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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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Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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13-03-2018 дата публикации

Приспособление для ремонта дисков сошника

Номер: RU0000177811U1
Автор: Александр Геннадиевич Пастухов, Андрей Васильевич Сахнов, Михаил Иванович Волков
Принадлежит: Федеральное государственное бюджетное образовательное учреждение высшего образования "Белгородский государственный аграрный университет имени В.Я. Горина"

Полезная модель относится к приспособлениям для ремонта дисков сошника и может найти широкое использование в сельском хозяйстве, при восстановлении дисков путем сварки, в частности при варке кольца. 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 177 811 U1 (51) МПК B23K 37/04 (2006.01) B23P 6/00 (2006.01) A01C 7/20 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B23K 37/04 (2006.01); B23P 6/00 (2006.01); A01C 7/20 (2006.01) (21)(22) Заявка: 2017113238, 17.04.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: Приоритет(ы): (22) Дата подачи заявки: 17.04.2017 (45) Опубликовано: 13.03.2018 Бюл. № 8 R U 1 7 7 8 1 1 (54) Приспособление для ремонта дисков сошника (57) Реферат: Полезная модель относится к приспособлениям для ремонта дисков сошника и может найти широкое использование в сельском Стр.: 1 (56) Список документов, цитированных в отчете о поиске: RU 114899 U1, 20.04.2012. RU 2380786 С1, 27.01.2010. EP 0404020 A1, 27.12.1990. GB 2227191 A, 25.07.1990. хозяйстве, при восстановлении дисков путем сварки, в частности при варке кольца. 3 ил. U 1 U 1 Адрес для переписки: 308503, Белгородская обл., Белгородский р-н, п. Майский, ул. Вавилова, 24, ФГБОУ ВО Белгородский ГАУ, Н.Е. Крючковой 1 7 7 8 1 1 (73) Патентообладатель(и): Федеральное государственное бюджетное образовательное учреждение высшего образования "Белгородский государственный аграрный университет имени В.Я. Горина" (RU) 13.03.2018 R U 17.04.2017 (72) Автор(ы): Сахнов Андрей Васильевич (RU), Пастухов Александр Геннадиевич (RU), Волков Михаил Иванович (RU) RU 5 10 15 20 25 30 35 40 45 177 811 U1 Полезная модель относится к приспособлениям для ремонта дисков сошника и может найти широкое использование в сельском хозяйстве, при восстановлении дисков путем сварки, в частности, при варке кольца. Известно приспособление для ремонта дисков сошника, снабженное фиксатором, обеспечивающее возможность точной и быстрой фиксации верхнего ...

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Номер записи: 1
26-01-2012 дата публикации

Cylinder head rocker arm stand repair and process

Номер: US20120017861A1
Автор: Christopher Bach, CURTIS Graham, Michael Bridges, Trent Simpson
Принадлежит: Caterpillar Inc

A process for remanufacturing a cylinder head that includes a worn or damaged rocker arm stand adapted to receive a rocker shaft to which at least one rocker arm is mounted, the steps including machining a channel in a surface of the worn or damaged rocker arm stand, securing an insert into the channel, and machining the insert to form a remanufactured inner facing surface. The remanufactured cylinder head includes at least one rocker arm stand that has a machined channel with a remanufactured insert secured therein, the rocker shaft being disposed adjacent the inner facing surface, not the rocker arm stand.

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Номер записи: 2
01-03-2012 дата публикации

Retaining ring arrangement for a rotary assembly

Номер: US20120051918A1
Автор: Bruno Chatelois, David F. GLASSPOOLE
Принадлежит: Pratt and Whitney Canada Corp

A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

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Номер записи: 3
15-03-2012 дата публикации

Low-pressure turbine

Номер: US20120063914A1
Автор: Gerald Gillant Gregory Nicolas, OLIVIER Belmonte
Принадлежит: SNECMA SAS

A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

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Номер записи: 4
05-04-2012 дата публикации

Steam turbine rotor, method of manufacturing the same, and steam turbine

Номер: US20120082542A1
Автор: Masato Misawa
Принадлежит: Individual

In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates.

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Номер записи: 5
05-04-2012 дата публикации

Apparatus and methods for cooling platform regions of turbine rotor blades

Номер: US20120082550A1
Автор: Adrian Lional Scott, John Wesley Harris, JR., Scott Edmond Ellis, Xiaoyong Fu
Принадлежит: General Electric Co

A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.

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Номер записи: 6
05-04-2012 дата публикации

Cooed IBR for a micro-turbine

Номер: US20120082563A1
Автор: Jack W. Wilson, Jr., James P. Downs, John E. Ryznic
Принадлежит: Florida Turbine Technologies Inc

A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

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Номер записи: 7
05-04-2012 дата публикации

Cooled rotor blade

Номер: US20120082567A1
Автор: Ian Tibbott, Oliver C.T. TIBBOTT
Принадлежит: Rolls Royce PLC

A cooled turbine rotor blade for a gas turbine engine is provided. The engine has an annular flow path for conducting working fluid though the engine. The blade has an aerofoil section for extending across the annular flow path. The blade further has a root portion radially inward of the aerofoil section for joining the blade to a rotor disc of the engine. The blade further has a platform between the aerofoil section and the root portion. The platform extends laterally relative to the radial direction of the engine to form an inner boundary of the annular flow path and to provide a rear overhang portion which projects in use towards a corresponding platform of a downstream nozzle guide vane. The platform contains at least one internal elongate plenum chamber for receiving cooling air. The longitudinal axis of the plenum chamber is substantially aligned with the circumferential direction of the engine. The plenum chamber supplies the cooling air to a plurality of exit holes formed in the external surface of the rear overhang portion to cool that portion.

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Номер записи: 8
19-04-2012 дата публикации

Thermally insulating turbine coupling

Номер: US20120093661A1
Автор: Keith R. Pullen, Michael J. Vick
Принадлежит: IMPERIAL INNOVATIONS LTD

A rotor assembly, including at least one driven member, e.g., a compressor rotor, and at least one driving member, e.g., a turbine. At least one rotating thermal insulator rigidly attached to either the driven member or the driving member. A coupling feature that includes mating geometric surfaces on the driven member and the driving member, wherein the geometric surfaces are configured to allow radial sliding, relative centering, torque transmission, and axial constraint between the driven member and the driving member.

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Номер записи: 9
24-05-2012 дата публикации

Repair of turbine components and solder alloy therefor

Номер: US20120125979A1
Автор: Bernd Daniels, Michael Hillen
Принадлежит: MTU AERO ENGINES GMBH

A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated.

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Номер записи: 10
21-06-2012 дата публикации

Turbine rotor for air cycle machine

Номер: US20120156046A1
Автор: Brent J. Merritt, Harold W. Hipsky
Принадлежит: Hamilton Sundstrand Corp

A turbine rotor for an Air Cycle Machine includes a hub with a multiple turbine blades which extend therefrom, each of the multiple of turbine blades defined by a set of coordinates.

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Номер записи: 11
21-06-2012 дата публикации

Method for the local heat treatment of gas turbine blades

Номер: US20120156630A1
Автор: Christian Hornig, Jens Weder
Принадлежит: MTU AERO ENGINES GMBH

A method for heat-treating gas turbine blades, namely for locally heat-treating at least one gas turbine blade in a blade section thereof; a blade root section, which is not to be heat-treated, of the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the particular blade root section, which is not to be heat-treated, during the heat treatment of the particular blade section. The blade root section of the gas turbine blade is positioned in an interior space in a way that allows a remaining interior space of the holding receptacle, to be filled with a filler material; the holding receptacle, together with the gas turbine blade, being subsequently positioned in a heat treatment chamber to enable the gas turbine blade in the heat treatment chamber to undergo local heat treatment under vacuum.

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Номер записи: 12
05-07-2012 дата публикации

Apparatus and methods for cooling platform regions of turbine rotor blades

Номер: US20120171046A1
Автор: Bradley Taylor Boyer
Принадлежит: General Electric Co

A configuration of cooling channels through the interior of a turbine rotor blade having a platform, wherein the rotor blade includes an airfoil cooling channel that includes a cooling channel formed within the airfoil and an outboard airfoil supply channel. The configuration of cooling channels may include: a platform cooling channel that comprises a cooling channel that traverses at least a portion of the platform, the platform cooling channel having an upstream end and a downstream end; an outboard platform supply channel, which comprises a cooling channel that stretches from a second coolant inlet formed in the root to the upstream end of the platform cooling channel; and an inboard platform return channel, which comprises a cooling channel that stretches from the downstream end of the platform cooling channel to a termination point formed in the root.

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Номер записи: 13
30-08-2012 дата публикации

Repair alignment method and apparatus for turbine components

Номер: US20120216402A1
Автор: Gary R. Peters, Hai Sam, Michael Gary Krizansky
Принадлежит: General Electric Co

A turbine component repair apparatus includes: a first die having male and female halves for clamping a first section of a turbine blade with a platform and a root portion of an airfoil, the first die having a recess shaped to receive the root portion and retain a faying surface thereof in predetermined alignment; and a second die having male and female halves for clamping a repair section which defines a tip portion of the airfoil, the second die having a second recess shaped to receive the tip portion and retain a faying surface of the tip portion in predetermined alignment. The first and second dies have mating front faces configured to align their bottom surfaces in a common plane. A alignment device is removably attached to the second die to temporarily align the repair section in the absence of the male half of the second die.

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Номер записи: 14
25-10-2012 дата публикации

Turbine wheel for a turbine engine

Номер: US20120269650A1
Автор: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq
Принадлежит: SNECMA SAS

A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.

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Номер записи: 15
01-11-2012 дата публикации

Systems and methods for making flush architectural doors using post-consumer materials

Номер: US20120272616A1
Автор: William Henry Lucas, Iii
Принадлежит: RECOR INTERNATIONAL Inc

A method for forming a flush architectural wooden door using at least one post-consumer material includes collecting a previously-used door from a collection site. The previously-used door includes a core having a first major surface, a second major surface opposite to the first major surface, and a perimeter extending around the opposing major surfaces. The core is extracted from the previously-used door. Rails and styles are applied to a perimeter of the extracted core. A first skin is applied over the first major surface of the extracted core and applied rails and styles. The extracted core, rails, styles, and first skin have a collective weight. The extracted core forms over half of that collective weight.

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Номер записи: 16
08-11-2012 дата публикации

Blade, Integrally Bladed Rotor Base Body and Turbomachine

Номер: US20120282109A1
Автор: Frank Stiehler
Принадлежит: MTU AERO ENGINES GMBH

A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.

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Номер записи: 17
17-01-2013 дата публикации

Rotor assembly for gas turbines

Номер: US20130017092A1
Автор: Christopher Edward Miller
Принадлежит: General Electric Co

A rotor assembly is disclosed. The rotor assembly may include a first rotor disk defining a first axially extending slot and a second rotor disk defining a second axially extending slot. Additionally, the rotor assembly may include a pin extending lengthwise between the first and second rotor disks. The pin may include a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot.

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Номер записи: 18
24-01-2013 дата публикации

Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy

Номер: US20130020377A1
Автор: Alexander Stankowski, Daniel Beckel
Принадлежит: Individual

In a Ni-based, Co-based, or Ni—Co-based braze alloy ( 1 ) for high-temperature brazing of components ( 7 ) of modular structure and for repairing damaged components ( 7 ) which are formed of single crystal or directionally solidified superalloys using said braze alloy ( 1 ), the braze alloy has a first metallic powder component ( 2 ) having particle sizes in the nanometer range and a second metallic powder component ( 3 ) having particle sizes in the micrometer range. The surface of the particles of the second powder component ( 3 ) is thinly coated with particles of the first powder component ( 2 ). The braze alloy ( 1 ) additionally includes grain boundary stabilizing elements as alloying elements. In addition, melting point depressants can be present in the braze alloy ( 1 ) in a commercially common quantity or with a considerably increased proportion. Both the melting temperature of the braze alloy ( 1 ) and the probability of recrystallization are advantageously reduced.

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Номер записи: 19
31-01-2013 дата публикации

Compressor rotor

Номер: US20130028750A1
Автор: Christian Dombek, Mauro Corradi
Принадлежит: Alstom Technology AG

A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring.

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Номер записи: 20
14-02-2013 дата публикации

Oil mist separation in gas turbine engines

Номер: US20130039760A1
Автор: Alexander J. Burt, Keith C. Sadler
Принадлежит: Rolls Royce PLC

A rotor stage is provided which comprises a shank passage for separating liquid from secondary air system (SAS) air. The shank passage is formed between a radially outer surface of a disc post, a radially inner surface of one or more blade platforms, and the shanks of two neighbouring blades. In use, SAS air is supplied to the shank passage. Any liquid, such as oil, is separated from the SAS air due to the centripetal acceleration of the rotation of the rotor disc. The separated oil can then flow, or seep, past the blade platform and into the working fluid. The remainder of the SAS air passes through a hole in a sealing plate at the downstream end of the rotor stage, thereby providing SAS air with a lower liquid content for use downstream of the rotor stage.

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Номер записи: 21
14-02-2013 дата публикации

System and method for controlling flow in turbomachinery

Номер: US20130039772A1
Автор: Karthik Srinivasan, Sushil Babu Mane, Vishal Rajpurohit
Принадлежит: General Electric Co

A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge.

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Номер записи: 22
21-02-2013 дата публикации

Rotor seal wire groove repair

Номер: US20130042474A1
Автор: Daniel David Noe, Douglas Jerome JONES, Michael Alan PIERSON
Принадлежит: General Electric Co

A method of repairing a seal wire groove is disclosed, the groove forming an annular structure having an outer surface and an inner surface and defining an original profile when new, comprising the steps of: removing a less-than-annular portion of the original profile of the groove to remove damaged portions of at least one of the inner and outer surfaces thereby forming a void; adding new material to the void; and shaping the new material to form a new profile of the groove.

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Номер записи: 23
21-02-2013 дата публикации

Turbine blade cooling system with bifurcated mid-chord cooling chamber

Номер: US20130045111A1
Автор: Ching-Pang Lee
Принадлежит: Siemens Energy Inc

A cooling system for a turbine blade of a turbine engine having a bifurcated mid-chord cooling chamber for reducing the temperature of the blade. The bifurcated mid-chord cooling chamber may be formed from a pressure side serpentine cooling channel and a suction side serpentine cooling channel with cooling fluids passing through the pressure side serpentine cooling channel in a direction from the trailing edge toward the leading edge and in an opposite direction through the suction side serpentine cooling channel. The pressure side and suction side serpentine cooling channels may flow counter to each other, thereby yielding a more uniform temperature distribution than conventional serpentine cooling channels.

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Номер записи: 24
14-03-2013 дата публикации

Zipper repairer and extender

Номер: US20130061434A1
Автор: Tammy Rice Hampton
Принадлежит: Individual

A zipper device for repairing and extending the life of a standard zipper used on boat tops, covers and enclosures, or the tops, covers and enclosures on other equipment that use a zipper for fastening and snapping together their openings. The use of the zipper device of the present invention also widens a standard zipper to provide slack to tops, covers and enclosures on boats and other equipment.

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Номер записи: 25
28-03-2013 дата публикации

Interface element between a blade root and a blade root housing of a turbine disc, and turbine rotor comprising an interface element

Номер: US20130078101A1
Автор: Alain Dominique Gendraud, Fabrice Marcel Noel Garin, Romain Nicolas Lunel, Thierry Lequitte
Принадлежит: SNECMA SAS

An interface element to be mounted between a blade root and a blade root housing provided in a turbine disc of a gas turbine engine to limit wear between the root and the housing. The interface element includes: a base, configured to be aligned with a lower part of the root; and first and second upper side walls connected to the base and configured to surround the blade root up to an upper portion thereof, the first upper side wall including at least one ventilation opening to allow a flow of cooling air flowing through the rotor disc housing to flow over the upper portion of the root via the ventilation opening.

