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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 4. Отображено 4.
22-03-2017 дата публикации

A sealing attachment for a gas turbine engine

Номер: GB0002542486A
Автор: SIMON LLOYD JONES [GB], SIMON LLOYD JONES, Simon Lloyd Jones
Принадлежит:

Wall component for a gas turbine engine comprises a gas facing surface and male part 310 of a male-female sealing attachment which radially locates a component within the engine. The male part comprises main body 312 having two arms 314, 316 extending in a common direction either side of a mid-line 318. At least one of the arms is convexly curved, providing a contact portion 320 being furthest from the mid-line plane. The sealing attachment may be a hook and groove attachment extending longitudinally in a circumferential direction. The male part may be integral to the wall component. The first and second arms may be arranged symmetrically, may be coterminous at their distal ends, and may be connected by an end cap 322 which may be convexly curved. The arms may be resiliently deformable such that the contact portion compressibly engages with a female part 410. The wall component may be a turbine seal segment designed to provide an improved seal and reduce leaking. Also claimed is a gas turbine ...

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Номер записи: 1
07-12-2016 дата публикации

Manufacture of component with cavity

Номер: GB0002539092A
Автор: SIMON LLOYD JONES [GB], MATTHEW TUCKER [GB], SIMON LLOYD JONES, MATTHEW TUCKER, Simon Lloyd Jones, Matthew Tucker
Принадлежит:

A component made from additive layer manufacturing, with main core passage 32, has an inclined channel 36 extending from a first end of the core passage 32 to an external surface of the component. The channel 36 axis forms an obtuse apex with the main core passage 32 axis, and is inclined to the build plane. The component, e.g. with side walls 33, 34, may be formed from powder. Excess material is removed via the channel 36, e.g. by turning the component and agitating, using a vibrating rig. The channel 36 may meet the core passage 32 with a smoothly curved join and sloping shoulders. Additional channels 36 may extend from the core passage 32, e.g. for cooling the component when used in a gas turbine engine. The channel 36 and core passage 32 may be straight, curved or serpentine, with various cross-sections. The manufacturing process involves defining an external and a core geometry of the component.

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Номер записи: 2
13-12-2017 дата публикации

Radial flow turbine heat engine

Номер: GB0002551181A
Автор: SIMON LLOYD JONES [GB], DRUMMOND WATSON HISLOP [GB], KIETH ROBERT PULLEN [GB], SIMON LLOYD JONES, DRUMMOND WATSON HISLOP, KIETH ROBERT PULLEN, Simon Lloyd Jones, Drummond Watson Hislop, Kieth Robert Pullen
Принадлежит:

A radial flow turbine heat engine 2 includes a compressor 6, a recuperator 10, a combustor 12 and a turbine 8. A compressor outlet manifold 14 collects compressed gas from the compressor through a plurality of compressor outlets 18. A turbine inlet manifold 16 supplies combustion gas to the turbine through a plurality of turbine inlets 24. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft 4 of the turbine to provide a flow path for compressed gas through the recuperator 10 located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine 2. Furthermore, a flow path for the combustion gas is provided to the turbine inlets which are radially inward with respect to the ...

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Номер записи: 3
28-12-2016 дата публикации

A wall cooling arrangement for a gas turbine engine

Номер: GB0002539782A
Автор: SIMON LLOYD JONES [GB], MARK JOHN SIMMS [GB], SIMON LLOYD JONES, MARK JOHN SIMMS, Simon Lloyd Jones, Mark John Simms
Принадлежит:

A wall arrangement 310 for the main gas path of a gas turbine engine comprises a wall segment 312 which defines the main gas path, the wall segment having a gas path side 320, an outboard side 322 and a support wall 324 extending from the outboard side towards a supporting structure. A channel member 350 abuts the support wall and defines one or more channels 356 between the support wall and channel member. The channel has radially separated inlet 352 and outlet 354, so that radial cooling flow is provided. This cooling arrangement may be particularly useful for a ceramic composite (CMC) component.

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Номер записи: 4