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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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12-01-2012 дата публикации

Split flow valve arrangement

Номер: US20120006433A1

Автор: Antony Morgan

Принадлежит: Rolls Royce PLC

A split flow valve arrangement comprising a first valve portion having an inlet, a first outlet and a second outlet; and a second valve portion having a first inlet coupled to the first outlet, a second inlet coupled to the second outlet, a main outlet and a secondary outlet. The inlet is selectively coupled to none, one or both of the first and second outlets; the first inlet is selectively coupled to the main outlet and the second inlet is selectively coupled to the secondary outlet. The first and second valve portions are constrained to move in synchronicity to therefore selectively direct fluid to flow from the inlet to none, one or both of the main and secondary outlets.

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Номер записи: 1

26-10-2021 дата публикации

Свеча зажигания газотурбинных промышленных установок

Номер: RU0000207379U1

Автор: Александр Владимирович Краснов, Андрей Николаевич Мурысев, Вадим Петрович Домбровский

Принадлежит: Акционерное общество "Уфимское научно-производственное предприятие "Молния"

Свеча зажигания для газотурбинного двигателя, содержащая основной трубчатый корпус с установленным в нем искрообразующим изолятором с полупроводниковым покрытием и внутренним каналом, в котором расположен центральный электрод, металлическую втулку, закрепленную в основном корпусе свечи и поджимающую искрообразующий изолятор к внутреннему торцу основного корпуса, образующего боковой электрод свечи, герметизирующий изолятор с ножками и внутренним каналом с закрепленным в нем в стеклогерметике токоведущим стержнем, установленный с упором в бурт дополнительного корпуса и закрепленный в нем медной клиновой втулкой, обращенной своим большим сечением в сторону искрообразующего изолятора, и стеклогерметизирующей уплотнительной втулкой, выполненной из нетокопроводящего стеклогерметика, охватывающей герметизирующий изолятор, экранную трубку, цангу, соединяющую токоведущий стержень с центральным электродом, при этом свеча дополнительно содержит промежуточный корпус и монтажный корпус, при этом в монтажном корпусе частично расположен дополнительный корпус и соединен с ним сваркой, а промежуточный корпус расположен между основным и монтажным корпусами, при этом контакт между монтажным, промежуточным и основным корпусами отсутствует, в основном корпусе дополнительно расположена керамическая трубка, в промежуточном корпусе размещен промежуточный изолятор, а в монтажном корпусе установлен дополнительный изолятор, помимо внутреннего канала основного изолятора центральный электрод расположен во внутренних каналах керамической трубки, промежуточного изолятора и дополнительного изолятора, центральный электрод состоит из трех частей, соединенных сваркой в местах между корпусами, при этом промежуточный изолятор установлен с упором в бурт промежуточного корпуса и закреплен в нем металлической втулкой, зафиксированной в промежуточном корпусе сваркой, при этом с упором в торцы промежуточного изолятора на центральном электроде закреплены сваркой два металлических кольца, керамическая трубка ...

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Номер записи: 2

26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1

Автор: Brian Patrick Hansen, Christopher Edward LaMaster, David August Snider, Timothy Edward DeJoris

Принадлежит: General Electric Co

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.

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Номер записи: 3

02-02-2012 дата публикации

Auxiliary power unit fire enclosure drain seal

Номер: US20120023897A1

Автор: Brian C. DeDe, Christine Ingrid Schade, David Lau, David Ronald Adair

Принадлежит: Hamilton Sundstrand Corp

A drain assembly for an auxiliary power unit having a hot zone formed by a combustor case comprises a fire enclosure, a drain fitting, a discharge port and a piston seal. The fire enclosure encapsulates the hot zone of the combustor case. The drain fitting connects to the fire enclosure. The discharge port extends from the combustor case into the drain fitting. The piston seal is positioned between the drain fitting and the discharge port.

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Номер записи: 4

02-02-2012 дата публикации

Methods for controlling fuel splits to a gas turbine combustor

Номер: US20120023953A1

Автор: Priscilla Graves Childers, Stephen Robert Thomas, Vamsi Duraibabu

Принадлежит: General Electric Co

Methods for controlling fuel splits to a combustor of a gas turbine are disclosed. The methods may include determining a combustion reference temperature of the gas turbine, measuring a biasing parameter of the gas turbine, determining at least one fuel split biasing value based on the combustion reference temperature and the biasing parameter and adjusting a nominal fuel split schedule based on the at least one fuel split biasing value.

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Номер записи: 5

09-02-2012 дата публикации

Combustor and the Method of Fuel Supply and Converting Fuel Nozzle for Advanced Humid Air Turbine

Номер: US20120031103A1

Автор: Kazuki Abe, Tomomi Koganezawa

Принадлежит: HITACHI LTD

A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units. A fuel ratio, at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.

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Номер записи: 6

09-02-2012 дата публикации

Ventilation inlet

Номер: US20120034068A1

Автор: Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone.

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Номер записи: 7

23-02-2012 дата публикации

method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

Номер: US20120042657A1

Автор: Celine Marie Anne Issert, Laurent Gilbert Yves Hodinot, Pascal Laurent

Принадлежит: SNECMA SAS

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

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Номер записи: 8

23-02-2012 дата публикации

Fuel supply system for gas turbine combustor and fuel supply method for gas turbine combustor

Номер: US20120042658A1

Автор: Ken Ugai, Ryo Higashi, Takeo Hirasaki, Yoshikiyo Okamoto, Yosuke Eto

Принадлежит: Mitsubishi Heavy Industries Ltd

A consumption amount of high-calorific gas such as coke oven gas (COG) during operation of a gas turbine is reduced, halt of the gas turbine due to clogging of a pilot system, a malfunction of a compressor which compresses high-calorific gas is prevented, and reliability of the gas turbine is improved. When operation of the gas turbine ( 11 ) starts, with use of both a first fuel supply system ( 31 ) which supplies a high-calorific fuel for a first nozzle constituting a combustor ( 17 ), and a second fuel supply system ( 32 ) which supplies a low-calorific fuel for a second nozzle constituting the combustor ( 17 ), the high-calorific fuel and the low-calorific fuel are supplied to the combustor ( 17 ), and at a time when the gas turbine ( 11 ) reaches output power which enables continuous operation with only the low-calorific fuel, supply of the high-calorific fuel to the combustor ( 17 ) is shut off, and only the low-calorific fuel is supplied to the combustor ( 17 ).