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Номер записи: 26
28-03-2013 дата публикации

METHOD AND A DEVICE PERTAINING TO THE SERVICE NEED OF A FILTER IN A SCR-SYSTEM'S LIQUID SUPPLY DEVICE

Номер: US20130078156A1
Автор: Arvidsson Daniel, Bremberg Per, Liljestrand Andreas
Принадлежит:

Disclosed is a method pertaining to SCR systems for exhaust cleaning whereby liquid is supplied to a feed device via which it is supplied to a dosing unit at a consumption point of the SCR system. The method includes continuously determining cumulative amounts of liquid dosed via the dosing unit. Need for replacement or cleaning of a filter unit for said liquid is also determined on the basis of the cumulative amounts of liquid dosed. The method further includes dosing at least part of the liquid supplied via the feed device and feeding undosed liquid back in a return flow to enable it to be supplied again to the feed device. Also disclosed is a computer program product that includes code for a computer for implementing the disclosed method. 1. A method pertaining to SCR systems for exhaust cleaning whereby liquid is then supplied to a feed device via which it is then supplied to a dosing unit at a consumption point of the SCR system , comprising:continuously determining cumulative amounts of liquid dosed via the dosing unit, by determining need for replacement or cleaning of a filter unit for said liquid on the basis of said cumulative amounts of liquid dosed;dosing at least part of the liquid supplied via the feed device; andfeeding undosed liquid back in a return flow to enable said liquid to be supplied again to said feed device.2. A method according to claim 1 , further comprising the step of:determining the need by comparing a value which represents cumulative amounts of liquid dosed with a predetermined value.3. A method according to claim 1 , further comprising the step of:determining the need on the basis of the amount of undosed liquid fed back.4. A method according to claim 1 , further comprising the step of:determining said cumulative amounts of liquid dosed, on the basis of pressures of the liquid at said consumption point during at least one period of time when said liquid is being dosed.5. A method according to claim 1 , further comprising the step of ...

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Номер записи: 27
04-04-2013 дата публикации

COUNTER-ROTATABLE FAN GAS TURBINE ENGINE WITH AXIAL FLOW POSITIVE DISPLACEMENT WORM GAS GENERATOR

Номер: US20130081374A1
Автор: Fakunle Oladapo, Giffin Rollin George, Murrow Kurt David
Принадлежит:

A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section through a gearbox. The gas generator has inner and outer bodies having offset inner and outer axes extending through first, second, and third sections of a core assembly. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. A combustor section extends through at least a portion of the second section. 1. A counter-rotatable fan gas turbine engine comprising in downstream serial flow relationship a counter-rotatable fan section , a worm gas generator , and a counter-rotatable low pressure turbine operably connected to the counter-rotatable fan section.2. The engine as claimed in further comprising:the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and ...

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Номер записи: 28
11-04-2013 дата публикации

ROTOR DISC AND METHOD OF BALANCING

Номер: US20130086805A1
Автор: LECUYER Joseph Daniel, PRONOVOST Christian
Принадлежит: PRATT & WHITNEY CANADA CORP.

A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life. 1. A method of manufacturing a turbomachine rotor disc , the method comprising:providing the turbomachine rotor disc with at least one generally annular appendage coaxially disposed with reference to a central rotation axis of the turbomachine rotor disc; andmachining a plurality of spaced-apart and substantially radially-extending slots in a free end of the appendage, the slots delimiting a plurality of sacrificial protrusions from which material can be removed during balancing.2. The method as defined in claim 1 , wherein the spaced-apart slots are circumferentially equally spaced on the free end of the appendage.3. The method as defined in claim 1 , wherein the turbomachine rotor disc comprises a plurality of blade receiving slots on an outer periphery thereof.4. A method for gas turbine rotor disc balancing comprising the steps of:providing a rotor disc having at least one balancing assembly provided substantially coaxially with reference a rotation axis of the rotor disc, the balancing assembly having a plurality of spaced-apart sacrificial protrusions extending between adjacent stress-relieving slots, bottoms of said adjacent slots defining a base end of the protrusions, each protrusion extending from its base end to a free end, the slots provided with a shape providing a stress concentration below a crack propagation threshold in a region of the slot bottoms;determining an imbalance to the rotor disc; and thenremedying the imbalance by ...

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Номер записи: 29
11-04-2013 дата публикации

HEAT-EXCHANGE ARCHITECTURE BUILT INTO THE EXHAUST OF A TURBINE ENGINE

Номер: US20130086906A1
Автор: THOMAS Rainer
Принадлежит: TURBOMECA

A heat-exchange architecture for exhaust of a turbine engine, including heat-exchange elements partially obstructing a hot exhaust gases stream. In an architecture built into an exhaust line for gas streams of a turbine engine, the turbine engine is a turboshaft engine including a gas generator and a free turbine supplying power to a shaft via a through-shaft and an upstream reduction gear. An annular plate-shaped exchanger is installed in the axisymmetric portion of the ejector. The exchanger includes inlet and outlet channels, connected to the inlet and outlet of a central channel wound into a helix shape or sine curve in the annular plate. The channels are connected at the other ends to mechanical or electromechanical mechanisms for recovering and recycling energy. The energy is recovered via a cold fluid heated in the central channel by transfer of heat from residual gases. 110-. (canceled)11: An architecture of a turbine engine with a heat exchanger built into an exhaust line for a stream of hot gases of a turbine engine , comprising:heat-exchange elements installed in one of units constituting the exhaust line configured to channel the stream of the hot gases and achieve a partial obstruction of the gas stream, in an environment that globally diffuses the gases, while a part of the stream flows across the heat-exchange elements; andmechanical or electromechanical means connected to the heat exchange elements for recovery and recycling of residual thermal energy of the gases to increase power available at a shaft of the turbine engine without substantially disturbing the stream of the gases.12: An architecture with a built-in heat exchanger according to claim 11 , in which the heat-exchange elements have a structure with a section that evolves in a continuous way.13: An architecture with a built-in heat exchanger according to claim 11 , in which the heat-exchange elements have claim 11 , in cross-section claim 11 , a localized structure claim 11 , which is ...

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Номер записи: 30
11-04-2013 дата публикации

METHOD FOR REPLACING AN OUTER ANNULAR RING OF A FLUID SWIVEL AND A FLUID SWIVEL

Номер: US20130088008A1
Автор: Evrard Cyril
Принадлежит:

Method for replacing an outer annular ring a fluid swivel (), the fluid swivel being adapted to allow fluid transfer across a rotary interface between the end of a fluid line connected to the seabed and product piping on a vessel for gas and oil production, wherein the swivel () comprises an inner annular ring () and an outer annular ring, the rings being located with their adjacent cylindrical surfaces in close proximity for defining a chamber (), for receiving a fluid, between the peripheral opposing faces of the inner annular ring and the outer annular ring, wherein the inner annular ring () is adapted to be connected to the end of the fluid line and wherein the outer annular ring is adapted to be connected to the product piping on the vessel, wherein the method comprises the steps of: removing the outer annular ring, replacing the outer annular ring by means of a first semi-circular element () and a second semi-circular element (), and fixing the first semi-circular element () to the second semi-circular element (), by means of a fixing means, to form the replacement outer annular ring of the swivel. 1. A method for replacing an outer annular ring of a fluid swivel , the fluid swivel being adapted to allow fluid transfer across a rotary interface between the end of a fluid line connected to the seabed and product piping on a vessel for gas and oil production , wherein the swivel comprises an inner annular ring and an outer annular ring , the rings being located with their adjacent cylindrical surfaces in close proximity for defining a chamber , for receiving a fluid , between the peripheral opposing faces of the inner annular ring and the outer annular ring , wherein the inner annular ring is adapted to be connected to the end of the fluid line and wherein the outer annular ring is adapted to be connected to the product piping on the vessel , wherein the method comprises the steps of:removing the outer annular ring;replacing the outer annular ring by means of at ...

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Номер записи: 31
18-04-2013 дата публикации

PAINTBALL MARKER WITH QUICK ACCESS RECEIVER

Номер: US20130091677A1
Автор: Rice John R.
Принадлежит: TIPPMANN SPORTS LLC

A paintball marker with a barrel having a bore dimensioned to receive a frangible projectile. The marker has a receiver defining an interior cavity with a breech area. The receiver includes a flip top portion that is, in some embodiments, pivotally connected to the receiver. The flip top portion is configured to pivot between an open position that provides access to the interior cavity and a closed position that blocks access to the interior cavity. A valve arrangement is provided to selectively allow flow between a supply of compressed gas and the breech area to propel frangible projectiles through the barrel. The marker has a firing assembly configured to actuate the valve arrangement in response to actuation of a trigger. 1. A method of servicing a paintball marker , the method comprising the steps of:providing a paintball marker including a receiver with an interior cavity in which a front bolt and a rear bolt are disposed, wherein the front bolt and the rear bolt are configured to move during firing to push a paintball towards a barrel and actuate a valve arrangement, respectively, wherein the receiver includes at least one wall that is movable with respect to one or more other walls of the receiver between an open position that opens the interior cavity to expose the front bolt and the rear bolt and a closed position that blocks access to the interior cavity;moving the wall of the receiver that is movable with respect to the other walls to expose the front bolt and the rear bolt; andremoving the front bolt and the rear bolt from the receiver.2. The method as recited in claim 1 , where the wall of the receiver is moved by pivoting the wall with respect to one or more other walls of the receiver.3. The method as recited in claim 1 , wherein the front bolt and the rear bolt are removed through an opening in the receiver created by moving the wall to the open position.4. The method as recited in claim 1 , further comprising the step of putting the front bolt and ...

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Номер записи: 32
18-04-2013 дата публикации

METHOD FOR REPAIRING ROTOR BLADES

Номер: US20130091704A1
Автор: Nebesni Josef
Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

In a method for repairing worn or damaged rotor blades of an aircraft engine, laser cladding for the reconstruction of the blade tips is not performed in a continuous welding process along the blade edge but during a cycle-by-cycle rotation of the rotor blades attached to a rotor disk, in only one limited section of the respective blade edge for each cycle. The method reduces time expenditure for the repair of the blades and improves the tribological properties of the blade material in the area of the repaired blade tip. 1. A method for repairing rotor blades of an aircraft gas turbine , comprising:removing a damaged portion of a rotor blade tip of each of a group of selected of rotor blades of a rotor, the rotor blades fastened to the rotor, at least one chosen from detachably and in one piece;reconstructing the damaged portion of the rotor blade tip of each of the group of selected rotor blades by laser cladding as follows:rotating the rotor to index the selected rotor blades to a laser-cladding unit;using a laser beam from the laser-cladding unit to heat and melt corresponding limited areas of tips of the rotor blades as each selected rotor blade is indexed at the laser-cladding unit, the laser beam being generated in a certain time interval for each selected rotor blade;supplying a metal powder flow in a certain time interval to the heated and melted corresponding limited areas as each selected rotor blade is indexed at the laser cladding unit to coat the tip of the indexed rotor blade in the corresponding limited area;rotating the rotor to index a further selected rotor blade to the laser-cladding unit and repeating above steps to coat the corresponding limited area of the tip of each selected rotor blade;repositioning the laser beam with respect to the rotor to heat and melt further corresponding limited areas along lengths of the tips of the selected rotor blades and repeating above steps until a desired length selected rotor blade is coated;repositioning the ...

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Номер записи: 33
18-04-2013 дата публикации

TURBINE

Номер: US20130091861A1
Автор: Groot Cornelis
Принадлежит: WEST 6 B.V.

A turbine includes a rotor having at least two rotor members for rotating in a plane, the rotor members being substantially diametrically arranged and attached to an axis situated substantially transversely to the plane, and drive unit coupled to the axis, wherein the rotor members include a fluid contact member, that is hingingly connected to an arm which is attached to the axis, characterized in that the fluid contact members are adapted to hinge between a fluid-active position in which the members project transversely to the plane and a fluid-transparent position in which the members extend mainly parallel to the plane. 112711812913101453547891011121314378910. Turbine () comprising a rotor () having at least two rotor members ( ,; ,; ,; ,) for rotating in a plane () , the rotor members being substantially diametrically arranged and attached to an axis () situated substantially transversely to the plane () , and drive unit () coupled to the axis , wherein the rotor members comprise a fluid contact member ( , , ,) that is hingingly connected to an arm ( , , ,) which is attached to the axis () , characterized in that the fluid contact members ( , , , ,) are adapted to hinge between a fluid-active position in which the members project transversely to the plane and a fluid-transparent position in which the members extend mainly parallel to the plane.2789101819533. Turbine according to claim 1 , wherein the fluid contact members ( claim 1 , claim 1 , claim 1 ,) comprise a flexible material claim 1 , the contact members being with one side connected to the arms and having a free end ( claim 1 ,) claim 1 , the free end in the fluid-active position being bent away from the plane () by a fluid force having a component situated parallel to the plane claim 1 , in a first angular position of the axis () claim 1 , and being lifted away from the fluid active position to the fluid-transparent position at a second angular position of the axis ().311121314. Turbine according to ...

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Номер записи: 34
18-04-2013 дата публикации

REPAIRING METHOD, REPAIRING STRUCTURE AND CONNECTING STRUCTURE OF EMBEDDED OPTICAL FIBER OF COMPOSITE MATERIAL STRUCTURE

Номер: US20130094820A1
Автор: HIRANO Noriyoshi, KIMOTO Junichi, Minakuchi Shu, MIZUTANI Tadahito, Takeda Nobuo, TSUTSUI Hiroaki
Принадлежит:

A method of repairing an embedded optical fiber of a composite material structure including an embedded optical fiber embedded in a composite material, includes removing a portion of the composite material including a damaged portion of the embedded optical fiber to form an opening portion; polishing an end surface of the embedded optical fiber exposed in the opening portion and an end surface of the composite material exposed in the opening portion; and performing position adjustment such that a core of the polished embedded optical fiber and a core of a replacement optical fiber are aligned with each other, butting the end surface of the embedded optical fiber and an end surface of the replacement optical fiber with each other, and connecting the end surface of the embedded optical fiber and the end surface of the replacement optical fiber together. 1. A method of repairing an embedded optical fiber of a composite material structure including an embedded optical fiber embedded in a composite material , comprising:removing a portion of the composite material including a damaged portion of the embedded optical fiber to form an opening portion;polishing an end surface of the embedded optical fiber exposed in the opening portion and an end surface of the composite material exposed in the opening portion; andperforming position adjustment such that a core of the polished embedded optical fiber and a core of a replacement optical fiber are aligned with each other, butting the end surface of the embedded optical fiber and an end surface of the replacement optical fiber with each other, and connecting the end surface of the embedded optical fiber and the end surface of the replacement optical fiber together.2. The method of repairing the embedded optical fiber of the composite material structure claim 1 , according to claim 1 ,wherein the replacement optical fiber has an optical fiber array at an end portion thereof, and an end surface of the optical fiber array and the ...

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Номер записи: 35
25-04-2013 дата публикации

EXHAUST GAS TREATMENT DEVICE, METHOD FOR PRODUCING A TUBE FOR AN EXHAUST GAS TREATMENT DEVICE AND WATERCRAFT HAVING AN EXHAUST GAS TREATMENT DEVICE

Номер: US20130098002A1
Автор: DANCKERT BERND, VOGEL SAMUEL
Принадлежит:

An exhaust gas treatment device for off-road applications includes a housing having a cross-sectional area and a first wall. At least one pipe extends through the first wall and has a second wall with a perforation. The exhaust gas treatment device includes, in particular, a reducing agent supply for urea and an SCR catalytic converter. A method for producing a tube with a perforation for an exhaust gas treatment device and a watercraft having at least one exhaust gas treatment device are also provided. 1. An exhaust gas treatment device , comprising:a housing having a cross-sectional area and a first wall; andat least one tube extending through said first wall;said at least one tube having a second wall with a perforation formed therein.2. The exhaust gas treatment device according to claim 1 , wherein said at least one tube has a first side and a second side claim 1 , and said perforation is disposed only at said first side of said at least one tube.3. The exhaust gas treatment device according to claim 1 , which further comprises:at least one exhaust gas treatment component disposed in said housing;said at least one tube having a first side facing away from said at least one exhaust gas treatment component; andsaid perforation being disposed only at said first side of said at least one tube.4. The exhaust gas treatment device according to claim 1 , wherein said housing has a cross-sectional area and a shape claim 1 , and said perforation is adapted to at least one of said cross-sectional area or said shape of said housing.5. A method for producing a tube with a perforation for an exhaust gas treatment device claim 1 , the method comprising the following steps:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'a) positioning said tube of the exhaust gas treatment device according to in said housing;'}b) dividing said cross-sectional area of said housing into segments;c) dividing said at least one tube into longitudinal sections;d) allocating said segments to said ...

