherein the rotor blade has a convex shape in positions constituting the front edge (12a) side and the negative-pressure surface (12d) side of the end wall (10), and the rotor blade has a concave shape in positions ...

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Номер записи: 2
29-11-2012 дата публикации

CASING SHROUD FOR TURBO MACHINE

Номер: WO2012160586A1
Автор: HIGUCHI, Shinichi, MARUSHIMA, Shinya, NODA, Masami, MIYOSHI, Ichiro, TAKEDA, Takuya
Принадлежит:

Provided is a gas turbine configured so that the rotor blades have high energy conversion efficiency. A gas turbine comprises a compressor which compresses air, a combustor to which air discharged from the compressor is supplied and which combusts fuel, and a turbine to which combustion gas from the combustor is supplied. The turbine comprises stator blades, rotor blades which are located downstream of the stator blades, and a casing shroud which is located on the outer peripheral side of the rotor blades and which forms the outer peripheral wall of the flow path for the combustion gas. The casing shroud is characterized in that the casing shroud is provided with a coating having grooves in the surface thereof which faces the flow path for the combustion gas, the groove extending from the upstream end of the coating, within the range of ±10 degrees of the flow out angle of the stator blades.

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Номер записи: 3