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Номер записи: 9

23-02-2012 дата публикации

Air turbine starter inlet housing assembly airflow path

Номер: US20120042659A1

Автор: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter

Принадлежит: Hamilton Sundstrand Corp

An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.

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Номер записи: 10

23-02-2012 дата публикации

Air turbine starter turbine blade airfoil

Номер: US20120045342A1

Автор: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter

Принадлежит: Hamilton Sundstrand Corp

A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

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Номер записи: 11

01-03-2012 дата публикации

Casing body through which hot gases can flow and comprising an inner heat shield

Номер: US20120047905A1

Автор: Marc Rauch, Peter Oskar Baldischweiler

Принадлежит: Alstom Technology AG

A casing body for a hot gas flow includes an outer casing body having a hot gas side with a precisely prepared locating surface. A pin-type retainer is disposed on the locating surface, and an inner heat shield is disposed at a distance from the hot gas side of the outer casing body and fastened to the retainer.

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Номер записи: 12

22-03-2012 дата публикации

Exhaust washed structure and associated composite structure and method of fabrication

Номер: US20120066882A1

Автор: Buddhadev Chakrabarti, Gopal P. Mathur, Leanne L. Lehman, Michael L. Hand

Принадлежит: Boeing Co

A composite structure and an associated exhaust washed structure are provided which may be formed of ceramic matrix composite (CMC) materials. A method of fabricating a composite structure which may include the CMC material is also provided. A composite structure may include a corrugated septum extending in a lengthwise direction. The composite structure may also include a flute within which the corrugated septum is disposed to form, for example, a partitioned flute assembly.

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Номер записи: 13

05-04-2012 дата публикации

Method, apparatus and system for igniting wide range of turbine fuels

Номер: US20120079831A1

Автор: Denis Michel Martin, Joseph Kirzhner, Matthieu Paul Frederic Vierling, Nicolas Pourron

Принадлежит: General Electric Co

In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for the supplied fuel to be ignited. In one aspect, fuel parameters related to the molecular weight of the fuel such as specific gravity and pressure drop are determined. Ignitability of the fuel is calculated based on the fuel parameters and adjusted as necessary to bring the fuel's ignitability to designed values. The fuel's ignitability can be calculated without actually igniting the fuel and also without direct knowledge of the fuel's calorific value or its composition.

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Номер записи: 14

05-04-2012 дата публикации

Method for installing heat shielding on a fixed internal structure of a jet engine nacelle

Номер: US20120082808A1

Автор: Laurence Lemains, Pascal Mer

Принадлежит: Aircelle SA

The invention relates to a method for installing heat shielding ( 31 ), including a heat cushion ( 33 ) covered with a ply ( 35 a ) made from a structural material, on a fixed internal structure ( 29 ) of a jet engine nacelle, including the following consecutive steps: spreading an adhesive ( 43 ) that guarantees good mechanical strength at high temperatures on at least one of the elements selected from said ply ( 35 a ) and an internal skin ( 39 ) of the fixed internal structure; applying said ply ( 35 a ) to said internal skin ( 39 ); and, if necessary, setting said adhesive ( 43 ).

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Номер записи: 15

19-04-2012 дата публикации

Systems and methods for providing ac power from multiple turbine engine spools

Номер: US20120091716A1

Автор: Farhad Nozari, Richard A. Cote

Принадлежит: Boeing Co

Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.

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Номер записи: 16

26-04-2012 дата публикации

Catcher pin assembly

Номер: US20120096951A1

Автор: Lawrence D. Foster

Принадлежит: Rolls Royce PLC

A catcher pin assembly for attachment to a catcher link of an aircraft frame, the catcher pin assembly having an engine mounting element, a catcher pin, a compressible element, and a nut, which is lockable to the catcher pin, the compressible element being compressed between the pin and the mounting element and/or between the mounting element and the nut, in the assembled condition of the assembly, such that the compressible element applies a predetermined resistance to rotation of the catcher pin relative to the mounting element. The invention also relates to a method of testing a catcher pin assembly to determine if the catcher pin is carrying load from the catcher link, the method including applying a predetermined torque to the catcher pin sufficient to overcome the resistance to rotation of the catcher pin when it is unloaded, and determining whether the catcher pin rotates relative to the mounting element.

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Номер записи: 17

10-05-2012 дата публикации

Igniter with integral pressure sensing line

Номер: US20120110975A1

Автор: Hannes A. Alholm

Принадлежит: United Technologies Corp

An igniter device for a combustor system includes an igniter housing and a pressure sense passage. The igniter housing surrounds an electrode and an insulating body. The igniter has a tip to be positioned within a chamber for combustion. The pressure sense passage is attached to an exterior surface of the igniter housing. The pressure sense passage is configured to direct fluid to a pressure sensor.