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Номер записи: 36
02-05-2013 дата публикации

TAG TOOL PROTECTIVE DEVICE, SYSTEM, AND METHOD

Номер: US20130105543A1
Автор: Davis Raymond E., Hampton Clifton Glenn
Принадлежит:

A method for replacing a tag tool needle includes securing at least a portion of a tag tool needle coupled to a tag tool in a needle container; and removing the tag tool needle from the tag tool with the needle container. A tag tool needle container includes a first tubular aperture adapted to receive at least a portion of a first tag tool needle therein, where the first tubular aperture has a compression-fit adapted to securely enclose the portion of the first tag tool needle when urged over the first tag tool needle; and a second tubular aperture coupled to the first tubular aperture and adapted to receive at least a portion of a second tag tool needle therein, where the second tubular aperture has a compression-fit adapted to adapted to securely enclose the portion of the second tag tool needle when urged over the second tag tool needle. 1. A method for replacing a tag tool needle , the method comprising:securing at least a portion of a tag tool needle coupled to a tag tool in a needle container; andremoving the tag tool needle from the tag tool with the needle container.2. The method of claim 1 , wherein securing at least a portion of a tag tool needle coupled to a tag tool in a needle container comprises securing at least a portion of a tag tool needle coupled to a tag tool in a needle container without human contact of the tag tool needle.3. The method of claim 2 , wherein securing at least a portion of a tag tool needle coupled to a tag tool in a needle container without human contact of the tag tool needle comprises securing a sharpened end of the tag tool needle in a needle container without human contact of the tag tool needle.4. The method of claim 1 , wherein removing the tag tool needle from the tag tool with the needle container comprises removing the tag tool needle from the tag tool with the needle container without human contact of the tag tool needle.5. The method of further comprising applying a force to a portion of the tag tool needle extending ...

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Номер записи: 37
09-05-2013 дата публикации

APPARATUS FOR AIRCRAFT WITH HIGH PEAK POWER EQUIPMENT

Номер: US20130111917A1
Автор: Ho YuHang, KNOWLES JEFFREY A.
Принадлежит: Northrop Grumman Systems Corporation

An apparatus is provided for supplying electrical power and cooling for an aircraft. The apparatus includes a cooling turbine coupled to a shaft, a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air, a flywheel coupled to the shaft, a power turbine coupled to the shaft, and a starter generator coupled to the shaft between the compressor and the power turbine. 1. An apparatus for providing electrical power and cooling for an aircraft , the apparatus comprising:a cooling turbine coupled to a shaft;a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air;a flywheel coupled to the shaft;a power turbine coupled to the shaft; anda starter generator coupled to the shaft between the compressor and the power turbine.2. The apparatus of claim 1 , further comprising:a combustion chamber coupled to the power turbine; anda valve for connecting the combustion chamber to an output of the compressor.3. The apparatus of claim 1 , wherein the starter generator is connected to an energy accumulator unit bus through an inverter control unit.4. The apparatus of claim 3 , further comprising:a power distribution system connected to receive electrical power from the energy accumulator unit bus.5. The apparatus of claim 4 , wherein the power distribution system comprises:a first generator configured to supply power to a first power distribution unit;a second generator configured to supply power to a second power distribution unit;a first switch for connecting the energy accumulator unit to the first power distribution unit; anda second switch for connecting the energy accumulator unit to the first power distribution unit.6. The apparatus of claim 5 , further comprising:a solid state power controller connected between the first switch and the first power distribution unit.7. The apparatus of claim 6 , ...

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Номер записи: 38
09-05-2013 дата публикации

Turbomachine component and method of connecting cooling circuits of a turbomachine component

Номер: US20130115090A1
Автор: Aaron Ezekiel Smith, Scott Edmond Ellis
Принадлежит: General Electric Co

A turbomachine component is provided and includes a turbine blade, which is rotatable about a rotor of a turbine for power generation operations and a platform with which the turbine blade is to be assembled. The turbine blade is formed to define a main circuit having an appendage. The platform is formed to define a platform circuit, and a substantially radially extendible pathway configured to be coupled to the appendage and to the platform circuit.

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Номер записи: 39
16-05-2013 дата публикации

Fluid Movement System and Method for Determining Impeller Blade Angles for Use Therewith

Номер: US20130121804A1
Автор: Kerry N. Oliphant
Принадлежит: Concepts ETI Inc

A fluid movement system that includes an impeller having a blade with a leading edge blade tip angle determined as a function of an increase in mass flow rate due to reinjection of flow from a flow stability device located proximate to the leading edge tip of the blade. In an exemplary method, the leading edge blade tip angle can be determined based on selecting a blade incidence level based on a mass flow gain versus flow coefficient curve. Blade leading edge tip angles determined in accordance with a method of the present invention are typically greater than blade leading edge tip angles determined using traditional methods. The greater blade leading edge tip angles can lead to more robust blades designs.

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Номер записи: 40
23-05-2013 дата публикации

Gas turbine engine comprising a tension stud

Номер: US20130125559A1
Автор: Andrew Shepherd
Принадлежит: SIEMENS AG

A gas turbine engine including a rotor is disclosed. The rotor includes a stud extending along an axis, rotating elements of a first section, and rotating elements of a second section. The stud includes a first and second external end, the first external end adapted to engage a first pre-load nut or a shaft and the second external end adapted to engage a second pre-load nut or a shaft such that the set of rotating elements are secured. Thus stud includes a first shank connected to the first external end and a second shank connected to the second external end. The first shank is located in the first section and has a first diameter. The second shank is located in the second section and has a second diameter which is greater than the first diameter.

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Номер записи: 41
23-05-2013 дата публикации

SYSTEMS AND METHODS FOR PUNCTURE CLOSURE

Номер: US20130126012A1
Автор: Buchbinder Maurice, Cohen Aharon, Eckhouse Shimon, Goldberg Eran, LOGAN Julie, Mizrahi Noam, Yadin Amnon
Принадлежит: Cardiodex Ltd.

Systems, apparatuses and methods are provided for use in closing punctures in vessel walls. An apparatus may have various combinations of an anchoring device, a positioning device and a heating element for closing a puncture within a vessel wall. An anchoring device may be a balloon, an expansible cage, a wire operated T-anchor, and/or a floating anchor. A positioning device may be a balloon, a sponge, and/or an expansible cage. A heating element may be flexible or rigid and preferably provides heat to target tissue through conduction and convection. A heating element may be flat-ended or dome-shaped. The heating element and anchoring device may be positioned a fixed distance apart to sandwich tissue between the heating element and the anchoring device. The heating element may operate in multiple stages. An initial stage may non-permanently adhere the heating element to the tissue and the subsequent stage may close the puncture. 1. An apparatus for closing a puncture in a vessel wall comprising:an anchor shaft,an anchor coupled to a distal end of the anchor shaft wherein the anchor is deployed within a vessel lumen and moved into contact with an inner surface of a vessel wall,a heating element for passing over the anchor shaft to a position a predetermined distance from the anchor, wherein the heating element is not within the vessel lumen, andwherein tissue is compressed between the anchor and the heating element during activation of the heating element.2. The apparatus of claim 1 , wherein the anchor is selected from the group consisting of a balloon claim 1 , a T-anchor claim 1 , an expansible cage claim 1 , a floating anchor claim 1 , and combinations thereof.3. The apparatus of claim 1 , further comprising a positioning device passing over the anchor shaft.4. The apparatus of claim 3 , wherein the positioning device is selected from the group consisting of a balloon claim 3 , a sponge claim 3 , an expansible cage claim 3 , and combinations thereof.5. The ...

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Номер записи: 42
23-05-2013 дата публикации

GAS TURBINE ROTOR COMPRISING AN AXIALLY DISPLACEABLE TURBINE ROTOR SHAFT

Номер: US20130129478A1
Автор: Braun Stefan, Butzeck Christopher, Hahn Jürgen, Schröder Peter, Wigger Hubertus Michael
Принадлежит:

A gas turbine rotor for a gas turbine is provided. The gas turbine rotor includes a compressor rotor shaft, a turbine rotor shaft and a coupling device frictionally connecting the two rotor shafts, wherein the coupling device is designed in such a way that the friction connection also exists when the two rotor shafts are displaced relative to one another. In this case, the turbine rotor shaft is lengthened at the end facing the compressor rotor shaft in such a way that said turbine rotor shaft overlaps with the compressor rotor shaft in the axial direction and the coupling device connects this lengthened end of the turbine shaft to the compressor rotor shaft in the radial direction. 18-. (canceled)9. A gas turbine rotor for a gas turbine , comprising:a compressor rotor shaft;a turbine rotor shaft displaced axially in relation to the compressor rotor shaft; anda coupling device which constantly connects the compressor rotor shaft with the turbine rotor shaftwherein the compressor rotor shaft is a hollow shaft through which the turbine rotor shaft is guided, such that it completely overlaps the compressor rotor shaft10. The gas turbine rotor as claimed in claim 9 ,wherein the coupling device is a splined shaft connection, one splined shaft rim of which extends in the circumferential direction over an inner face of the compressor rotor shaft formed as a hollow shaft, and the second splined shaft rim of which, corresponding to the first splined shaft rim, extends in the circumferential direction over the outer face of the lengthened end of the turbine rotor shaft.11. The gas turbine rotor as claimed inwherein the coupling device comprises two regions for connecting the compressor rotor shaft and the turbine rotor shaft in a force-fitting manner, andwherein the first region is located at one end of the compressor rotor shaft and the second region is located at the second end of the compressor rotor shaft.12. The gas turbine rotor as claimed inwherein the coupling device ...

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Номер записи: 43
30-05-2013 дата публикации

Cylinder Head Rocker Arm Stand Repair and Process

Номер: US20130133196A1
Автор: Bach Christopher, Bridges Michael, Graham Curtis, Simpson Trent
Принадлежит: CATERPILLAR INC.

A process for remanufacturing a cylinder head that includes a worn or damaged rocker arm stand adapted to receive a rocker shaft to which at least one rocker arm is mounted, the steps including machining a channel in a surface of the worn or damaged rocker arm stand, securing an insert into the channel, and machining the insert to form a remanufactured inner facing surface. The remanufactured cylinder head includes at least one rocker arm stand that has a machined channel with a remanufactured insert secured therein, the rocker shaft being disposed adjacent the inner facing surface, not the rocker arm stand. 1. A process for remanufacturing a cylinder head including a worn or damaged rocker arm stand adapted to receive a rocker arm shaft having an axis to which at least one rocker arm is mounted , the process comprising the steps ofmachining a channel in a surface of the rocker arm stand adapted to be disposed adjacent the rocker arm shaft in the worn or damaged cylinder head, the channel extending generally parallel to the axis,securing an insert into the channel, andmachining the insert to form a remanufactured inner facing surface adapted to receive the rocker arm shaft, the rocker arm shaft being disposed adjacent the inner facing surface, but not adjacent the rocker arm stand.2. The process of wherein the securing step includes the step of at least one of providing a retention substance between the insert and the channel or mechanically fastening the insert within the channel.3. The process of wherein the securing step includes positioning an insert including an outer facing surface adapted to closely fit the channel.4. The process of wherein the rocker arm stand includes side faces disposed substantially normal to an axis of the rocker arm shaft when assembled claim 1 , and the securing step includes positioning the insert to dispose at least one flange of the insert along at least one of the rocker arm stand side faces.5. The process of further including a ...

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Номер записи: 44
06-06-2013 дата публикации

Radial flow steam turbine

Номер: US20130142638A1
Автор: Teruhiko Ohbo
Принадлежит: Individual

Provided is a high-efficiency, realistic, radial flow steam turbine such that the steam supply method is simplified, and that a sufficient amount of steam is supplied to the interior of a turbine unit which is additionally provided in the axial direction. The radial flow steam turbine is equipped with a rotation shaft; a rotor disk connected to the rotation shaft; rotor blades are mounted on the rotor disk; stator disks which face the rotor disk are supported by a casing by being fixed thereto; stator blades are mounted on the stator disk; and an operating steam circulation path is formed wherein the rotor blades on the rotor disk and the stator blades on the stator disk are alternately disposed in the radial direction, and wherein the flow direction of operating steam is in a radial direction which is outward with respect to the rotation shaft. Also, the radial flow steam turbine is configured in such a way that the steam supplied by a steam supply source is circulated as operating steam in the operating steam path, and that thereby the rotor disk and the rotation shaft are rotated. In this radial flow steam turbine, openings are provided in those areas of the rotor disk in the vicinity of the rotation shaft, with the result that an axial steam supply passage is secured.

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Номер записи: 45
06-06-2013 дата публикации

APPARATUS FOR FORMING FILMS ON SUBSTRATES

Номер: US20130142955A1
Автор: Lambert Stephen Mark, Leung Peter Wing, Mullins Dennis, Ta Cuong Manh
Принадлежит: INTERMOLECULAR, INC.

A doctor blade assembly for use in combination with apparatus for forming a film on a substrate. The doctor blade assembly includes a doctor blade to be mounted on a programmable robot. The doctor blade has a bottom face and spacers at opposite ends of the body of the doctor blade extending a predetermined distance down below the bottom face of the body for contacting a substrate and spacing the bottom face from the substrate. The spacers are adjustable relative to the doctor blade for adjusting the predetermined distance according to the thickness of film to be formed on the substrate. Other aspects and methods are also disclosed. 1. Apparatus for forming films on substrates , comprising:a doctor blade,a programmable robot for moving the doctor blade along X, Y and Z axes, the X and Y-axes being generally horizontal and the Z axis being generally vertical, anda flexible coupling for coupling the doctor blade to the robot, said flexible coupling being configured for exerting a downward force on the doctor blade as it moves along a substrate during the formation of a film on the substrate.2. Apparatus as set forth in wherein said downward force is a spring force having a vertical component and a horizontal component.3. Apparatus as set forth in wherein said flexible coupling comprises a spring member having a longitudinal axis.4. Apparatus as set forth in wherein said spring member is adapted to bend along its longitudinal axis as it exerts said downward force on the doctor blade.5. Apparatus as set forth in wherein said spring member has a releasable connection with said doctor blade.6. Apparatus as set forth in wherein said doctor blade comprises a body having a bottom face adapted to be spaced a predetermined distance from the substrate to form a gap between the bottom surface and the substrate generally corresponding to the thickness of the film to be formed on the substrate claim 3 , and wherein said bottom face lies in a plane oblique to the longitudinal axis ...

