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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 7. Отображено 7.
30-05-2017 дата публикации

Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system

Номер: US0009664062B2
Автор: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon, MUNSHI MRINAL, FINNERAN JOHN W, SHTEYMAN YEVGENIY, GRABER DARYL J, PORTER MATTHEW R, LEAGON JONATHAN M, Munshi Mrinal, Finneran John W., Shteyman Yevgeniy, Graber Daryl J., Porter Matthew R., Leagon Jonathan M.
Принадлежит: SIEMENS ENERGY, INC., MUNSHI MRINAL, FINNERAN JOHN W, SHTEYMAN YEVGENIY, GRABER DARYL J, PORTER MATTHEW R, LEAGON JONATHAN M, SIEMENS ENERGY INC, Munshi Mrinal, Finneran John W., Shteyman Yevgeniy, Graber Daryl J., Porter Matthew R., Leagon Jonathan M.

An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.

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Номер записи: 1
13-06-2013 дата публикации

GAS TURBINE OUTER CASE ACTIVE AMBIENT COOLING INCLUDING AIR EXHAUST INTO A SUB-AMBIENT REGION OF EXHAUST FLOW

Номер: US20130149107A1
Автор: Finneran John W., Graber Daryl J., Leagon Jonathan M., Munshi Mrinal, Porter Matthew R., Shteyman Yevgeniy
Принадлежит:

A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end. 1. A gas turbine engine comprising:an outer case defining a central longitudinal axis, and an outer surface of said outer case extending circumferentially around the central longitudinal axis;a cooling channel associated with said outer surface of said outer case, said cooling channel having a channel inlet and a channel outlet;an air duct including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of said gas turbine engine; andan exit structure at said air duct outlet end, said exit structure providing a sub-ambient pressure at said air duct outlet end to induce a flow from said air duct inlet end to said air duct outlet end.2. The gas turbine engine of claim 1 , wherein said exit structure interacts with a portion of said exhaust gas flow passing over said exit structure for effecting a reduced pressure at said outlet end to draw air from said cooling channel into said air duct.3. The gas turbine engine of claim 2 , wherein said exit structure partially covers said air duct outlet end claim 2 , shielding an upstream side of said outlet end and defining a downstream facing opening adjacent a downstream side of said outlet end.4. The gas turbine engine of claim 1 , wherein said exit structure produces a jet ...

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Номер записи: 2
13-06-2013 дата публикации

GAS TURBINE ENGINE WITH OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM

Номер: US20130149120A1
Автор: Finneran John, Graber Daryl, Leagon Jonathan M., Lee Ching-Pang, Munshi Mrinal, Porter Matthew R., Shteyman Yevgeniy
Принадлежит:

A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface. 1. A gas turbine engine comprising:an outer case defining a central longitudinal axis, and an outer case surface extending circumferentially around the central longitudinal axis; an internal insulating layer supported on an inner case surface opposite the outer case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case; and', 'a convective cooling channel defined by a panel structure located in radially spaced relation to the outer case surface and extending around the circumference of the outer case surface, the convective cooling channel is generally axially aligned with the internal insulating layer and forms a flow path for an ambient air flow cooling the outer case surface., 'a thermal barrier/cooling system for controlling a temperature of the outer case, the thermal barrier/cooling system including2. The gas turbine engine of claim 1 , wherein the convective cooling channel includes a cooling air supply inlet at a first circumferential location claim 1 , and an exhaust air outlet at a second circumferential location diametrically opposite from ...

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Номер записи: 3
13-06-2013 дата публикации

GAS TURBINE ENGINE WITH MULTIPLE COMPONENT EXHAUST DIFFUSER OPERATING IN CONJUNCTION WITH AN OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM

Номер: US20130149121A1
Автор: Finneran John W., Graber Daryl J., Leagon Jonathan M., Munshi Mrinal, Porter Matthew R., Shteyman Yevgeniy
Принадлежит:

An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling. 1. A gas turbine engine comprising:at least one exhaust diffuser positioned downstream from a turbine assembly, extending circumferentially around a central longitudinal axis of the gas turbine engine and having an increasing cross-sectional area from an upstream edge to a downstream edge;wherein the downstream edge of the at least one exhaust diffuser includes at least one downstream attachment flange having at least one downstream attachment orifice extending therethrough.2. The gas turbine engine of claim 1 , wherein the at least one downstream attachment flange comprises a plurality of downstream attachment flanges extending generally radially outward from the at least one exhaust diffuser.3. The gas turbine engine of claim 2 , wherein adjacent downstream attachment flanges are separated by a void that is defined by a first outer surface extending between a first downstream attachment flange and the exhaust diffuser and having a radius claim 2 , a second outer surface extending between a second downstream attachment flange and the exhaust diffuser and having a radius claim 2 , and a third outer surface extending between first and second outer surfaces claim 2 , wherein the third outer surface has a radius larger than the radii of the first and second outer surfaces.4. The gas turbine engine of claim 3 , wherein the ...

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Номер записи: 4
25-09-2014 дата публикации

Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity

Номер: US20140286763A1
Автор: Daryl J. Graber, John W. Finneran, Jonathan M. Leagon, Matthew R. Porter, Mrinal Munshi, Yevgeniy Shteyman
Принадлежит: SIEMENS AG

A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.

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Номер записи: 5
28-07-2011 дата публикации

Removal of stuck blade in a turbine engine

Номер: US20110179645A1
Автор: Jonathan M. Leagon, Kenneth L. Moore, Mahmood K. Silieti, Robert D. Barker
Принадлежит: Siemens Energy Inc

An apparatus for dislodging stuck blades in a turbine engine. The apparatus includes a housing, cam structure, and impact structure. The housing is capable of being temporarily secured to a blade disc structure adjacent to a stuck blade to be dislodged. The cam structure is associated with the housing and is adapted to receive an input torque that rotates the cam structure, the cam structure capable of translating the input torque into an impact force, the impact force including a component in a desired direction. The impact structure is associated with the housing and is capable of receiving the impact force from the cam structure and exerting the impact force on a root area of the stuck blade for dislodging the stuck blade from the blade disc structure non-destructively.

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Номер записи: 6
18-09-2014 дата публикации

Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow

Номер: WO2014114652A3
Автор: Daryl J. Graber, John W. Finneran, Jonathan M. Leagon, Matthew R. Porter, Mrinal Munshi, Yevgeniy Shteyman
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end.

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Номер записи: 7