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Номер записи: 18

17-05-2012 дата публикации

Turbine

Номер: US20120121393A1

Автор: Asaharu Matsuo, Hiroharu Ooyama, Kazuyuki Matsumoto, Yoshihiro Kuwamura, Yoshinori Tanaka

Принадлежит: Mitsubishi Heavy Industries Ltd

The turbine is provided with a blade ( 50 ) and a structure body ( 11 ) which rotates relatively with respect to the blade ( 50 ). A stepped part ( 52 A) having a step surface ( 53 A) is installed at one of the leading end of the blade ( 50 ) and the structure body ( 11 ) corresponding to the leading end thereof, while a seal fin ( 15 A) which extends toward the stepped part ( 52 A) to form a small space (H) is installed at the other of them. A cavity (C 1 ) is formed between the blade ( 50 ) and the structure body ( 11 ) and also between the seal fin ( 15 A) and the partition wall which faces thereto in the rotating shaft direction of the structure body ( 11 ) on the upstream side. When a distance of the cavity (C 1 ) between the partition wall and the seal fin ( 15 A) is given as a cavity width (W), and a distance between the seal fin ( 15 A) and the end edge ( 55 ) of the stepped part ( 52 A) in the rotating shaft direction on the upstream side is given as (L), at least one of the distances (L) satisfies the following formula (1). 0.7H≦L≦0.3W (1)

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Номер записи: 19

31-05-2012 дата публикации

Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines

Номер: US20120131927A1

Автор: Chukwueloka Obiora Umeh, Gabor Ast, Gary Lee Leonard, Herbert Kopecek, Mark Patrick Kelsey, Richard Wade Stickles, Sara Rocci Denis, Shai Birmaher, Steven Clayton Vise

Принадлежит: General Electric Co

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

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Номер записи: 20

07-06-2012 дата публикации

Fluid impingement arrangement

Номер: US20120137650A1

Автор: Andrew J. Mullender, Brian A. Handley, Christopher T.J. SHEAF, David Macmanus, Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

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Номер записи: 21

14-06-2012 дата публикации

Oxidizer Compound for Rocket Propulsion

Номер: US20120144799A1

Автор: Joseph R. Herdy, JR., Robert L. Sackheim

Принадлежит: National Aeronautics and Space Administration NASA

A rocket propulsion oxidizer compound that is a mixture that is a homogenous and stable liquid at room temperature that includes nitrous oxide and nitrogen tetroxide.

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Номер записи: 22

21-06-2012 дата публикации

Pegless secondary fuel nozzle

Номер: US20120151927A1

Автор: Amit Monga, Divyang Rajendra Desai, Kodukulla Venkat Sridhar, Sandeep Gopalakrishna

Принадлежит: General Electric Co

A unitary fuel injection manifold for a secondary fuel nozzle improves fuel-air mixing and offers flexibility to alter the mixing profile through adaptability to a variety of number, types, and orientation of discharge outlets to the combustion air mixing space around the secondary fuel nozzle. An aerodynamic surface with reduced extension into the mixing space reduces pressures drop and interference with design airflow. Manifold integrity is enhanced by elimination of fillet welds to mount external pegs.

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Номер записи: 23

28-06-2012 дата публикации

Accessory gearbox with a starter/generator

Номер: US20120159964A1

Автор: Hao Huang, Jan Zywot

Принадлежит: General Electric Co

An assembly for a gas turbine engine comprising an accessory gearbox comprising a drive gear and pinion gear and a starter/generator mechanically mounted to the accessory gearbox. The starter/generator comprising a housing and a portion of a rotatable shaft with a safety disconnect where the safety disconnect is located within the housing of the starter/generator.

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Номер записи: 24

05-07-2012 дата публикации

Fuel anti-icing and apu compartment drain combination

Номер: US20120167579A1

Автор: Greg R. Giddings, Jay M. Francisco

Принадлежит: Hamilton Sundstrand Corp

A heat exchanger has a first passage to be connected to a source of fuel. The heat exchanger has an outlet to communicate the fuel downstream. A second passage connects to a source of air. The air passes adjacent to the first passage to heat fuel in the first passage. A jet pump is positioned downstream of the second passage to receive air from the second passage. The jet pump includes a tap connected to a housing compartment to drain fluid from the compartment. A method is also disclosed.

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Номер записи: 25

05-07-2012 дата публикации

Method to maximize lng plant capacity in all seasons

Номер: US20120167619A1

Автор: Robert C. HAVLIK, Stanley H. HUANG

Принадлежит: Chevron USA Inc

As described herein, a method and system for operating a liquefied natural gas (LNG) plant are provided. The method and system also provide for domestic natural gas production. In the present methods and systems, substantially all of the natural gas produced from a well or formation is processed to form LNG; a portion of the LNG produced is regasified; and the regasification is utilized to cool the inlet air to the gas turbines in the LNG plant, either directly or indirectly.

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Номер записи: 26

05-07-2012 дата публикации

Anti-rotation for thrust washers in planetary gear system

Номер: US20120171017A1

Автор: Bradley A. Delmore, Dean A. Norem, Jeff A. Brown, Tye L. Klipp, William C. Trommer

Принадлежит: Hamilton Sundstrand Corp

A bushing for use in a planetary gear system has a cylindrical body portion defining a bore extending along a central axis to be received on a planetary gear shaft. A tab extends axially beyond a nominal body portion of the bushing and is received in a notch in a thrust washer adjacent to the bushing to prevent rotation of the thrust washer. A gear cage and an air turbine starter incorporating the bushing, along with a method of installing the bushing are also disclosed.

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Номер записи: 27

12-07-2012 дата публикации

Runner for circumferential seals

Номер: US20120177486A1

Автор: Jonathan Logan Miller, Leslie Charles Kurz, M. Rifat Ullah

Принадлежит: Individual

A runner assembly for a circumferential seal assembly includes a runner having an inwardly extending runner mounting flange, a flexible mounting structure and a retainer assembly therefore.