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Номер записи: 46
13-06-2013 дата публикации

PROCESS FOR ADJUSTING THE RELATIVE POSITION OF A FIRST AND A SECOND PIECE OF A MECHANICAL ASSEMBLY

Номер: US20130145811A1
Автор: Bourban Stewes, DUBACH Alban, Winkler Yves
Принадлежит: The Swatch Group Research and Development Ltd

A process for adjusting a device including a first piece and at least one second piece, wherein the at least one second piece is fixed to the first piece by a joint made from a first material arranged between the first and second piece. The first material is an at least partially amorphous metal alloy. The process further includes: heating at least the joint to a heating temperature in a range of between a glass transition temperature and a crystallisation temperature of the first material; modifying a position of the at least one second piece until a desired determined position is obtained; cooling at least the joint so that it retains its at least partially amorphous state. 19-. (canceled)10. A process for adjusting a device comprising a first piece and at least one second piece , comprising:fixing said at least one second piece to the first piece by a joint made from a first material arranged between said first and second pieces, wherein said first material is an at least partially amorphous metal alloy;heating at least said joint to a heating temperature in a range of between a glass transition temperature and a crystallisation temperature of the first material;modifying a position of said at least one second piece until a desired determined position is obtained;cooling at least said joint so that it retains its at least partially amorphous state.11. The process according to claim 10 , wherein said first material is completely amorphous.12. The process according to claim 10 , wherein said metal alloy comprises at least one precious metal element selected from the group consisting of gold claim 10 , platinum claim 10 , palladium claim 10 , rhenium claim 10 , ruthenium claim 10 , rhodium claim 10 , silver claim 10 , iridium or osmium.13. The process according to claim 11 , wherein said metal alloy comprises at least one precious metal element selected from the group consisting of gold claim 11 , platinum claim 11 , palladium claim 11 , rhenium claim 11 , ruthenium ...

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Номер записи: 47
20-06-2013 дата публикации

BATTERY-POWERED MOTORIZED WINDOW TREATMENT HAVING A SERVICE POSITION

Номер: US20130153162A1
Автор: Blair Edward J., Chambers Samuel F., JR. Peter W., Kirby David A., Ogden, WILSON JAMES J., Zernhelt Justin M.
Принадлежит: LUTRON ELECTRONICS CO., INC.

A battery-powered motorized window treatment for covering at least a portion of a window may be adjusted into a service position to allow for access to at least one battery that is powering the motorized window treatment. A headrail of the motorized window treatment may be adjusted to the service position to allow for easy replacement of the batteries without unmounting the headrail and without requiring tools. The motorized window treatment may comprise brackets having buttons that may be actuated to release the headrail from a locked position, such that the head rail may be rotated into the service position. The headrail easily rotates through a controlled movement into the service position, such that a user only needs one free hand available to move the motorized window treatment into the service position and change the batteries. 1. A battery-powered motorized window treatment adapted to be mounted to a surface for covering at least a portion of a window , the motorized window treatment comprising:a covering material;a motor drive unit adapted to be disposed near a top of the window for controlling the covering material between a fully-opened and a fully-closed position;an enclosure adapted to be disposed near the top of the window, the enclosure including a compartment for receiving at least one battery for powering the motor drive unit; andat least one mounting bracket for coupling the enclosure to the surface;wherein the motorized window treatment is operable to be adjusted into a service position in which access is provided to the at least one battery, the mounting bracket remaining coupled to the surface and the enclosure remaining coupled to the mounting bracket when the motorized window treatment is in the service position.2. The motorized window treatment of claim 1 , wherein the mounting bracket comprises a mounting portion adapted to be fastened to the surface and a rotating portion coupled to the enclosure claim 1 , the rotating portion adapted to ...

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Номер записи: 48
20-06-2013 дата публикации

RETROFITTING METHODS AND DEVICES FOR LARGE STEAM TURBINES

Номер: US20130156587A1
Автор: Hunziker Rolf, Kubel Sigurd
Принадлежит: ALSTOM Technology Ltd

A method of replacing rotating metal blades of a steam turbine inserted into a rotor having one or more existing grooves for inserting root sections of the metal blades is described, the method including the steps of providing replacement blades having radially inwards directed root sections of fiber-reinforced composite material, changing the shape of the one or more grooves in the rotor to form a cavity for the insertion of the root sections of fiber-reinforced composite material and inserting the replacement blades into the rotor. 1. A method of replacing rotating metal blades of a steam turbine inserted into a rotor having at least one existing groove configured to receive root sections of the metal blades , the method comprising:providing replacement blades having radially inwards directed root sections of fiber-reinforced composite material;changing a shape of the at least one groove in the rotor to provide cavities for the insertion of the root sections of fiber-reinforced composite material; andinserting the replacement blades into the rotor.2. The method of wherein the shape of the at least one existing groove is changed by machining an altered groove profile into the rotor and/or by inserting adapters into the existing grooves.3. The method of wherein the at least one existing groove have several teeth or hooks and the shape of the at least one existing groove is changed by machining an altered groove profile into the rotor such that at least the top and the bottom teeth remain without significant alterations and the adapter is hooked onto the remaining at least the top and the bottom teeth.4. The method of wherein the root sections of fiber-reinforced composite material extend into the altered groove profile in the rotor and/or the adapters such that the end sections are separated from steam in the turbine by at least one layer of metal.5. The method of wherein a transition between fiber-reinforced composite material of the root section of the blades and ...

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Номер записи: 49
27-06-2013 дата публикации

METHOD OF SERVICING A GAS TURBINE ENGINE

Номер: US20130160291A1
Автор: BROUGHTON Paul, PEACE Richard
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine 10 is provided with rigid raft assemblies 290, which may be electrical harness raft assemblies 290 comprising electrical conductors embedded in a rigid composite material. The rigid raft assemblies 290 can be provided with engine dressings, such as pipework and ECUs to produce an electrical raft assembly. In order to assemble or dress the gas turbine engine 10, the rigid raft assemblies can be pre-prepared to incorporate at least a part of at least one gas turbine engine system/component before being installed on the gas turbine engine 10. During maintenance, whole raft assemblies can be removed and replaced with corresponding, pre-prepared assemblies. This can save considerable time during engine build and maintenance. 1. A method of servicing a gas turbine engine , the method comprising:removing a first rigid raft assembly from the gas turbine engine, the rigid raft assembly incorporating at least a part of at least one component or system of the gas turbine engine; andinstalling a second, pre-prepared, rigid raft assembly onto the gas turbine engine in place of the first raft assembly.2. A method of servicing a gas turbine engine according to claim 1 , wherein the first and second rigid raft assemblies are electrical harness raft assemblies having electrical conductors embedded in a rigid material claim 1 , the electrical conductors being at least a part of an electrical system arranged to transfer electrical signals around the engine.3. A method of servicing a gas turbine engine according to claim 1 , wherein the first and second rigid raft assemblies are dressed rigid raft assemblies comprising a rigid mounting surface on which at least a part of at least one of the components or systems of the gas turbine engine is mounted.4. A method of servicing a gas turbine engine according to claim 3 , wherein the rigid mounting surface of each of the first and second rigid raft assemblies has a pipe for transferring fluid around the engine attached ...

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Номер записи: 50
27-06-2013 дата публикации

ADSORPTION HEAD FOR SURFACE MOUNTING DEVICE

Номер: US20130160293A1
Автор: SUSUMU Kitada
Принадлежит: SAMSUNG TECHWIN CO., LTD.

An adsorption head for a surface mounting device, including: a main body; a shaft which moves in a direction of a longitudinal axis of the shaft and rotates around the longitudinal axis mounted on the main body, and the shaft includes a lower shaft and an upper shaft. The lower shaft is detachably attached to the upper shaft; and an adsorption nozzle which adsorbs electronic parts mounted on a lower end of the shaft, wherein an air passage connected to the adsorption nozzle is provided in the lower shaft. 1. An adsorption head for a surface mounting device , comprising:a main body;a shaft which moves in a direction of a longitudinal axis of the shaft and rotates around the longitudinal axis mounted on the main body,wherein the shaft comprises a lower shaft and an upper shaft, andwherein the lower shaft is detachably attached to the upper shaft; andan adsorption nozzle which adsorbs electronic parts mounted on a lower end of the shaft,wherein an air passage connected to the adsorption nozzle is provided in the lower shaft.2. The adsorption head of claim 1 , wherein if the lower shaft is detached from the upper shaft claim 1 , the lower shaft is detached from the main body.3. The adsorption head of claim 1 , wherein the lower shaft comprises joint pins disposed at an upper end of the lower shaft claim 1 , and the upper shaft comprises joint holes disposed at a lower end of the upper shaft claim 1 , andwherein the lower shaft is detachably attached to the upper shaft if the joint pins are inserted through the joint holes.4. The adsorption head of claim 2 , wherein the lower shaft comprises joint pins disposed at an upper end of the lower shaft claim 2 , and the upper shaft comprises joint holes disposed at a lower end of the upper shaft claim 2 , andwherein the lower shaft is detachably attached to the upper shaft if the joint pins are inserted through the joint holes.5. The adsorption head of claim 3 , wherein a motion for inserting the joint pins through the joint ...

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Номер записи: 51
27-06-2013 дата публикации

AERODYNAMIC SHROUD FOR THE BACK OF A COMBUSTION CHAMBER OF A TURBOMACHINE

Номер: US20130160452A1
Автор: Bourgois Sebastien Alain Christophe, Hernandez Didier Hippolyte
Принадлежит: SNECMA

An annular shroud has an internal face intended to cover the back end wall of an annular combustion chamber of a turbomachine fitted with a centrifugal compressor, together with an external face opposite the internal face. The shroud includes multiple apertures intended to allow fuel injectors supported by the back end wall to pass through. The shroud includes multiple bosses which extend as projections on the external face radially towards the interior respectively from the respective radially internal edges of the apertures. Each of the bosses delimits an extension of the corresponding aperture open radially towards the exterior so as to form an air intake scoop. 18-. (canceled)9. An annular shroud , comprising:an internal face to cover the back end wall of an annular combustion chamber of a turbomachine fitted with a centrifugal compressor;an external face opposite said internal face;multiple apertures to allow fuel injectors supported by said back end wall of the combustion chamber to pass through; andmultiple bosses which extend as projections on said external face of the shroud, radially towards the interior respectively from the respective radially internal edges of said apertures, such that each of said bosses delimits an extension of the corresponding aperture open radially towards the exterior so as to form an air intake scoop.10. The annular shroud according to claim 9 , wherein said bosses extend as far as a radially internal end of said shroud.11. The annular shroud according to claim 9 , wherein each of said bosses has a radial plane of symmetry including a central axis of said shroud and an axis of injection of the corresponding aperture.12. The annual shroud according to claim 9 , wherein said extension of each of said apertures has a protrusion offset circumferentially relative to an axis of injection of the aperture.13. An annular combustion chamber to be installed downstream from a centrifugal compressor in a turbomachine claim 9 , comprising:two ...

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Номер записи: 52
27-06-2013 дата публикации

GAS TURBINE ENGINE WITH SUPERSONIC COMPRESSOR

Номер: US20130160454A1
Автор: LAWLOR SHAWN P., ROBERTS II WILLIAM BYRON
Принадлежит: RAMGEN POWER SYSTEMS, LLC

A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct. 1. A gas turbine engine , comprising: (1) an inlet for supply of a selected oxidant-containing gas;', '(2) a rotor extending along a longitudinal axis, the rotor comprising a plurality of impulse blades configured to act on said selected oxidant-containing gas to impart axial and tangential velocity thereto to provide a supersonic gas flow;', (i) one or more aerodynamic ducts each having a converging portion and a diverging portion that, with input of said supersonic gas flow, generate a plurality of shock waves as said oxidant-containing gas passes through said one or more aerodynamic ducts, each of said one or more aerodynamic ducts sized and shaped to decelerate said supersonic gas flow to subsonic conditions,', '(ii) bypass gas passageway(s) or a geometrically adjustable portion, or both, operable to adjust the effective contraction ratio of some or all of said one or more aerodynamic ducts, and', '(iii) boundary layer control structures;, '(3) a stator, said stator comprising'}], '(a) a compressor section, said compressor section comprising (1) a high pressure combustion chamber for receiving said selected oxidant containing gas from said compressor section,', '(2) a combustor for receiving fuel from a fuel supply and said selected oxidant containing gas ...

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Номер записи: 53
27-06-2013 дата публикации

SYSTEM AND METHOD OF EXPANDING A FLUID IN A HERMETICALLY-SEALED CASING

Номер: US20130160455A1
Автор: Dourlens Herve, Leconte Patrice, Mullier Jean-Pierre G.
Принадлежит: DRESSER-RAND COMPANY

An expander-generator is disclosed. The expander-generator is disposed within a hermetically-sealed housing and includes a high-pressure expander stage and a low-pressure expander stage. A working fluid, such as ammonia, is introduced into the high and low pressure expander stages and expanded therein so as to provide rotational torque to a shaft. A generator, such as a motor, pump, or compressor, may be coupled to a free end of the shaft such that rotation of the shaft will provide useful work for the generator. 1. An expander-generator , comprising:a hermetically-sealed housing having a rotatable shaft disposed therein, the rotatable shaft having a free end and extending from a first end of the housing to a second end of the housing;a high pressure expander section rotatably disposed on the shaft and configured to receive and expand a working fluid and discharge the working fluid via a high pressure discharge defined within the housing, thus imparting rotational motion to the shaft;a low pressure expander section rotatably disposed on the shaft and axially-offset from the high pressure expander section and in fluid communication with the high pressure expander section via the high pressure discharge, wherein the low pressure expander is configured to receive and further expand the working fluid derived from the high pressure discharge to impart additional rotational motion to the shaft; anda generator coupled to the free end of the rotatable shaft, wherein the working fluid is expanded to rotate the shaft and thereby generate rotational shaft power to be used by the generator to generate electrical.2. The expander-generator of claim 1 , wherein the high pressure expander section and the low pressure expander section are configured in a back-to-back arrangement along the shaft.3. The expander-generator of claim 1 , wherein the working fluid is ammonia4. The expander-generator of claim 1 , wherein the working fluid remains in a gaseous state throughout expansion in ...

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Номер записи: 54
27-06-2013 дата публикации

RAFT ASSEMBLY

Номер: US20130160463A1
Автор: BROUGHTON Paul, KENNEA Robin Charles, PEACE Richard, SKINNER Gary Alan
Принадлежит: ROLLS-ROYCE PLC

A raft assembly for a gas turbine engine is provided. The raft assembly includes a rigid raft formed of a rigid material that has an electrical system and/or a fluid system embedded therein. The raft assembly further includes one or more clamps for mounting tubular members to the raft. The or each clamp has a first clamp block and a second clamp block which, in use, clamp together to grip a tubular member between the blocks. The first block is fixed to the raft. The or each clamp further has a fastener operatively extending between the blocks. The fastener is tightenable to apply a clamping load between the blocks, and releasable to remove the clamping load such that the second block can be moved relative to the first block to allow the tubular member to be received between or removed from between the blocks 1. A raft assembly for a gas turbine engine , the raft assembly comprising:a rigid raft formed of a rigid material that has an electrical system and/or a fluid system embedded therein, and one or more clamps for mounting tubular members to the raft;wherein the or each clamp has:a first clamp block and a second clamp block which, in use, clamp together to grip a tubular member between the blocks, the first block being fixed to the rigid raft, anda fastener operatively extending between the blocks, the fastener being tightenable to apply a clamping load between the blocks, and releasable to remove the clamping load such that the second block can be moved relative to the first block to allow the tubular member to be received between or removed from between the blocks.2. A raft assembly according to claim 1 , wherein the raft assembly is an electrical raft assembly that includes an electrical system comprising electrical conductors embedded in the rigid material.3. An electrical raft assembly according to claim 1 , wherein the rigid material is a rigid composite material.4. A raft assembly according to claim 1 , wherein the first block is integrally formed with the ...

