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

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Применить Всего найдено 8. Отображено 8.
13-12-2012 дата публикации

ICE SHED REDUCTION FOR LEADING EDGE STRUCTURES

Номер: US20120312924A1
Принадлежит: GENERAL ELECTRIC COMPANY

A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface. 1. A leading edge structure for use in an aerospace vehicle , comprising:(a) a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and(b) a plurality of mechanical discontinuities formed in the flowpath surface, the mechanical discontinuities adapted to promote stress concentrations in ice attached to the flowpath surface.2. The leading edge structure of wherein the discontinuities are defined by one or more ribs extending from the flowpath surface.3. The leading edge structure of wherein the ribs are curved so as to be generally parallel to the expected flowfield around the flowpath surface during operation.4. The leading edge structure of wherein the discontinuities are defined by adjacent portions of the flowpath surface which are offset from each other.5. The leading edge structure of wherein faces defined by adjacent portions of the flowpath surface are curved so as to be generally parallel to the expected flowfield around the flowpath surface during operation.6. The leading edge structure of wherein the body comprises aluminum.7. A splitter for a turbofan engine claim 1 , comprising:(a) an annular body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and(b) a plurality of mechanical discontinuities formed in the flowpath surface, the mechanical discontinuities adapted to promote stress concentrations in ice attached to the flowpath surface.8. The splitter of wherein the discontinuities are defined by one or more ribs extending from the flowpath surface.9. The ...

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08-05-2012 дата публикации

Ice shed reduction in leading edge structures

Номер: CA2722175C
Принадлежит: General Electric Co

A leading edge (39) structure for use in an aerospace vehicle includes a body-having a flowpath surface (40) which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating (42) comprising nickel applied to at least a portion of the flowpath surface (40).

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13-06-2017 дата публикации

Ice shed reduction for leading edge structures

Номер: CA2722099C
Принадлежит: General Electric Co

A leading edge structure for use in an aerospace vehicle includes a body (38) having a flow-path surface (48) which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities (42), so as to promote stress concentrations in ice attached to the flow-path surface.

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29-11-1991 дата публикации

BEARING FOR USE IN AN OPERATING ENVIRONMENT AT HIGH TEMPERATURE.

Номер: FR2662477A1
Принадлежит: General Electric Co

Un palier (14) de support d'un arbre de rotor (10) tournant à haute vitesse dans un réacteur d'avion où la température atteint 800degré C est soumis à cette température et comprend des chemins de roulement intérieur et extérieur (18, 20) munis d'éléments roulants (22), capables de fonctionner à une telle température sans effet néfaste, ceux-ci étant constitués, par exemple, de composites à matrice céramique. Comme l'unité de palier aura une dilatation thermique différente de celle de son logement métallique de support, elle est maintenue dans des paires de cages cylindriques opposées, une paire de cages intérieures (46, 48) servant au maintien du chemin de roulement intérieur (18) et une paire de cages extérieures (42, 44) à celui du chemin extérieur (20). Les cages comportent des rebords à une extrémité et des bras de support espacés circulairement les uns des autres qui s'étendent à partir des rebords jusqu'aux emplacements de l'extrémité opposée des cages où ils sont formés en structures de doigts se montant dans les éléments de chemin de roulement, l'espacement entre les bras définissant des fentes dans les corps des cages. Des goujons d'assemblage sont portés par les structures de doigts et se montent dans les passages ou rainures ménagées dans les chemins de roulement. Les bras de support sont flexibles radialement mais rigides dans les directions tangentielle ou circonférentielle de sorte que la flexibilité radiale permet des dilatations thermiques radiales différentielles dans les composants de support tout en ayant l'unité de palier supportée et restreinte radialement. Application aux paliers à roulements des moteurs à réaction d'avion. A bearing (14) for supporting a rotor shaft (10) rotating at high speed in an aircraft engine where the temperature reaches 800 degrees C is subjected to this temperature and comprises inner and outer raceways (18, 20 ) provided with rolling elements (22), capable of operating at ...

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05-11-2009 дата публикации

Ice shed reduction for leading edge structures

Номер: US20090272850A1
Принадлежит: General Electric Co

A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

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24-03-2011 дата публикации

Reduction of ice separation at leading edge structures

Номер: DE112009000980T5
Принадлежит: General Electric Co

Vorderkantenstruktur zur Verwendung in einem Luft- oder Raumfahrtfahrzeug, die aufweist: (a) einen Körper, der eine Strömungspfadoberfläche aufweist, die eine Vorderkante definiert, die eingerichtet ist, um während des Betriebes einem Luftstrom zugewandt zu sein; und (b) eine metallische eisphobische Plattierung, die Nickel aufweist und die auf wenigstens einem Abschnitt der Strömungspfadoberfläche aufgebracht ist. Leading edge structure for use in an aerospace vehicle, comprising: (a) a body having a flow path surface defining a leading edge configured to face an airflow during operation; and (b) a metallic ice phobic plating comprising nickel deposited on at least a portion of the flow path surface.

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26-11-2009 дата публикации

Ice shed reduction for leading edge structures

Номер: CA2722099A1
Принадлежит: General Electric Co

A leading edge structure for use in an aerospace vehicle includes a body (38) having a flow-path surface (48) which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities (42), so as to promote stress concentrations in ice attached to the flow-path surface.

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21-08-2012 дата публикации

Ice shed reduction for leading edge structures

Номер: US8245981B2
Принадлежит: General Electric Co

A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

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