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Номер записи: 28

30-08-2012 дата публикации

Assembly for holding the interface of stationary outer structure of a nacelle and housing of a jet engine

Номер: US20120217372A1

Автор: Georges Alain Bouret, Guy Bernard Vauchel, Patrick Gonidec, Pierre Caruel

Принадлежит: Aircelle SA

The invention relates to an assembly for holding the interface of a stationary outer structure ( 15 ) of a nacelle ( 3 ) and housing ( 27 ) of a jet engine ( 5 ), said assembly including: a first raised element belonging to the upstream end of the stationary outer structure ( 15 ); a second raised element belonging to the downstream end of the housing ( 27 ), said first and second raised elements being formed so as to be placed in contact with each other; two half-rings ( 109 ) formed by a wall defining a recess that is formed so as to receive the first and second raised elements when the housing ( 27 ) and the stationary outer structure ( 15 ) are mounted edge to edge; and an abutment means formed so as to keep the first and second raised elements in the recess.

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Номер записи: 29

13-09-2012 дата публикации

Combustion chamber having a ventilated spark plug

Номер: US20120227373A1

Автор: Guillaume Sevi, Jacques Marcel Arthur Bunel, Mario César De Sousa

Принадлежит: SNECMA SAS

A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.

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Номер записи: 30

13-09-2012 дата публикации

Centerline generator support system and method of elevating a centerline generator from a support surface

Номер: US20120228974A1

Автор: Donald Michael Ronca, Jayan Kaadaapuram George, John Russell Yagielski, Ronald Joseph Rinaolo

Принадлежит: General Electric Co

A generator support system for a centerline mounted generator includes a generator support member configured and disposed to support a generator upon a support surface. The generator support member includes at least one lifting element having a lifting surface that faces the support surface.

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Номер записи: 31

20-09-2012 дата публикации

Combustor Liner and Flow Sleeve Tool

Номер: US20120233845A1

Автор: Mustafa Gerengi

Принадлежит: General Electric Co

A tool includes an annular frame portion including a mount portion extending radially from the frame portion, a hook portion arranged on the mount portion, the hook portion sized and shaped to engage a member of a tubular component of a turbine combustor, and a force exertion portion arranged on the mount portion, the force exertion portion operative to engage a portion of the turbine combustor.

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Номер записи: 32

20-09-2012 дата публикации

Turbocharger

Номер: US20120237343A1

Автор: Yoshimitsu Matsuyama

Принадлежит: IHI Corp

A variable geometry turbocharger includes a bearing housing rotatably supporting a turbine impeller; and an exhaust nozzle changing the flow rate of an exhaust gas supplied to the turbine impeller, wherein the exhaust nozzle has an exhaust inlet wall disposed at the bearing housing side, the turbocharger has a seal member exhibiting a ring shape and sealing a gap formed between the bearing housing and the exhaust inlet wall, and an inner circumferential edge of the seal member firmly contacts the bearing housing and an outer circumferential edge of the seal member firmly contacts the exhaust inlet wall.

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Номер записи: 33

06-12-2012 дата публикации

Integrated fuel nozzle and ignition assembly for gas turbine engines

Номер: US20120304651A1

Автор: Bhawan B. Patel, Enzo Macchia, George Guglielmin, Oleg Morenko

Принадлежит: Pratt and Whitney Canada Corp

There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.

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Номер записи: 34

20-12-2012 дата публикации

Flow Machine

Номер: US20120321450A1

Автор: Carsten Bennewa, Christian ROESNER, Emil Aschenbruck

Принадлежит: MAN Diesel and Turbo SE

A flow machine includes two structural component parts that cooperate with one another by a bellows seal so that the bellows seal forms a medium barrier between two spaces of the flow machine which directly adjoin the two structural component parts. The flow machine is constructed as a gas turbine, and one space of the two spaces is a hot-gas space of a high-pressure stage of the gas turbine.

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Номер записи: 35

03-01-2013 дата публикации

Impingement cooled nozzle liner

Номер: US20130001319A1

Автор: Curtis C. Cowan, Jorge I. Farah

Принадлежит: Individual

A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.

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Номер записи: 36

10-01-2013 дата публикации

Apparatus and systems relating to fuel injectors and fuel passages in gas turbine engines

Номер: US20130008169A1

Автор: Donald Timothy Lemon, Keith Cletus Belsom

Принадлежит: General Electric Co

A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold.

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Номер записи: 37

17-01-2013 дата публикации

Contained shaft spring load

Номер: US20130017113A1

Автор: Steven A. Heitz, Timothy P. Walgren

Принадлежит: Hamilton Sundstrand Corp

An input shaft assembly is movable along an axis to absorb external impact loads. A biasing member exerts an axial load in a direction counter to potential impact loads. A stop is provided to control the application of biasing loads to control application of such axial load.

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Номер записи: 38

31-01-2013 дата публикации

Strut, a gas turbine engine frame comprising the strut and a gas turbine engine comprising the frame

Номер: US20130028718A1

Автор: Jonas Lindskog, Linda STRÖM, Per Widström

Принадлежит: Volvo Aero Corp

A strut is provided for being arranged between an annular inner structural casing and an annular outer structural casing in a gas turbine engine frame for carrying loads between the inner and outer structural casing during operation. The strut includes a first tube, which is configured to house a service line or pipe between the inner and outer structural casing. The strut includes a second tube, which is configured to house a fastening element for rigidly connecting the inner and outer structural casing. The first and second tube are arranged in a side-by-side relationship and rigidly attached to each other.

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Номер записи: 39

31-01-2013 дата публикации

Power generation unit startup evaluation

Номер: US20130030582A1

Автор: Antonio Chamblin, Kenneth Clifford Barnett

Принадлежит: Southern Company Services Inc

Various methods and systems are provided for evaluation of events such as the startup of power generation units. In one embodiment, a method includes obtaining operational data associated with a power generation unit, the operational data corresponding to a predefined period of time; determining start and end times for a startup phase associated with the power generation unit based upon a set of predefined startup conditions corresponding to the startup phase; and generating a network page including the start and times. In another embodiment, a system includes a unit evaluation system executable in a computing device that includes logic that obtains operational data associated with a power generation unit, the operational data corresponding to a predefined period of time and logic that determines start and end times for an event phase associated with the power generation unit based upon a set of predefined conditions corresponding to the event phase.