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Номер записи: 55
27-06-2013 дата публикации

GAS TURBINE ENGINE SYSTEMS

Номер: US20130160465A1
Автор: BROUGHTON Paul, KENNEA Robin Charles, PEACE Richard, SKINNER Gary Alan
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprises at least one rigid raft assembly that has a fluid passageway at least partially embedded therein. The fluid passageway is at least a part of a fluid system. In addition to the fluid passageway the rigid raft assembly also has at least a part of another system. For example, the rigid raft assembly may also include electrical conductors which are part of an electrical system. The rigid raft assembly may be lighter, easier to assemble, more robust and more compact than conventional solutions for providing systems to gas turbine engines. 1. A rigid raft assembly for a gas turbine engine , the rigid raft assembly comprising a rigid material that carries at least a part of a first gas turbine engine system and at least a part of a second gas turbine engine system , wherein:the first gas turbine engine system is a fluid system that comprises at least one fluid passage that is at least partially embedded in the rigid raft assembly.2. A rigid raft assembly according to claim 1 , wherein:the second gas turbine engine system is an electrical system that comprises electrical conductors at least partially embedded in the rigid material.3. A rigid raft assembly according to claim 1 , wherein:the fluid passage has an axial direction (p) along which, in use, fluid flows; andthe rigid material surrounds the fluid passage over at least one axial portion of the passage.4. A rigid raft assembly according to claim 1 , wherein the fluid passage is formed by a fluid pipe that is at least partially embedded in the rigid raft assembly.5. A rigid raft assembly according to claim 1 , wherein the fluid passage is formed by the rigid material.6. A rigid raft assembly according to claim 4 , wherein:the rigid raft assembly comprises two rigid rafts formed by the rigid material; andthe fluid pipe is embedded between the two rigid rafts.7. A rigid raft assembly according to claim 6 , wherein:the rigid rafts are thin elements having an upper major surface separated by ...

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Номер записи: 56
04-07-2013 дата публикации

REGENERATING METHOD OF CUTTING BLADE AND ITS REGENERATING EQUIPMENT

Номер: US20130167349A1
Автор: AZUI Yoshinobu, HONDA Yasuhiko, MATSUMOTO Katsu, NAGAI Isao, TAKAMI Keita, TAKEMOTO Natsuki, WADA Naoya, YASUKAWA Tetsuo
Принадлежит: Kabushiki Kaisha Kinki

A regenerating method of a cutting blade to be repaired includes a grouping step of dividing the cutting blade differing in the degree of abrasion of the leading end part and side edge parts, into groups A to E depending on the degree of abrasion, a chamfering step of chamfering the leading edge part and the side edge parts of the cutting blade belonging to groups A to D, to positions passing reference lines K, K, - - - , K built up to a specified height determined in each group, a build-up welding step of welding a build-up on the chamfered leading edge part and side edge parts, and a processing step of regenerating and processing the build-up welding portions of the cutting blade into a specified shape of leading edge part and side edge parts. 1. A regenerating method of a cutting blade to be repaired , having a fixed part , and a blade tip projecting outward from this fixed part , the blade tip having a leading edge part pointed toward a rotational direction , and having side edge parts at the side outer edge including the leading end , comprising:a grouping step of dividing the cutting blade differing in the degree of abrasion of the leading end part and side edge parts, into a plurality of groups depending on the degree of abrasion,a chamfering step of chamfering the leading edge part and the side edge parts of the cutting blade belonging to individual groups, to positions passing reference lines or reference planes as the reference of height of building up determined in each group,a build-up welding step of welding a build-up on the chamfered leading edge part and side edge parts, anda processing step of regenerating and processing the build-up welding portions of the cutting blade into a specified shape of leading edge part and side edge parts.2. The regenerating method of a cutting blade according to claim 1 , wherein the build-up welding step is to build up and weld to a specified build-up height determined in each group claim 1 , in the leading edge part ...

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Номер записи: 57
04-07-2013 дата публикации

Adjustable Pitch Link

Номер: US20130168492A1
Автор: Biser Joseph, Day Clifton B., Spivey Daniel, Stamps Frank B.
Принадлежит: Bell Helicopter Textron Inc.

According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link. 1. A rotorcraft , comprising:a body;a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;a hub coupled to the drive shaft;a rotor blade coupled to the hub;a swashplate positioned about the drive shaft; and a link assembly having an overall adjustable length, the link assembly comprising a first link, a second link coupled to a first end of the first link, and a third link coupled to a second end of the first link opposite the first end;', 'a first bearing housing having a first bearing, the first bearing housing removably coupled to the second link, the second link separating the first bearing housing from the first link; and', 'a second bearing housing having a second bearing, the second bearing housing removably coupled to the third link, the third link separating the second bearing housing from the first link., 'a pitch link coupled between the swashplate and the hub corresponding to the rotor blade, the pitch link comprising2. The rotorcraft of claim 1 , further comprising:a first jam nut coupling the first link to the second link; anda second jam nut coupling the first link to the third link.3. The rotorcraft of claim 2 , wherein the overall adjustable length is adjustable by adjusting at least one of the first jam nut and the second jam nut.4. The rotorcraft of claim 1 , wherein the second link separates the first bearing housing ...

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Номер записи: 58
04-07-2013 дата публикации

High Pressure Compressor

Номер: US20130170954A1
Автор: Pauli Ernst, Seng Daniel, Shchukin Sergey
Принадлежит: ALSTOM TECHNOLOGY LTD.

A high-pressure compressor (), in particular in a gas turbine (), has a compressor rotor () which is surrounded by a stator () thereby forming a main flow channel () and which is delimited at the compressor outlet by an end face () substantially extending in the radial direction, along which end face cooling air () is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face () is provided with a first system () for improving the heat transfer between the cooling air () and the end face (). 1. A high-pressure compressor comprising:a compressor rotor and a compressor stator surrounding the rotor thereby forming a main flow channel therebetween;a compressor outlet; anda rotor end face at the compressor outlet extending in a radial direction, along which end face cooling air can be conveyed in the radial direction for cooling;wherein the end face comprises first means for improving the heat transfer between the cooling air and the end face.2. The high-pressure compressor according to claim 1 , wherein the means for improving the heat transfer between the cooling air and the end face comprises claim 1 , on the end face claim 1 , a plurality of radially oriented blades which are circumferentially distributed and form cooling channels between each other for conveying the cooling air.3. The high-pressure compressor according to claim 2 , wherein the plurality of blades are molded onto the compressor rotor.4. The high-pressure compressor according to claim 2 , wherein the each of the plurality of blades is formed curved counter to a rotational direction (ω) of the compressor rotor.5. The high-pressure compressor according to claim 4 , wherein a curvature of each of the plurality of blades follows a parabola claim 4 , a hyperbola claim 4 , or a polynomial function.6. The high-pressure compressor according to claim 1 , further comprising:second means for imposing a tangential speed component in the rotational ...

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Номер записи: 59
11-07-2013 дата публикации

COMBUSTOR FOR A GAS TURBINE ENGINE

Номер: US20130174557A1
Автор: SPOONER Michael Paul
Принадлежит: ROLLS-ROYCE PLC

A combustor in a gas turbine engine has a wall which forms a gap with an outer nozzle guide vane platform. A closure mechanism is operable to open or close the gap. Opening of the gap, for example during cruise conditions, reduces the mass flow rate of air through an open end of the combustor, so enriching the air fuel ratio and improving flame stability and combustion efficiency. Under high power conditions, the gap is closed, causing an increase in air flow rate through the open end to achieve a lean burn air fuel ratio when the fuel flow rate is increased. 1. A combustor for a gas turbine engine , the combustor comprising a housing having a circumferential wall defining a circumferential gap which provides communication between the interior and the exterior of the housing , an annular closure mechanism provided which is displaceable into and out of a closing relationship with the gap.2. A combustor as claimed in claim 1 , in which the closure mechanism comprises an actuator device which is displaceable radially with respect to the axis of the housing.3. A combustor as claimed in claim 2 , in which the actuator device comprises an array of arcuate actuator elements extending circumferentially of the housing.4. A combustor as claimed in claim 3 , in which the actuator elements are displaceable by a common control mechanism.5. A combustor as claimed in claim 3 , in which adjacent circumferential edges of adjacent actuator elements engage one another in a sealing manner.6. A combustor as claimed in claim 1 , in which an annular sealing element is disposed between the housing and the closure mechanism.7. A combustor as claimed in claim 6 , in which the sealing element comprises an annular leaf spring.8. A combustor as claimed in claim 6 , in which the sealing element comprises a retaining portion mounted on the housing and a sealing lip which is displaceable relative to the retaining portion for engagement with the closure mechanism.9. A combustor as claimed in claim ...

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Номер записи: 60
11-07-2013 дата публикации

Rotor, a steam turbine and a method for producing a rotor

Номер: US20130177407A1
Автор: Robin Carl Schwant, Thomas Joseph Farineau
Принадлежит: General Electric Co

A rotor, a steam turbine having a rotor, and a method of producing a rotor are disclosed. The rotor disclosed includes a shaft high pressure section. The high pressure section includes a first high pressure section, a second high pressure section, the second high pressure section being joined to the first pressure section, and a third high pressure section, the third high pressure section being joined to the second high pressure section. At least a portion of the second high pressure section is formed of a high-chromium alloy steel comprising 0.1-1.2 wt % of Mn, up to 1.5 wt % of Ni, 8.0-15.0 wt % of Cr, up to 4.0 wt % of Co, 0.5-3.0 wt % of Mo, 0.05-1.0 wt % of V, 0.02-0.5 wt % of Cb, 0.005-0.15 wt % of N, up to 0.04 wt % of B, up to 3.0 wt % of W, and balance Fe and incidental impurities.

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Номер записи: 61
25-07-2013 дата публикации

GAS TURBINE ENGINE COMPRISING MEANS FOR AXIALLY RETAINING A FAN OF THE ENGINE

Номер: US20130186056A1
Автор: Balk Wouter, Gerez Valerio, Jadczak Edouard Joseph
Принадлежит: SNECMA

A gas turbine engine including: a casing in which is mounted at least one shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; and an axial retention mechanism, on standby, solidly connected to the casing and arranged to come into contact with the driving drum such as to prevent axial movement of the drum in event of breakage of the driving shaft. 110-. (canceled)11. A gas turbine engine comprising:a casing including at least one mounted shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; andan axial retention means, on standby, solidly connected to the casing and configured to come into contact with the driving drum so as to prevent axial movement of the driving drum in event of breakage of the driving shaft.12. An engine according to claim 11 , in which the driving drum includes stop means configured to come into contact with the axial retention means claim 11 , the stop means being formed by a downstream part of the driving drum claim 11 , or a downstream end of the driving drum.13. An engine according to claim 12 , in which the stop means extends radially towards an inside of the engine.14. An engine according to one of claim 11 , in which the axial retention means claim 11 , on standby claim 11 , extends into the driving drum.15. An engine according to claim 14 , in which the driving drum includes a radially convex part claim 14 , the axial retention means claim 14 , on standby claim 14 , facing the convex part.16. An engine according to claim 11 , in which the axial retention means includes at least one retention dog longitudinally aligned with a downstream part of the driving drum so as to prevent the axial movement of the driving drum in the event of breakage of the driving shaft.17. An engine according to claim 11 , in which the axial retention means includes an ...

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Номер записи: 62
01-08-2013 дата публикации

Incubation system with low temperature enclosure

Номер: US20130192036A1
Автор: David M. Robbins, Jacky Yam, James C. Bishop, Kevin G. Ketsenburg, Mark J. Fanning
Принадлежит: Biomerieux Inc

An incubator is fitted with an enclosure which surrounds the incubator. A cold air generation system supplies relatively cold air to a space formed between enclosure and the incubator. The system supplying the cold air can be embodied in a cart or base upon which the incubator sits. The enclosure is also placed on the base in a manner such that it substantially envelops the incubator. The top of the cart has openings for egress of cold air and return of air so that air may circulate in a closed loop. The incubator, cold air supply system and enclosure present a solution for incubating samples in a nominal 20-25° C. temperature environment. The enclosure, which is preferably insulated, may include a void or opening which exposes doors or other access device of the incubator, allowing direct access to the samples in the incubator while the rest of the incubator is enveloped by the enclosure.

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Номер записи: 63
01-08-2013 дата публикации

Split Sleeve Shaft Repair

Номер: US20130192037A1
Автор: Mike Muilenburg
Принадлежит: Individual

A sleeve for use in repairing a shaft having an unworn diameter and a worn diameter, the sleeve providing a fresh bearing surface for a split roller bearing, comprising: two halves which, when joined, define a cylinder having a diameter adapted to firmly engage a portion of unworn diameter shaft at each end; bolts holes adapted to releasably affix the halves together, and bolts adapted to attach the halves thereby; joiner pin holes defined in at least one intersection between the halves, the joiner holes adapted to receive joiner pins therein and adapted to serve as a stable joinder point for the halves, and joiner pins adapted to be firmly engaged therein; a smooth bearing surface defined on an external surface of the sleeve; and a split roller bearing adapted to engage the bearing surface. A method for field manufacture of said sleeve.

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Номер записи: 64
08-08-2013 дата публикации

METHOD FOR MANUFACTURING A COMPONENT BY SELECTIVE LASER MELTING

Номер: US20130199013A1
Автор: Graichen Andreas
Принадлежит:

A method of manufacturing a component by selective laser melting and to provide heat treatment to the component is provided. The method includes building a heat treatment device adapted to provide a heat treatment to the component as part of the same selective laser melting for manufacturing the component and providing a heat treatment to the component by the heat treatment device. 115-. (canceled)16. A method for manufacturing a component by selective laser melting , comprising:building a heat treatment device adapted to provide a heat treatment to the component as part of the same selective laser melting for manufacturing the component; andproviding a heat treatment to the component by the heat treatment device.17. The method according to claim 16 ,wherein the heat treatment device is spatially positioned in relation to the component, such that the heat treatment device is adapted to provide the heat treatment to the component.18. The method according to claim 16 ,wherein the component is made of an electrically and thermally conductive material.19. The method according to claim 16 ,wherein the heat treatment device is coil shaped.20. The method according to claim 16 ,wherein the coil shaped heat treatment device circumferentially encircles the component.21. The method according to claim 16 ,wherein the component is manufactured onto a device, for repairing the device.22. The method according to claim 21 , further comprising:providing cooling to the device by a cooling arrangement.23. The method according to claim 22 ,wherein the cooling arrangement further comprises a holder for holding the component and having an integrated cooling channel through which a cooling medium flows.24. The method according to claim 23 ,wherein the holder is made of an electrically and magnetically insulating material.25. The method according to claim 22 ,wherein cooling is provided to the device during SLM of the component and heat treatment of the component.26. The method according ...

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Номер записи: 65
08-08-2013 дата публикации

SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE

Номер: US20130199206A1
Автор: Cigal Brian P., David Todd A.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan about an engine central axis, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool. The first spool is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. The turbine section also includes a second turbine coupled through a second spool to drive the second compressor. A sensor probe is operable to determine a rotational speed of the first spool. The sensor probe is located at a third axial position that is axially forward of the first axial position and axially aft of the second axial position. 1. A gas turbine engine comprising:a fan;a fan drive gear system coupled to drive the fan about an engine central axis;a compressor section including a first compressor and a second compressor; a first turbine coupled to drive a first spool, the first spool being coupled at a first axial position to a compressor hub that is coupled to drive the first compressor and the first spool being coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system, and', 'a second turbine coupled through a second spool to drive the second compressor; and, 'a turbine section includinga sensor probe operable to determine a rotational speed of the first spool, the sensor probe being located at a third axial position that is axially forward of the first axial position and axially aft of the second axial position.2. The gas turbine engine as recited in claim 1 , further comprising a fan output shaft coupled to be rotated by the fan drive gear system and coupled at a fourth axial position to the fan claim 1 , the fourth axial position being ...

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Номер записи: 66
08-08-2013 дата публикации

Turbine engine shaft coupling

Номер: US20130202349A1
Автор: James B. Coffin
Принадлежит: United Technologies Corp

A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediate tie shaft segment connected axially between a first tie shaft segment and a second tie shaft segment. The first tie shaft segment includes a first threaded tie shaft surface that is mated with a first threaded shaft surface of the first sub-shaft. The second tie shaft segment includes a second threaded tie shaft surface that is mated with a second threaded shaft surface of the second sub-shaft. The tie shaft also includes a sub-shaft bumper stop extending radially from the intermediate tie shaft segment to a bumper stop distal end, which has a radius that is greater than a radius the first and/or second threaded shaft surfaces.