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Номер записи: 40

28-02-2013 дата публикации

Method and Apparatus to Provide Sealing Contact Between First and Second Fueldraulic Components

Номер: US20130049301A1

Автор: Kevin M. Ryan

Принадлежит: Hamilton Sundstrand Corp

According to one aspect, an apparatus to provide sealing contact between first and second fueldraulic components includes a metallic member, wherein the metallic member comprises a layer of metal that is formed into a spring energized seal member. The apparatus also includes a layer disposed on an outer portion of the metallic member to provide sealing contact between the first and second fueldraulic components.

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Номер записи: 41

28-02-2013 дата публикации

Nacelle assembly having integrated afterbody mount case

Номер: US20130052005A1

Автор: Thomas G. Cloft

Принадлежит: Individual

A nacelle assembly for a gas turbine engine includes an integrated afterbody mount case. The integrated afterbody mount case includes an outer ring and a plurality of spokes that extend radially inwardly from the outer ring. The outer ring includes a radially outer surface and a radially inner surface. The plurality of spokes are circumferentially disposed about the radially inner surface and extend radially inwardly from the radially inner surface.

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Номер записи: 42

14-03-2013 дата публикации

Fuel manifold cooling flow recirculation

Номер: US20130061599A1

Автор: Frederick Ehrwulf Van Alen

Принадлежит: General Electric Co

Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow according to at least some aspects of the present disclosure may include a flow split valve having a spool valve disposed therein, the flow split valve having a pilot manifold and a main manifold attached thereto; a jet pump fluidically coupled to the pilot manifold, the jet pump being arranged to drive recirculation of a cooling flow through the main manifold via a cooling flow circuit in a pilot only mode of operation; and/or a fuel nozzle in fluid communication with the pilot manifold and the main manifold.

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Номер записи: 43

14-03-2013 дата публикации

Aerofoil assembly

Номер: US20130064661A1

Автор: Dale E. Evans, Ian C D Care

Принадлежит: Rolls Royce PLC

This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.

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Номер записи: 44

21-03-2013 дата публикации

FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE

Номер: US20130067919A1

Автор: OGATA Hideki

Принадлежит: KAWASAKI JUKOGYO KABUSHIKI KAISHA

A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force. 1. A fuel supply device of a gas turbine engine , which supplies a fuel to a combustor including a pilot burner and a main burner; the fuel supply device comprising:a pilot fuel passage through which the fuel is supplied to the pilot burner;a main fuel passage through which the fuel is supplied to the main burner;a collecting fuel passage through which the fuel is supplied to the pilot fuel passage and to the main fuel passage; anda fuel divider which divides the fuel supplied from the collecting fuel passage to feed the fuel to the pilot fuel passage and to the main fuel passage;wherein the fuel divider includes:a fuel entrance into which the fuel supplied from the collecting fuel passage is introduced;a pilot port connected to the pilot fuel passage;a main port connected to the main fuel passage;a movable member which is movable according to a fuel pressure at the fuel entrance, the movable member being configured to open only the pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and to open both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure; andan adjusting means for adjusting a value of the first pressure in such a manner that the adjusting means ...

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Номер записи: 45

21-03-2013 дата публикации

FUEL INJECTOR AND SWIRLER ASSEMBLY WITH LOBED MIXER

Номер: US20130067920A1

Автор: Fox Timothy A., Van Kampen Jaap, Williams Steven, Wörz Ulrich

Принадлежит:

Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly. 115-. (canceled)16. A gas turbine fuel injector and swirler assembly , comprising:a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly;a first fuel supply channel arranged in the delivery tube structure;a shroud surrounding the delivery tube structure;a plurality of swirl vanes arranged between the delivery tube structure and the shroud;a radial passage in each swirl vane, communicating with the first fuel supply channel;a set of apertures open between the radial passage and the exterior surface of each swirl vane; anda second fuel supply channel arranged in the delivery tube structure extending to a downstream end of the delivery tube structure,wherein a mixer with a plurality of lobes for fuel injection is arranged at the downstream end.17. The fuel injector and swirler assembly as claimed in claim 16 , wherein the delivery tube structure comprises coaxial cylindrical inner and outer tubes claim 16 , providing the first fuel supply channel in the inner tube and forming the annular second fuel supply channel between the inner and outer tubes.18. The fuel injector and swirler ...

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Номер записи: 46

21-03-2013 дата публикации

Multiple Tube Premixing Device

Номер: US20130067926A1

Автор: Felling David, Kraemer Gilbert Otto, Lacy Benjamin, Stevenson Christian, Uhm Jong Ho, Varatharajan Balachandar, Yilmaz Ertan, Ziminsky Willy Steve

Принадлежит: GENERAL ELECTRIC COMPANY

The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. 1. A premixer for a combustor , comprising: a plurality of fuel tubes comprising a first plurality of fuel tubes and a second plurality of fuel tubes:', 'a first chamber in communication with the first plurality of fuel tubes; and', 'a second chamber in communication with the second plurality of fuel tubes; and, 'a fuel plenum comprisinga burner tube comprising a plurality of air tubes,wherein the plurality of fuel tubes extend about the plurality of air tubes.2. The premixer of claim 1 , wherein the burner tube comprises a bell mouth at a first end and a burner tube nozzle at a second end.3. The premixer of claim 2 , wherein the plurality of air tubes extends from the bell mouth to the burner tube nozzle.4. The premixer of claim 1 , further comprising a plurality of spacers positioned between the fuel plenum and the burner tube.5. The premixer of claim 1 , wherein the fuel plenum comprises a chamber in communication with the plurality of fuel tubes.68-. (canceled)9. The premixer of claim 1 , wherein the first plurality of fuel tubes surrounds the second plurality of fuel tubes.10. The premixer of claim 1 , wherein the plurality of air tubes comprises a first diameter claim 1 , wherein the plurality of fuel tubes comprises a second diameter claim 1 , and wherein the first diameter is larger than the second diameter.11. A method of mixing a first flow and a second flow claim 1 , comprising:dividing the first flow into a plurality first flow tubes;dividing the second flow into a plurality of second flow tubes;placing the plurality of first flow tubes about the plurality of second flow tubes; andmixing the first flow and the second flow within the plurality of second flow tubes.12. The method of claim 11 , further comprising dividing a third flow into a ...