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Номер записи: 67
08-08-2013 дата публикации

Method and Device for variable motion and applications using Interchangeable Heads

Номер: US20130202401A1
Автор: Taitler Isaac
Принадлежит:

A machine for automating manual labor has a motor portion, transmission portion, and a head portion which may all be interchanged with alternates for different applications. The machine is driven by an electric motor that can perform different motions and actions, one at a time or simultaneously, depending on the transmission and head portions. Two such motions are rotary and linear reciprocating motion. Applications include cleaning surfaces, cleaning vessels, mixer, blender, chopper, slicer, shredder, vibrator, massager, semi and fully automatic milk cream maker. 1. An apparatus for achieving a variety of rotary motion , linear motion and simultaneously rotary and linear motions via two axes used for cleaning dirty , singed and oily surfaces of kitchen utensils and for preparing whipped milk , said apparatus comprising ,a. a motor portion operatively producing a rotational force;b. a transmission mechanism configured to convert said of rotational force of said motor into a preconfigured operational motionc. an interchangeable head-piece having a housing, a distal end and a proximal endd. wherein said preconfigured operational motion is selected for the group consisting of linear motion, rotary motion and a combination of linear and rotary motions;e. wherein said head-piece, coupled with a said respective transmission mechanism, is adopted to receive either a linear motion, or a rotary motion, or a combination of linear and rotary motions;f. wherein said proximal end of said head-piece is securely attached to the housing of said motor;g. wherein said distal end of said head-piece is a functionary portion; and whereinh. the said preconfigured operational motion activates said functionary portioni. head section, said modified motion being selected from the group consisting of: rotational motion; eccentric rotation; linear reciprocating motion; and combinations thereof;j. wherein said motor, head, and transmission portions are replaceable allowing for a variety of ...

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Номер записи: 68
15-08-2013 дата публикации

SECOND WHEEL HOLDER

Номер: US20130205541A1
Автор: ASBO Sven, Backman Erik, Palsson Ingemar
Принадлежит: ASSA ABLOY ENTRANCE SYSTEMS AB

The present invention relates to the field of sliding door systems. The invention relates to a second wheel holder () enabling using a flexible number of wheels in a wheel carriage () for a sliding door resting in sliding track (). The second wheel holder () comprises one attachment means () adapted to be removably attached to the first wheel connection means () and at least two second wheel connection means () each adapted to connect one wheel (). The invention also relates to a method for exchanging the wheels () and of a wheel carriage (), by lowering a door panel and replacing the wheels, by removing the second wheel holder (), while the wheel carriage () is resting in the sliding track (). 1. A second wheel holder , for a wheel carriage holding a sliding door running in a sliding track , said wheel carriage comprising at least two first wheel connection means each adapted to connect one wheel , characterised in that it comprises:one attachment means adapted to be removably attached to one of the first wheel connection means andat least two second wheel connection means each adapted to connect one wheel.2. A second wheel holder according to claim 1 , wherein each second wheel connection means comprises two connection points claim 1 , adapted to be connected to opposite sides of the wheel.3. A second wheel holder according to claim 1 , wherein the second wheel connection means the attachment means are horisontally aligned.4800. A second wheel holder according to claim 1 , wherein the attachment means comprises at least one protrusion on the upper side of the second wheel holder () with a width corresponding to the thickness of a wheel shaft.5. A second wheel holder according to claim 1 , wherein each second wheel connection means comprises at least one recess at the lower side of the second wheel holder with a width corresponding to the thickness of a wheel shaft.7. A second wheel holder according to claim 6 , wherein the attachment means comprises one protrusion ...

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Номер записи: 69
15-08-2013 дата публикации

METHOD FOR PREPARING A BEARING ARRANGEMENT, AND BEARING ARRANGEMENT

Номер: US20130205592A1
Автор: Keller Karl, Roeingh Konrad
Принадлежит: SMS SIEMAG AKTIENGESELLSCHAFT

The invention relates to a method for preparing a bearing arrangement for a roll journal, wherein the bearing arrangement comprises a bearing insert, with a bearing bush, and a journal bush which is mounted with bearing play in the bearing bush and can be pushed onto the roll journal. In order to extend the service life of the bearing arrangement and therefore to save costs, the method according to the invention provides, in order to eliminate scoring, for the external diameter Dof the journal bush also to be reduced below a threshold value Dand at the same time for a novel bearing bush to be supplied which, with regard to its internal diameter D, is adapted to the reduced external diameter of the bearing bush in such a way that the bearing play remains within a predefined permissible value range. 1. Method of preparing a bearing arrangement for a roll journal of a roll for rolling roll goods , wherein the bearing arrangement includes a bearing insert with a bearing bush and a journal bush pushable onto the roll journal and located in the bearing bush with a bearing clearance; andwherein the method is characterized by the following steps:{'sub': a', 'ak', 'i old, 'machining the journal bush with a first time reduction of its outer diameter Dbelow a threshold value D, with this reduction, the bearing clearance between the inner diameter Dof the previous bearing bush and the reduced below its threshold value, enter diameter of the journal bush not any more remaining in an allowable value region, and'}{'sub': i new', 'i new', 'ak, 'providing a new bearing bush with the inner diameter Dbeing so adapted to the reduced outer diameter of the machined journal bush that the bearing clearance between the inner diameter Dof the new bearing bush and the reduced below its threshold value D, outer diameter of the machined journal bush has a value in a predetermined allowable value region.'}2. Method according to claim 1 , characterized in that the predetermined allowable value ...

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Номер записи: 70
15-08-2013 дата публикации

FIRE FIGHTING BUCKET FOR AIRCRAFT

Номер: US20130206430A1
Автор: Zheng Shilan
Принадлежит:

The present invention provides a collapsible firefighting bucket having purse lines that have a pre-set, fixed functional length, and which are removably installed onto a releasable connector at one end of the line and onto a pair of aligned openings on the valve at the other end of the line. The fixed functional length of the purse lines is generally determined by the size of the bucket for which they are intended to be used, and more specifically by each purse line's intended location on the valve. The releasable connector may be a releasable connector clip which is itself connected to the control mechanism that moves the valve. Each purse line includes a pre-formed end-stop for stopping the end from passing through the grommet, and a pre-formed connector or loop portion for removably connecting to the releasable connector. 1. A collapsible fire fighting bucket assembly to be suspended from an aircraft comprising:(a) a harness for suspending the bucket from the aircraft;(b) an open bucket body of pliable material having an open upper rim to facilitate filling from an open body of water, a side wall extending downwardly from the rim and a bottom cooperating with the side wall and having an opening;(c) a tubular extension made of pliable material and extending from the opening in the bottom, the tubular extension having a free end formed with a discharge port to serve as a dump valve, the discharge port having a sealing lip of resilient sealing material which forms two opposite lip portions that are brought into sealing engagement with each other for minimizing water leakage from the tubular extension, the tubular extension having a plurality of aligned openings, each opening being associated with a respective lip portion of the sealing lip for bringing the lip portions into sealing engagement;(d) a plurality of tension lines, each having a first end with a pre-formed end stop and a second end with a pre-formed connector portion, each tension line passing from the ...

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Номер записи: 71
15-08-2013 дата публикации

METHOD FOR REPAIRING OR REINFORCING CUTTER POCKETS OF A DRILL BIT

Номер: US20130206483A1
Автор: Amundsen Marvin Windsor, Johnson Charles Daniel
Принадлежит: Varel International Ind., L.P.

A method for forming pockets of a drill bit includes inserting a displacement plug in a cutter pocket defined by a substrate of a drill bit. A hardfacing material is applied to the substrate and the displacement plug using a plasma arc welding torch. The heat from the plasma arc welding torch reduces an oxide layer on the outer surface of the displacement plug, and the molten hardfacing material flows over the displacement plug and wets against the displacement plug. The displacement plug is then removed to reveal a final cutter pocket configured to receive a cutter compact. The cutter compact is secured to the final cutter pocket by brazing. 1. A method for repairing or reinforcing cutter pockets of a drill bit , comprising:inserting a displacement plug in a cutter pocket formed in a substrate of a drill bit; andapplying a hardfacing material, using a plasma arc welding process, to the substrate, the hardfacing material flowing over and contacting a perimeter surface of the displacement plug.2. The method of claim 1 , further comprising heating the displacement plug using the plasma arc welding process such that an oxide layer on the perimeter surface of the displacement plug is reduced.3. The method of claim 2 , wherein a tip of an electrode within the plasma arc welding torch is heated to approximately 30 claim 2 ,000 degrees Fahrenheit.4. The method of claim 1 , further comprising:removing the displacement plug; andbrazing a cutter to the hardfacing material and into the cutter pocket.5. The method of claim 4 , wherein the cutter is a polycrystalline diamond compact cutter.6. The method of claim 5 , further comprising deburring the cutter pocket before brazing the cutter.7. The method of claim 1 , wherein the substrate comprises steel.8. The method of claim 1 , wherein the substrate comprises a matrix metal.9. The method of claim 1 , wherein the displacement plug comprises at least one of a graphite material claim 1 , a silicate material claim 1 , or a ceramic ...

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Номер записи: 72
15-08-2013 дата публикации

FIXTURE FOR USE IN SEMI-AUTOMATIC RECONDITIONING PROCESS OF A RAILCAR ARTICULATED CONNECTOR

Номер: US20130206742A1
Автор: Brueckert Richard A., Guess William A., Kroesch Donald F.
Принадлежит: TTX Company

A machining fixture for semi-automatically reconditioning an articulated connector is provided. The fixture comprises a housing having at least two side walls, a top plate having a first opening connecting the side walls, and a bottom plate connecting the side walls, the side walls, top plate, and bottom plate defining an interior space. The fixture also includes a clamping mechanism attached to at least one of the side walls, the clamping mechanism comprising a curved hook portion, the curved hook portion being laterally adjustable. 1. A machining fixture for semi-automatically reconditioning an articulated connector comprising:a housing having at least two side walls, a top plate having a first opening connecting the side walls, and a bottom plate connecting the side walls, the side walls, top plate, and bottom plate defining an interior space;a clamping mechanism attached to at least one of the side walls, the clamping mechanism comprising a curved hook portion, the curved hook portion being laterally adjustable.2. The fixture of claim 1 , further comprising a gauge removably positionable within the interior space.3. The fixture of claim 1 , further comprising a drive bar positioned within the interior space and through the first opening of the top plate; a rotational drive system electrically connected to the drive bar for automatically driving the drive bar; and a machining mechanism connected to and rotationally driven by the drive bar claim 1 , the machining mechanism including a cutting tool.4. The fixture of claim 2 , wherein the rotational drive system further comprises a crank mechanism connected with the drive bar for manually adjusting the drive bar.5. The fixture of claim 1 , further comprising:a housing having a bearing in relative alignment above and below the opening of a male portion of an articulated connector; anda feed control electrically connected with the machining mechanism to control the rate of feed of the machining mechanism.6. The ...

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Номер записи: 73
15-08-2013 дата публикации

Semi-automated optical fiber distribution system

Номер: US20130209048A1
Автор: Ludwig Vleugels
Принадлежит: Giga com Benelux BVBA

The present invention relates to a method for reconfiguration of an optical fiber distribution system ( 100 ). The system ( 100 ) comprises a patch panel ( 101 ). The patch panel ( 101 ) comprises subsets of adapters ( 103 ). Each adapter ( 103 ) is configured to receive an optical connector and provide optical connection to the connector when patched in the adapter ( 103 ). The patch panel ( 101 ) further comprises subsets of parking adapters ( 111 ). Each parking adapter ( 111 ) is configured to park an optical connector. The system ( 100 ) further comprises a first connectorized fiber cable ( 105 ) terminated in a first end with a first optical connector. The first optical connector is connected to a first adapter ( 103 ). The first optical connector is moved from the first adapter ( 103 ) to a first parking adapter ( 111 ). Each subset of parking adapters ( 111 ) is positioned in a predetermined distance from the subset of adapters ( 103 ).

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Номер записи: 74
15-08-2013 дата публикации

Cooled vane of a turbine and corresponding turbine

Номер: US20130209230A1
Автор: Andy Pacey, Stephen Batt
Принадлежит: SIEMENS AG

A vane is provided for use in a fluid flow of a turbine engine. The vane includes a thin-walled radially extending aerodynamic vane body having axially spaced leading and trailing edges, and a radially outer platform. The wall of the vane body includes an outer shell and an inner shell and defines an interior cavity therein for flowing a cooling medium. A radially extending load strut is arranged at the inner shell of the wall of the leading edge of the vane body.

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Номер записи: 75
15-08-2013 дата публикации

Set of rotor disks for a turbine engine

Номер: US20130209238A1
Автор: Lionel Rene Henri Weller, Ludovic Gallego, OLIVIER Belmonte
Принадлежит: SNECMA SAS

A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk.

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Номер записи: 76
22-08-2013 дата публикации

RETRACTABLE BIRD AND DEBRIS DEFLECTOR FOR AN AIRCRAFT JET ENGINE

Номер: US20130213003A1
Автор: MATOS JEFFREY A.
Принадлежит:

A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a forward opening for air receipt. The deflector includes a plurality of elongate members disposed on the duct in spaced relation to each other, each member having two end segments and a central segment disposed between the two end segments; and a plurality of guiding members, each mounted for movement along the perimeter of the duct and coupled to one end segment of an elongate member. The central segment of each elongate member extends between a pair of guiding members such that the elongate member is movable by a respective pair of guiding members between a retracted position and a deployed position in front of the duct. When in the deployed position, the central segments are situated to impede the ingress of debris into the duct. 2. The deflector apparatus defined in claim 1 , wherein said central segments are maintained in a substantially parallel relationship in the retracted position.3. The deflector apparatus defined in claim 1 , wherein said central segments are maintained in a substantially parallel relationship in the deployed position.4. The deflector apparatus defined in claim 1 , wherein said elongate members are arranged in a single closely spaced grouping when in said retracted position.5. The deflector apparatus defined in claim 1 , wherein said elongate members are arranged in a plurality of closely spaced groupings when in said retracted position.6. The deflector apparatus defined in claim 1 , wherein each said elongate member comprises a flexible cable.7. The deflector apparatus defined in claim 6 , wherein each said cable is comprised primarily of metal.8. The deflector apparatus defined in claim 6 , wherein each said cable is stretchable.9. The deflector apparatus defined in claim 1 , wherein said end segments of said elongate members are disposed inside a housing of said intake duct.10. The deflector apparatus of claim 6 , ...

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Номер записи: 77
22-08-2013 дата публикации

CENTRAL DATUM FEATURE ON RAILROAD COUPLER BODY AND CORRESPONDING GAUGES

Номер: US20130213921A1
Автор: Eaton Edward T., Larson Eric W., Marchese Thomas A., Nibouar F. Andrew, Sellberg Ronald P., Smerecky Jerry R.
Принадлежит: BEDLOE INDUSTRIES LLC

A coupler body for a railcar coupler, said coupler body comprising at least one central datum feature that does not wear during coupler use. 122.-. (canceled)23. A method for establishing a central datum feature on a railcar coupler body , comprising:determining a location on a surface of the coupler body that does not wear during coupler use over time, where wearing over time comprises repeated frictional contact sufficient to wear metal down to change a dimension of the coupler body such as to be in need of reconditioning; andestablishing a central datum feature on the coupler body at the determined location and which uses the determined location as a primary reference point for reconditioning.24. The method of claim 23 , where the central datum feature comprises a location on a shank or on a back of a horn on the coupler body.25. The method of claim 23 , further comprising creating an opening on the surface of the coupler body at the determined location to serve as the central datum feature.26. The method of claim 25 , where the opening comprises a hole and the central datum feature further includes a plane running through a center of the hole.27. The method of claim 25 , further comprising:positioning a conical feature within the opening for stabilizing a gauge positioned within or on a surface of the coupler.28. The method of claim 23 , further comprising attaching a component to the coupler body at the determined location to serve as the central datum feature.29. The method of claim 23 , where determining a location on the surface of the coupler body comprises determining the location using a coordinate measuring machine or a probing tool.30. The method of claim 23 , where establishing the central datum feature further comprises combining the determined location with another non-wearing feature on the surface of the coupler body as a set of central datum features that act as a set of primary reference points for reconditioning.31. The method of claim 23 , ...