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Номер записи: 47

21-03-2013 дата публикации

Wall structure with noise damping insulation properties and gas turbine with such a wall structure

Номер: US20130071231A1

Автор: Antun Svilicic, Eduard Bruhwiler, Marc Rauch, Mladen Matan

Принадлежит: Alstom Technology AG

A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

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Номер записи: 48

28-03-2013 дата публикации

Motor-generator turbomachine starter

Номер: US20130076035A1

Автор: Adam M. Finney, Andreas C. Koenig

Принадлежит: Hamilton Sundstrand Corp

An exemplary turbomachine starter assembly includes a motor-generator that selectively operates in a motor mode or a generator mode. The motor-generator provides a rotational input to a turbomachine when operating in the motor mode. The motor-generator generates a supply of electrical power when operating in the generator mode. The supply of electrical power is used to power accessories of the turbomachine.

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Номер записи: 49

04-04-2013 дата публикации

GUIDE AND SEALING DEVICE FOR A TURBINE ENGINE, THE DEVICE HAVING A CARBON GASKET AND AN INTEGRATED SMOOTH BEARING

Номер: US20130081405A1

Автор: Galivel Jean-Pierre Elie

Принадлежит: SNECMA

A guide and sealing device a shaft in an orifice in a casing in a turbine engine, the device including a carbon gasket mounted around the shaft including a ring secured to the shaft and having an annular friction face rubbing against a carbon annulus mounted in a support bushing fastened to the casing, the ring presenting a cylindrical wall that is centered and guided in rotation in a cylindrical wall of the support bushing so as to form a smooth bearing for guiding the shaft. 110-. (canceled)11. A guide and sealing device for mounting in an orifice in a casing through which a shaft passes in a turbine engine , the device comprising:a carbon gasket mounted around the shaft in the orifice of the casing and comprising a ring that is carried by the shaft and that has an annular friction face for rubbing against a carbon annulus that is mounted in a support bushing fastened to the casing and that is urged axially towards the ring;wherein the ring includes a cylindrical wall that is centered and guided in rotation in a cylindrical wall of the support bushing so as to form a smooth bearing for guiding the shaft.12. A device according to claim 11 , wherein the cylindrical wall of the ring is formed as a single piece with the ring or is a fitting that is fastened to the ring.13. A device according to claim 11 , wherein the cylindrical wall of the ring presents an outer cylindrical surface that is coated in a thin layer or that is surrounded by a hoop claim 11 , the thin layer or the hoop being made of a material that is hard and has a low coefficient of friction.14. A device according to claim 11 , wherein the inner cylindrical surface of the cylindrical wall of the ring defines an annular groove opening out axially away from the carbon annulus and into which cooling oil is to be injected.15. A device according to claim 11 , wherein the cylindrical wall of the support bushing is made as a single piece with the support bushing or is a fitting that is fastened to the bushing. ...

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Номер записи: 50

11-04-2013 дата публикации

Low Emission Power Generation Systems and Methods

Номер: US20130086916A1

Автор: Minta Moses, Oelfke Russell H.

Принадлежит:

Methods and systems for C0separation for low emission power generation in combined-cycle power plants are provided. One system includes a gas turbine system that stoichiometrically combusts a fuel and an oxidant in the presence of a compressed recycle stream to provide mechanical power and a gaseous exhaust. The compressed recycle stream acts as a diluent to moderate the temperature of the combustion process. A boost compressor can boost the pressure of the gaseous exhaust before being compressed into the compressed recycle stream. A purge stream is tapped off from the compressed recycle stream and directed to a C0separator configured to absorb C0from the purge stream using a potassium carbonate solvent. 1. An integrated COseparation system , comprising:a gas turbine system having a combustion chamber configured to stoichiometrically combust a compressed oxidant and a fuel in the presence of a compressed recycle stream in order generate a discharge stream, which is expanded in an expander, thereby generating a gaseous exhaust stream and at least partially driving a main compressor, wherein the compressed recycle stream acts as a diluent configured to moderate the temperature of the discharge stream;an exhaust gas recirculation system having at least one of a boost compressor and one or more cooling units configured to increase the mass flow rate of the gaseous exhaust stream to provide a cooled recycle gas to the main compressor, wherein the main compressor compresses the cooled recycle gas and generates the compressed recycle stream, a portion of which is directed to the combustion chamber and a portion of which provides a purge stream; and{'sub': 2', '2, 'claim-text': [{'sub': '2', 'an absorber column configured to receive the purge stream and circulate a potassium carbonate solvent therein to absorb COin the purge stream, wherein the absorber column discharges a nitrogen-rich residual stream and a bicarbonate solvent solution;'}, 'a first valve fluidly coupled to ...

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Номер записи: 51

11-04-2013 дата публикации

Method of heating gas turbine inlet

Номер: US20130087219A1

Автор: Bradly Aaron Kippel, Prabhakaran Saraswathi Rajesh, Rahul Jaikaran Chillar, Ricky Daryl Conard

Принадлежит: General Electric Co

An air inlet system delivers a flow of air. The system included a temperature controlling section configured to alter temperature of the air flow. The temperature controlling section imparts a temperature variation distribution across different portions of the air flow. The system also includes a transition section, one or more flow diverters, one or more screens and/or a flow splitter to cause mixing of the different, temperature variant portions of the air flow and reduce the temperature variation distribution.