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Номер записи: 78
22-08-2013 дата публикации

COMBINED SEALING AND BALANCING ARRANGEMENT FOR A TURBINE DISC

Номер: US20130216383A1
Автор: Brathwaite Adrian
Принадлежит:

A turbine disc for a turbine is provided with a first protrusion and a second protrusion. The first protrusion and the second protrusion are formed in such a way that a balancing weight is coupleable between the first protrusion and the second protrusion. The first protrusion has a sealing section that is capable of sealing a fluid passage between the turbine disc and a further turbine part of the turbine. 114-. (canceled)15. A turbine disc for a turbine , comprisinga first protrusion and a second protrusion,wherein the first protrusion and the second protrusion are formed in such a way that a balancing weight is coupleable between the first protrusion and the second protrusion, andwherein the first protrusion comprises a sealing section that is capable of sealing a fluid passage between the turbine disc and a further turbine part of the turbine.16. The turbine disc of claim 15 , further comprisinga first surface and a second surface,wherein the first protrusion and the second protrusion are formed on at least one of the first surface or second surface.17. The turbine disc of claim 16 ,wherein the turbine disc is coupleable to the turbine in such a way that the first surface and the second surface are opposed surfaces in an axial direction of a shaft of the turbine.18. The turbine disc of claim 17 ,wherein the turbine disc is coupleable to the turbine in such a way that the first surface is orientated upstream with respect to a fluid flow of the turbine and the second surface is orientated downstream with respect to the fluid flow.19. The turbine disc of claim 15 ,wherein the sealing section comprises a single seal lip.20. The turbine disc of claim 15 ,wherein the sealing section comprises a labyrinth seal.21. The turbine disc of claim 15 ,wherein the first protrusion and the second protrusion are formed and/or arranged in such a way that a recess between the first protrusion and the second protrusion is formed, andwherein the recess is formed in such a way that the ...

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Номер записи: 79
29-08-2013 дата публикации

Gas Turbine Combustor

Номер: US20130219900A1
Автор: HAYASHI Akinori, HIRATA Yoshitaka, Koizumi Hiromi, SASAO Toshifumi, Sekiguchi Tatsuya, Takahashi Hirokazu, Yoshida Shohei
Принадлежит: Hitachi, Ltd.

The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel. 1. A gas turbine combustor adapted to mix liquid fuel with combustion air led from a compressor , burn the mixture and supply combustion gas generated to a gas turbine , the gas turbine combustor comprising:a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets, the fuel injection nozzle including a first system adapted to supply the liquid fuel, and a second system adapted to supply a fluid for atomizing the liquid fuel, wherein the fluid to be supplied to the second system is low-boiling liquid fuel; andmeans for heating the low-boiling liquid fuel.2. The gas turbine combustor according to claim 1 ,wherein the fuel injection nozzle includes a third system adapted to supply atomization air for atomizing the liquid fuel.3. The gas turbine combustor according to claim 2 ,wherein the means for heating the low-boiling liquid fuel supplied to the second system uses heat of the atomization air to be supplied to the third system to heat the low-boiling liquid fuel.4. The gas turbine combustor according to claim 1 ,wherein the low-boiling liquid fuel to be supplied to the ...

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Номер записи: 80
29-08-2013 дата публикации

METHOD AND SYSTEM FOR RETREADING TRACK WHEEL

Номер: US20130221073A1
Автор: MERCIER CRAIG
Принадлежит:

A wheel resurfacing method and system for resurfacing a worn track wheel to its original profile are disclosed. The system comprises a support for maintaining the worn railway wheel, a welding device, a controller, and a surface processing device. The worn railway wheel's circumferential surface defining a flange and a tread surface is reconstituted using a welding material. The welding device and the worn railway wheel rotate one relative to the other at a predetermined rate to adaptively aggregate annular welding beads along the circumferential surface to form a curvilinear profile slanted away from the flange. A surface processing device is then applied to the welded layer to form a substantially uniform surface to reconstitute the worn railway wheel to its original profile. 114-. (canceled)15. A method for resurfacing a worn railway wheel substantially to an original profile , comprising the steps of:maintaining a welding device spaced from the worn railway wheel, the worn railway wheel defining an axis;displacing at least one of the welding device and worn railway wheel about the axis for continuous revolving displacement therebetween at a predetermined rate;adaptively aggregating annular beads formed from a welding material along a circumferential surface of the worn railway wheel, the welding material being applied during the continuous revolving displacement to form a welded layer, the circumferential surface having a flange and a tread surface, each annular bead extending to substantially encircle a portion of the circumferential surface, whereby the welded layer forms a curvilinear profile tapered away from the flange; andsurface processing the welded layer to form a substantially uniform surface to substantially reconstitute the worn railway wheel to the original profile.16. The method for resurfacing the worn railway wheel of claim 15 , further comprising the step of mechanically disturbing the worn railway wheel to form a plurality of grooves into the ...

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Номер записи: 81
05-09-2013 дата публикации

Turbine diaphragm airfoil, diaphragm assembly, and method of repair

Номер: US20130230403A1
Автор: Christopher Charles Krosky, James Michael Kostrubanic, John Matthew Sassatelli, Sheldon Dirk Westwood
Принадлежит: General Electric Co

A turbine diaphragm airfoil, a turbine diaphragm assembly employing such an airfoil, and a method of repair are described. In one embodiment, a turbine diaphragm airfoil includes: a composite airfoil body which includes a pressure side and a suction side, the composite airfoil including: a leading edge section forming a portion of each of the pressure side and the suction side; and a trailing edge section integral with the leading edge section, the trailing edge section including: a prefabricated member affixed to the leading edge section, the prefabricated member forming a remainder of the pressure side of the composite airfoil body; and a weld or braze section contacting the leading edge section and the prefabricated member, the weld or braze section forming a remainder of the suction side of the composite airfoil body.

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Номер записи: 82
05-09-2013 дата публикации

ELECTRIC INSTALLATION MAINTENANCE METHOD AND DEVICE

Номер: US20130231756A1
Автор: BAUDOUIN Jean-Luc, Guillot Matthieu, Houdray Marc, Hypolite Jean-Marie, VOLLET Caroline
Принадлежит: Schneider Electric Industries SAS

The method for performing maintenance of an electric installation comprising at least one electric equipment unit comprises: 1. A method for performing maintenance of an electric installation comprising at least one electric equipment unit comprising:entry of data representative of an electric installation to be monitored in a database,storing of data representative of electric equipment settings and parameters,storing of data representative of events occurring in said electric installation to be monitored in a database so as to constitute an events history,detection of malfunctioning or opening disturbances of at least one electric protection equipment unit in the electric installation,analysis of causes of malfunctioning of the electric installation according to data of the events history and the state of the installation,management of restoration of operation of a part of the installation that is out of service according to the causes of malfunctioning and/or the state of electric lines of the installation, and to a predefined decision tree.2. The maintenance method according to comprising:detection of a voltage outage in a part of an electric installation,determination of the cause of said voltage outage according to events recorded in the events history.3. The maintenance method according to comprising:detection of electric short-circuits in an electric line,disabling closing of an electric equipment unit or of the power supply of said electric line so long as a short-circuit is detected,indication and/or communication of said disabling of power supply of said line.4. The maintenance method according to wherein said restoration management comprises:indication of events,acknowledgement of events having a high criticality level,enabling power supply of an electric line after acknowledgement of events having a high criticality level.5. The maintenance method according to comprising:detection of the causes of opening of an electric switchgear unit according to ...

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Номер записи: 83
19-09-2013 дата публикации

GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

Номер: US20130239587A1
Автор: Dye Christopher M., Karl Hasel, Merry Brian D., Staubach Joseph B., Suciu Gabriel L.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. 1. A gas turbine engine comprising:a fan section;a gear arrangement configured to drive the fan section;a compressor section, including both a low pressure compressor section and a high pressure compressor section;a turbine section configured to drive the compressor section and the gear arrangement; provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section;', 'is greater than about 35,, 'wherein an overall pressure ratiowherein the pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8,wherein the pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15; andwherein the fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.2. The gas turbine engine as set forth in claim 1 , wherein the pressure ratio across the first of the low and high pressure compressor sections being between about 4 and about 6.3. The gas turbine engine as set forth in claim 1 , wherein the ...

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Номер записи: 84
19-09-2013 дата публикации

GAS TURBINE

Номер: US20130243576A1
Автор: Arase Kenichi, Hashimoto Shinya, Tsutsumi Eiichi
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring and through which a cooling medium is flowed. The channel includes an inner channel formed in the blade ring , and a tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring , and extends in a circumferential direction of the blade ring . The outer channel includes a plurality of fixing portions fixed to the blade ring and a thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and expandable and contractible in the circumferential direction. 1. A gas turbine comprising:a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft; anda channel provided in the blade ring and through which a cooling medium is flowed, whereinthe channel includes:an inner channel formed in the blade ring; anda tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring, and extends in a circumferential direction of the blade ring, and whereinthe outer channel includes:a plurality of fixing portions fixed to the blade ring; anda thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and is expandable in the circumferential direction.2. The gas turbine according to claim 1 , whereinthe thermal stress absorbing portion is a bellows tube.3. The gas turbine according to claim 1 , whereinthe thermal stress absorbing portion is a tube bent so as to be folded in a direction crossing the circumferential direction. The present invention relates to a gas turbine in which a channel through which a cooling medium such as cooling steam is flowed is provided in a blade ring.The present application claims priority on Japanese Patent Application No. 2012-062126, filed ...

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Номер записи: 85
26-09-2013 дата публикации

NOVEL LINING PLATE STRUCTURE FOR USE WITH TUBE MILL OF CEMENT INDUSTRY AND MANUFACTURE METHOD THEREOF

Номер: US20130247349A1
Автор: Li Xiaoru
Принадлежит: HUAZHI ENERGY CONSERVATION (HK) CO., LIMITED

A manufacture method of a lining plate structure for use with a tube mill for the cement industry. The manufacture method has the following three technical solutions: 1) metal lining plate, 2) ceramic lining plate, and 3) combined lining plate. The manufacture method includes: lining the concave-convex space, formed in the combination of metal lining plate and tube body, with corundum ceramic lining plate; then installing the combined lining plate on the steel plate of the tube body through inlaying, sticking and local welding. Under the same reference conditions of the present method, the weight of lining plate is reduced 50%, saving the steel material consumption by more than 50%; and the service life of the lining plate for use with the tube mill of cement industry is doubled, up to 15000-20000 hours. 1. A manufacture method of a novel lining plate structure for use with a tube mill of cement industry , comprising following steps:cold and hot die stamping the material medium- and low-carbon steel plate to mold a lining substrate with desired geometry, then performing surfacing welding to the surface of lining substrate, to produce a lining plate of tube mill; installing the lining plate in the tube body; using high-strength cement mortar, epoxy resin, or various inorganic adhesives as cured substances, inlaying and sticking the lining plate, and connecting it to the inner steel plate of tube body by means of local welding.2. A manufacture method of a novel lining plate structure for use with a tube mill of cement industry , the lining plate being two types of ceramic lining plates , and the method comprising following steps:A. making use of the production technology and equipment of existing ceramic factory, to produce the desired sizes of bars, sheets, blocks and plates, and the required ceramic lining plate for surface geometry;B. preparing the material of the ceramic lining plate based on the compositions of corundum ceramics, and then molding with a press by ...

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Номер записи: 86
26-09-2013 дата публикации

INSPECTION DEVICE FOR AN INTERNAL COMBUSTION ENGINE

Номер: US20130247540A1
Автор: DANVERS Thomas Frederick, KELL James, PULISCIANO Adriano, RIGG Graeme Eric
Принадлежит: ROLLS-ROYCE PLC

This invention relates to an internal combustion engine having a cavity for inspection, comprising: an inspection device mounted within a housing, the housing at least partially located within the cavity to be inspected and having a shutter which is actuable between a closed configuration and an open configuration; and an actuation mechanism for moving the shutter between the closed configuration and the open configuration. 1. An internal combustion engine having a cavity for inspection , comprising:an inspection device mounted within a housing, the housing at least partially located adjacent the cavity to be inspected and having a shutter which is actuable between a closed configuration and an open configuration, wherein the inspection device is retractable between a stowed position and an inspection position; and,an actuation mechanism for moving the shutter between the closed configuration and the open configuration.2. An internal combustion engine as claimed in claim 1 , wherein the inspection device is configured to allow visual inspection of the cavity.3. An internal combustion engine as claimed in claim 1 , wherein the shutter is retractably stowed within the housing when in the closed configuration and actuated into the cavity so as to expose the inspection device when in the open configuration.4. An internal combustion engine as claimed in claim 1 , wherein the shutter is configured to be actuated by the inspection device when the inspection device is moved between the stowed and inspection positions.5. An internal combustion engine as claimed in claim 1 , wherein the shutter includes a cleaning device for cleaning the inspection device.6. An internal combustion engine as claimed in claim 1 , wherein the shutter and inspection device are simultaneously actuable.7. An internal combustion engine as claimed in claim 1 , wherein the actuation mechanism is one taken from the group including pneumatic claim 1 , hydraulic or electrical.8. An internal combustion ...

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Номер записи: 87
03-10-2013 дата публикации

Chained Clamp Pipeline Repair Structure and Method of Use

Номер: US20130255816A1
Автор: Benson Dan Thomas, Krohn Dan, Vuong Nghia K.
Принадлежит: OCEANEERING INTERNATIONAL, INC.

Interlocking bend limiter sections are substantially mirror images of each other and are joined to form an interlocking bend limiter segment without use of fasteners by engaging each other's interlocking ends. An interlocking bend limiter comprises a plurality of interlocking bend limiter segment secured at an end by an end piece. In alternative, related embodiments a repair system comprises one or more machinable length sections which function as chain clamps to repair a subsea pipeline while the subsea pipeline is still in service and which can comprise interlocking sections similar to bend limiter sections or which are locked in more traditional manners such as by using bolts or other fasteners. 1. A chain clamp link usable in a pipeline repair system , comprising:a. a first machinable length section comprising a radius configured to be larger than a subsea pipeline;b. a second machinable length section comprising a radius configured to be larger than the subsea pipeline and configured to securably mate with the first machinable length section; andc. a seal disposed intermediate the first machinable length section and the second machinable length section, the seal configured to occlusively seal the mated first machinable length section and the second machinable length section against an outer surface of the pipeline.2. The chain clamp link usable in a pipeline repair system of claim 1 , wherein the chain clamp link further comprises a pipeline gripping slip.3. The chain clamp link usable in a pipeline repair system of claim 1 , wherein the chain clamp link is configured to be structural.4. The chain clamp link usable in a pipeline repair system of claim 1 , wherein:a. the chain clamp comprises a plurality of chain clamps;b. the first machinable length section and the second machinable length section of a predetermined number of the chain clamps further comprise a mating end; andc. the first machinable length section and the second machinable length section of ...

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Номер записи: 88
03-10-2013 дата публикации

Thread load distribution

Номер: US20130259599A1
Автор: Daniel Benjamin, Daniel R. Kapszukiewicz, Kaliya Balamurugan
Принадлежит: Individual

A fastener arrangement includes a threaded member having threads extending from a first end to a second end. The threads have a thread contour provided by a load and clearance flank surfaces joined to one another by a crest and root. For the external threaded member the crest provides a crest diameter, and a root provides a root diameter and is arranged between adjoining threads. At least one thread near the first end has a weakened thread contour that decreases rigidity of the one thread compared to other threads, enabling axial loads to be distributed more evenly between the threads.