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Номер записи: 52

18-04-2013 дата публикации

GAS TURBINE AND GAS-TURBINE PLANT HAVING THE SAME

Номер: US20130091824A1

Автор: Fujii Satoko, Higashi Kazuya, Matsumoto Keigo, Murakami Masayuki, Nakamoto Yukimasa, Shimizu Takeyuki

Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

The invention provides a gas-turbine fuel nozzle () that includes a plurality of fuel supply channels () to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels () to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes () that are provided at downstream ends of the fuel supply channels () or the fuel/scavenging-fluid supply channels () and that inject the fuel guided from the fuel supply channels () or the fuel/scavenging-fluid supply channels (); a scavenging-fluid supply channel () that is connected to the fuel/scavenging-fluid supply channels () to guide the scavenging fluid; and scavenging-fluid cooling means () for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel. 1. A gas turbine comprising:a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes that are provided at downstream ends of the fuel supply channels or the fuel/scavenging-fluid supply channels and that inject the fuel or the scavenging fluid guided from the fuel supply channels or the fuel/scavenging-fluid supply channels;a scavenging-fluid supply channel that is connected to the fuel/scavenging-fluid supply channels and guides the scavenging fluid; andscavenging-fluid cooling means for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.2. A gas turbine according to claim 1 ,wherein the scavenging-fluid supply channel is connected to the fuel/scavenging-fluid supply channels and to a casing of the gas turbine and guides, as the scavenging fluid, a fluid extracted from the casing; andthe scavenging-fluid cooling means is a plurality of projections that are provided around the scavenging-fluid supply channel.3. A gas turbine ...

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Номер записи: 53

18-04-2013 дата публикации

Method and a device for producing a setpoint signal

Номер: US20130091851A1

Автор: Alexandra Riou, Bruno Robert Gaully, Cedrik Djelassi

Принадлежит: SNECMA SAS

A method and device producing a setpoint signal representing a flow rate of fuel that a metering unit having a slide valve is to supply to a fuel injection system of a combustion chamber in a turbine engine, the position of the valve depending on the setpoint signal. The method: obtains a first signal representing a measurement as delivered by a flow meter of a flow rate of fuel injected into the chamber; evaluates a second signal representing the flow rate of fuel injected into the chamber based on a measurement of the position of the valve; estimates a third signal representative of the measurement delivered by the flow meter by applying a digital model of the flow meter to the second signal; and produces the setpoint signal by adding a compensation signal to the first signal, the compensation signal obtained by subtracting the third signal from the second signal.

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Номер записи: 54

25-04-2013 дата публикации

Hydrajetting Nozzle and Method

Номер: US20130098043A1

Автор: Surjaatmadja Jim B.

Принадлежит: Halliburton Energy Services, Inc.

A jetting device comprises a body, and an interior flow path within the body. The interior flow path comprises a flow section, an expansion section, and a shoulder formed at the intersection of the flow section and the expansion section. The length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the nozzle when the fluid is flowing through the nozzle. 1. A jetting device comprising:a body; and a flow section;', 'an expansion section; and', 'a shoulder formed at the intersection of the flow section and the expansion section, wherein the length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the jetting device when the fluid is flowing through the jetting device., 'an interior flow path within the body, wherein the interior flow path comprises2. The jetting device of claim 1 , wherein a length and a diameter of an expansion section of the jetting device are configured such that a fluid stream diameter of a fluid stream discharged from the jetting device is less than the diameter of the expansion section at an outer end of the jetting device.3. The jetting device of claim 1 , wherein the portion of the pressure of the fluid downstream of the expansion section is at least about 10% of the pressure of the fluid downstream of the expansion section.4. The jetting device of claim 1 , wherein the portion of the pressure of the fluid downstream of the expansion section is less than about 80% of the pressure of the fluid downstream of the expansion section.5. A flow device comprising:a body; and a flow section;', 'an expansion section; and', 'a shoulder formed at the intersection of the flow section and the expansion section, wherein the length and diameter of the expansion section are configured to control the ...

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Номер записи: 55

25-04-2013 дата публикации

Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing

Номер: US20130098066A1

Автор: Audrey Grede, Francois Gallet

Принадлежит: SNECMA SAS

The present invention relates to an open rotor type aircraft turbine engine ( 1 ), comprising a contrarotating propeller receiver ( 30 ) and a dual-body gas generator ( 14 ) comprising a low-pressure compressor ( 16 ) and a high-pressure compressor ( 18 ) separated by an intermediate housing ( 27 ), said gas generator being arranged upstream from said receiver. According to the invention, the turbine engine further comprises a structural casing ( 50 ) for supporting the receiver ( 30 ), surrounding the gas generator ( 14 ) and having a downstream end ( 50 a ) attached to said receiver and an upstream end ( 50 b ) attached to said intermediate housing ( 27 ). Furthermore, it comprises additional connection means ( 60 ) between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends ( 50 b , 50 a ) of the casing.

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Номер записи: 56

09-05-2013 дата публикации

Aircraft ignition system and method of operating the same

Номер: US20130111914A1

Автор: Steve J. Kempinski

Принадлежит: CHAMPION AEROSPACE LLC

An aircraft ignition system having a power circuit, a control circuit, and a discharge circuit and coupled to the spark plugs of an aircraft engine. The power circuit may include two independent power sources; e.g., alternator power (such as a permanent magnet alternator) and power from aircraft or DC power bus. The control circuit may control one or more aspects of the discharge circuit, e.g., the ignition timing. And the discharge circuit may trigger a capacitive discharge ignition event to the spark plugs.