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Номер записи: 89
10-10-2013 дата публикации

Ultra-Low-Friction Treadmill Deck

Номер: US20130263418A1
Автор: Johnson, JR. Fred B.
Принадлежит:

A laminated treadmill deck or deck insert includes a wear surface formed of a phenolic impregnated paper laminated to an isocyanate resin bonded MDF core. A low moisture content isocyanate resin bonded wood fiber MDF core enables dimensional stability and high internal bonding strength even at reduced insert thicknesses. The deck or deck insert is disposed on a support deck adjacent the upper run of an endless treadmill belt. The deck or deck insert is provided with wear surfaces on each broad side and is easily removable and reversible to expose the second wear surface. The deck or deck insert is coated with as wax having fluoropolymer powder embedded in the exposed surface of the wax to provide a low-friction wear surface. 2. The method of claim 1 , wherein the fluoropolymer powder comprises submicron particles.3. The method of claim 1 , wherein the wax coating comprises a micronized-wax and the applying comprises heating and contact rolling of the micronized-wax along a central foot-plant portion of the at least on of the first and second major faces of the insert.4. The method of claim 3 , wherein sufficient wax coating is applied to accommodate transfer of a portion of the wax to the underside of the treadmill belt.5. The method of claim 3 , further comprising pre-heating the deck insert prior to applying the wax coating.6. The method of claim 3 , further comprising post-heating the deck insert after depositing the fluoropolymer powder to promote setting of the fluoropolymer powder in the wax coating.7. The method of claim 1 , further comprising claim 1 , applying the wax coating to both the first and second major faces of the insert and depositing the fluoropolymer powder on the wax coatings on both the first and second major faces of the insert.8. The method of claim 1 , where the moisture content of the fibrous substrate is less than about four percent prior to lamination of the paper layers.9. The method of claim 1 , further comprising substantially ...

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Номер записи: 90
17-10-2013 дата публикации

GAS TURBINE

Номер: US20130272860A1
Автор: Arase Kenichi, Tsutsumi Eiichi
Принадлежит:

A gas turbine according to the invention includes a seal housing in which a leaf-shaped seal is provided and a detection end space, a gas introduction path, and a gas discharge path are also formed. The detection end space is formed at a position on the outside in a radial direction from a leaf-shaped seal, and the gas introduction path has an introduction port formed at a position further on the downstream side than the leaf-shaped seal and also has a radially extending portion extending toward the outside in the radial direction from the introduction port and an axially extending portion extending in the direction of an axis from an end portion of the radially extending portion and reaching the detection end space. 1. A gas turbine comprising;a rotor that rotates around an axis of rotation;a casing that covers the rotor so as to be rotatable; anda vane fixed to the casing,wherein the rotor has a rotor disk; centered on the axis of rotation and a plurality of blades fixed to the rotor disk and arranged in a circumferential direction with respect to the axis of rotation, in each of a plurality of stages arranged in an axial direction in which the axis of rotation extends, and a plurality of the vanes are disposed side by side in the circumferential direction on the upstream side of the turbine blades in each of the plurality of stages,an upstream-side rim portion protruding to the upstream side and a downstream-side rim portion protruding to the downstream side are formed on the rotor disk of each of the plurality of stages,an annular seal housing is fixed to the inside of the vane in a radial direction of the rotor,an upstream-side seal member facing the downstream-side rim portion on the upstream side with respect to the seal housing is provided in the seal housing, and a detection end space in which a temperature detection end of a thermometer is accommodated, a gas introduction path which leads gas in a disk cavity between the seal housing and the upstream-side ...

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Номер записи: 91
17-10-2013 дата публикации

Axially-split radial turbines and methods for the manufacture thereof

Номер: US20130272882A1
Автор: Amandine Miner, David K. Jan, Don Mittendorf, Jason Smoke
Принадлежит: Honeywell International Inc

Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

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Номер записи: 92
24-10-2013 дата публикации

TURBINE FOR AN EXHAUST TURBOCHARGER OF AN INTERNAL COMBUSTION ENGINE

Номер: US20130276444A1
Автор: Hirth Torsten, SUMSER Siegfried
Принадлежит:

In a turbine for an exhaust gas turbocharger of an internal combustion engine having a housing part which has a receiving chamber and which comprises a spiral duct through which exhaust gas of the internal combustion engine can flow, the spiral duct having an outlet cross-section via which exhaust gas is directed onto a turbine wheel disposed in the receiving chamber whereby the turbine wheel can be rotated, at least one flow control member is provided which can be moved in the circumferential direction of the receiving chamber and by means of which the flow cross-section can be adjusted, wherein a warp angle of the outer contour region of the wall over which the flow cross-section can be adjusted is smaller than a wrap angle over which the outer contour region thereof extends. 15422105694581058609456687094609698585610468102941041089698102681086810210868108947010496981049470. A turbine () for an exhaust turbocharger () of an internal combustion engine () having at least one housing part () with a receiving chamber () and comprising at least one spiral duct () through which exhaust gas from the internal combustion engine () is conducted , said spiral duct () having an outlet cross-section (A) via which a turbine wheel () , which is accommodated in the receiving chamber () of the turbine housing () can be acted on by the exhaust gas , and at a flow control member () which is movable in the circumferential direction () of the receiving chamber () and by means of which the outlet flow cross-section (A) to the turbine wheel () can be adjusted , the turbine housing including a wall ( , ) , which delimits the spiral duct () in the housing part () and an outer contour region () which faces towards the flow control member () in the radial direction () of the receiving chamber () , said outer contour region () having a counterpart contour which at least substantially corresponds to an outer contour region () , which faces towards the outer contour region of the wall ( , ) in ...

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Номер записи: 93
24-10-2013 дата публикации

Axially-split radial turbine

Номер: US20130280036A1
Автор: Ardeshir Riahi, Christopher Zollars, David K. Jan, Rajiv Rana, Tom Polakis
Принадлежит: Honeywell International Inc

An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.

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Номер записи: 94
31-10-2013 дата публикации

ROTARY MACHINE AND MOUNTING METHOD OF ATMOSPHERE RELIEF MECHANISM FOR ROTARY MACHINE

Номер: US20130287549A1
Автор: FUJII Syota, FUKUMORI Hideki, MIHARA Ryoji
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

It is intended to provide a rotary machine provided with an atmosphere relief mechanism by which damage of a rupture disc when attaching the disc can be prevented and which can withstand use over a long period of time. The rotary machine is provided with a casing and an atmosphere relief mechanism for closing an opening for atmospheric release formed in the casing and relieving pressure of inner fluid to atmosphere when a pressure in the casing rises. The atmosphere relief mechanism includes: a rupture disc configured to rupture when the pressure in the casing reaches a predetermined pressure; a pair of annular holding parts arranged to hold an outer edge of the rupture disc from both sides; a plurality of fastening members for fastening the pair of annular holding parts to each other so as to hold the rupture disc between the pair of annular holding parts and an annular spacer part provided along an outer circumference of the rupture disc 1. A rotary machine comprising:a casing; andan atmosphere relief mechanism for closing an opening for atmosphere relief formed in the casing and relieving pressure of inner fluid to atmosphere when a pressure in the casing rises, wherein the atmosphere relief mechanism comprises:a rupture disc configured to rupture when the pressure in the casing reaches a predetermined pressure;a pair of annular holding parts arranged to hold an outer edge of the rupture disc from both sides;a plurality of fastening members for fastening the pair of annular holding parts to each other so as to hold the rupture disc between the pair of annular holding parts; andan annular spacer part provided along an outer circumference of the rupture disc.2. The rotary machine according to claim 1 ,wherein between the rupture disc and a first holding part of the pair of annular holding parts that is disposed on a side of an interior space of the casing, a liquid gasket is provided.3. The rotary machine according to claim 1 ,wherein the annular spacer part is a ...

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Номер записи: 95
07-11-2013 дата публикации

PURGE METHOD AND PURGE UNIT FOR GAS TURBINE COMBUSTOR

Номер: US20130291547A1
Автор: Ochiai Yoshiaki
Принадлежит:

A purging method and a purge unit for a gas turbine combustor capable of effectively preventing deviation of an exhaust gas environmental regulation value from a regulation range in the case of using a dual-fuel type gas turbine combustor. The gas turbine combustor is provided with nozzles. Which communicate with an oil fuel line where oil fuel flows and a gas fuel line where gas fuel flows and are capable of switching injection fuel between the oil fuel and the gas fuel. A purging method for the gas turbine includes a first purge step of purging the oil fuel line by at least water immediately after the injection fuel is switched to the gas fuel from the oil fuel and a second purge step of purging the oil fuel line by at least water immediately before the injection fuel is switched to the oil fuel from the gas fuel.

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Номер записи: 96
14-11-2013 дата публикации

ELECTRICAL RAFT WITH MAP

Номер: US20130298566A1
Автор: BROUGHTON Paul, KENNEA Robin Charles, PEACE Richard, SKINNER Gary Alan, SUMMERFIELD Philip, WILLMOT Michael Christopher
Принадлежит:

An electrical raft is provided that has electrical conductors embedded in a rigid material The electrical raft may have other embedded components, such as embedded fluid pipes The electrical raft is provided with a raft map that indicates the location and/or path of components embedded in the electrical raft The raft map can be used to identify the positions of the embedded components, and may also be provided with active elements, such as LEDs, which may be used to indicate an operating state of the systems/components embedded in the electrical raft The raft map may be useful in assembly, repair and fault diagnosis, for example. 1. An electrical raft comprising:components embedded in a rigid material, the components including electrical components that form at least a part of an electrical system; anda raft map indicating the position of at least some of the embedded electrical components within the electrical raft, the raft map being visible from outside the electrical raft.2. An electrical raft according to claim 1 , wherein:the electrical system comprises electrical conductors embedded in the rigid material; andthe raft map shows the paths of the embedded conductors within the raft.3. An electrical raft according to claim 1 , wherein the rigid material is a rigid composite material.4. An electrical raft according to claim 1 , wherein:the embedded components further comprise at least one fluid passage embedded in the rigid material; andthe raft map also shows the path of the or each embedded fluid passage.5. An electrical raft according to claim 4 , wherein the raft map also shows the direction in which fluid is configured to flow through the fluid passage in use.6. An electrical raft according to claim 4 , wherein:the raft map comprises an active indicator that has at least two outputs, each output indicating a different state of the fluid passage in use; and, optionallythe state indicated by the active indicator corresponds to a flow rate and/or a flow pressure ...

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Номер записи: 97
28-11-2013 дата публикации

METHOD FOR RECONDITIONING A RAILCAR ARTICULATED CONNECTOR

Номер: US20130312239A1
Автор: Brueckert Richard A., Guess William A., Kroesch Donald F.
Принадлежит:

A method for reconditioning a railcar articulated connector is provided. The method comprises the steps of marking a surface of a portion of an articulated connector to divide the surface into sections, pre-heating the surface of a portion of an articulated connector, adding weld to a first section of the pre-heated portion of the articulated connector, and adding weld to a second section of the pre-heated portion of the articulated connector. 1. A method for reconditioning a railcar articulated connector , the method comprising the steps of:marking a surface of a portion of an articulated connector to divide the surface into sections;pre-heating the surface of a portion of an articulated connector;adding weld to a first section of the pre-heated portion of the articulated connector; andadding weld to a second section of the pre-heated portion of the articulated connector.2. The method of claim 1 , wherein the portion of the articulated connector is a bottom bearing surface of a male portion of the articulated connector;3. The method of claim 2 , wherein the sections are wedge-shaped sections.4. The method of claim 3 , wherein the surface is divided into eight sections.5. The method of claim 4 , wherein weld is added to six of the eight sections leaving two opposite sections without weld.6. The method of claim 5 , further comprising the step of machining the welded sections.7. The method of claim 6 , further comprising the step of welding the remaining two unwelded sections.8. The method of claim 7 , further comprising the step of machining the remaining two sections.9. The method of claim 8 , further comprising the step of allowing the portion of the articulated connector to cool to ambient temperature.10. The method of claim 9 , wherein said step of allowing the portion of the articulated connector to cool is performed with the portion of the articulated connector covered in insulating material.11. The method of claim 10 , wherein the insulating material is an ...

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Номер записи: 98
28-11-2013 дата публикации

METHOD OF DETECTING SHAFT BREAK

Номер: US20130312423A1
Автор: BACIC Marko, Garner Stephen Granville
Принадлежит: ROLLS-ROYCE PLC

A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine. First construct a frequency model of the shaft system. Then determine a notch frequency and a first torsional frequency for the shaft system from the model. Then in real time measure a rotational speed of the shaft; detect the presence or absence of a feature at at least one of the notch frequency and the first torsional frequency in the measured speed; and generate a shaft break signal in response to the absence of at least one of the features. 1. A method of detecting shaft break in a gas turbine engine having a shaft system , the shaft system comprising shaft that couples a compressor and a turbine; the method comprises steps to:a. construct a frequency model of the shaft System;b. determine a notch frequency and a first torsional frequency for the shaft system from the modelc. measure a rotational speed of the shaft;d. detect the presence or absence of a feature at least one of the notch frequency and the first torsional frequency in the measured speed; ande. generate a shaft break signal in response to the absence of at least one of the features.2. A method as claimed in wherein the feature comprises a notch at the notch frequency and a peak at the first torsional frequency.3. A method as claimed in wherein the shaft break signal is generated in response to the absence of a feature at both the notch frequency and at the first torsional frequency.4. A method as claimed in wherein the rotational speed of the shaft is measured close to the compressor.5. A method as claimed in wherein the rotational speed of the shaft is measured close to the turbine.6. A method as claimed in wherein the notch frequency is proportional to the square root of the shaft stiffness divided by the turbine inertia.7. A method as claimed in wherein the notch frequency is proportional to the square root of the shaft stiffness divided by ...

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Номер записи: 99
28-11-2013 дата публикации

APPLICATION OF WEAR PLATE TO ARTICULATED CONNECTOR LOAD BEARING BOTTOM SURFACE

Номер: US20130313214A1
Автор: Brueckert Richard A., Guess William A., Kroesch Donald F.
Принадлежит: TTX Company

A method for reconditioning a railcar connector is provided. The method comprises machining a portion of a casting to create a wear plate application surface, positioning a wear plate on the wear plate application surface, and welding the wear plate to the wear plate application surface. 1. A method for reconditioning a railcar connector , comprising:machining a portion of a casting to create a wear plate application surface;positioning a wear plate on the wear plate application surface; andwelding the wear plate to the wear plate application surface.2. The method of claim 1 , wherein machining a portion of a casting to create a wear plate application surface further comprises machining a portion of a bottom bearing surface of a male portion of an articulated connector.3. The method of claim 1 , wherein welding the wear plate to the application surface further comprises:determining whether the male portion has achieved a desired machining dimension after wear plate application.4. The method of claim 1 , wherein welding the wear plate to the application surface further comprises welding a substrate layer of the wear plate to the application surface.5. The method of claim 1 , wherein the wear plate includes a layer made from chromium carbide.6. The method of claim 1 , wherein the wear plate includes a layer made from a weldable steel substrate.7. The method of claim 1 , wherein the wear plate includes a layer made from stainless steel.8. The method of claim 1 , wherein the wear plate is generally circular and includes an opening that is generally concentric with an outside edge of the wear plate.9. The method of claim 1 , wherein the wear plate is generally circular and includes an opening that is generally non-concentric with an outside edge of the wear plate.10. The method of claim 1 , wherein the wear plate is a non-circular shape.11. The method of claim 10 , wherein the wear plate includes a generally circular opening defined therein.12. The method of claim 1 , ...

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Номер записи: 100