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Номер записи: 57

09-05-2013 дата публикации

ASSEMBLY COMPRISING A SHAFT SEAL

Номер: US20130115049A1

Автор: Grieshaber Dirk

Принадлежит:

A shaft seal includes more than one sealing module, at least one fluid supply and a fluid discharge, and a main seal which is subject to a greatest partial pressure difference. A second main seal is a radial double seal, which includes two gas seals, each gas seal having a rotating sealing surface and a stationary sealing surface, wherein the two sealing surface pairs are located opposite each other in a sealing plan, and wherein the two sealing planes have substantially radial extension to the shaft. 114.-. (canceled)15. A shaft seal for sealing a gap of a penetration of a shaft through a casing ,wherein the shaft seal comprises a plurality of sealing modules,wherein in the interior of the casing there is a process fluid having a sealing pressure, and outside the casing there is an ambient fluid having an ambient pressure,wherein the ambient pressure differs from the sealing pressure by a pressure differential, which pressure differential, divided into proportions, is applied to individual sealing modules of the plurality of sealing modules as partial pressure differentials,wherein the plurality of sealing modules comprises a first main seal, wherein a greatest partial pressure differential is applied to the first main seal,wherein, between the plurality of sealing modules, a fluid drain is provided for discharging a first drain fluid,wherein the first main seal is a simple gas seal and is designed such that, during normal trouble-free operation and during starting and shutting down, the greatest partial pressure differential is applied to the first main seal, starting from the highest pressure level from the inside outwards,wherein the plurality of sealing modules comprises s second main seal which is designed such that, in an event of a malfunction of the first main seal, the greatest partial pressure differential is applied to the second main seal, starting from the highest pressure level from the inside outwards,wherein the second main seal is a radial double ...

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Номер записи: 58

16-05-2013 дата публикации

HYBRID FOSSIL FUEL AND SOLAR HEATED SUPERCRITICAL CARBON DIOXIDE POWER GENERATING SYSTEM AND METHOD

Номер: US20130118145A1

Автор: Brown, Fetvedt Jeremy Eron, Freed David Arthur, JR. Glenn William, Palmer Miles R.

Принадлежит:

The present disclosure provides an integrated power generating system and method that combines combustion power generation with solar heating. Specifically, a closed cycle combustion system utilizing a carbon dioxide working fluid can be increased in efficiency by passing at least a portion of a carbon dioxide working fluid through a solar heater prior to passage through a combustor. 1. A method of generating power , the method comprising:{'sub': 2', '2', '2, 'passing a COcontaining stream from a primary combustor through a turbine to expand the COcontaining stream, generate power, and form a turbine exhaust stream comprising CO;'}{'sub': '2', 'cooling the turbine exhaust stream comprising COin a heat exchanger to form a cooled turbine exhaust stream;'}{'sub': 2', '2, 'pressurizing COfrom the cooled turbine exhaust stream to form a pressurized COcontaining stream;'}{'sub': '2', 'heating the pressurized COcontaining stream in the heat exchanger;'}{'sub': '2', 'further heating the pressurized COcontaining stream with a solar heater; and'}{'sub': '2', 'passing the pressurized and solar heated COcontaining stream to the primary combustor.'}2. The method of claim 1 , wherein the COcontaining stream entering the turbine is at a pressure of about 150 bar (15 MPa) or greater.3. The method of claim 1 , wherein the COcontaining stream entering the turbine is at a temperature of about 500° C. or greater.4. The method of claim 1 , wherein the ratio of the pressure of the COcontaining stream entering the turbine to the pressure of the turbine exhaust stream comprising COis about 12 or less.5. The method of claim 1 , wherein the step of pressurizing the COcontaining stream comprises passing the stream through a plurality of pressurization stages.6. The method of claim 5 , further comprising cooling the COcontaining stream between two pressurization stages.7. The method of claim 1 , wherein a portion of the pressurized COcontaining stream is heated with supplemental heat after the ...

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Номер записи: 59

16-05-2013 дата публикации

FUEL INJECTION SYSTEM FOR TURBOJET ENGINE AND METHOD OF ASSEMBLING SUCH AN INJECTION SYSTEM

Номер: US20130118177A1

Автор: Bunel Jacques Marcel Arthur, De Sousa Mario César, Demoulin Brice Arnaud, Sevi Guillaume

Принадлежит: SNECMA

A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion. 1. A fuel injection system for a turbojet engine , comprising:a fixed portion and a sliding cross-member, the fixed portion and the sliding cross-member extending along a reference axis, the fixed portion comprising a cavity defined axially by a base and a closing cup, the sliding cross-member being provided with a flange contained in the cavity; anda spring disposed in the cavity so as to exert an axial force on the flange.2. The injection system as claimed in claim 1 , wherein the spring comprise comprises a corrugated plate.3. The injection system as claimed in claim 2 , wherein the corrugated plate is circular.4. The injection system as claimed in claim 1 , wherein the spring is axially constrained in the cavity.5. The injection system as claimed in claim 1 , comprising a washer disposed between the spring and the flange.6. The injection system as claimed in claim 1 , wherein the spring is configured to exert a force in the range 10 Newtons to 30 Newtons on the flange.7. A combustion chamber comprising at least one injection system as claimed in claim 1 , the sliding cross-member further comprising a centring cone in which a fuel injector is inserted.8. An aircraft engine comprising a combustion chamber as claimed in .9. A method for assembling an injection system comprising a fixed ...

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Номер записи: 60

16-05-2013 дата публикации

PROCEDURE FOR IGNITING A TURBINE ENGINE COMBUSTION CHAMBER

Номер: US20130118181A1

Автор: Maurice, Pieussergues Christophe, Sandelis Denis Jean

Принадлежит: SNECMA

A procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%. 17-. (canceled)8. A method for igniting a combustion chamber of a turbine engine , the chamber being fed with fuel by injectors and including igniter means for igniting the fuel injected into the chamber , the method comprising:an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter means; andin event of non-ignition of the chamber at an end of the initial stage, comprising a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%;the second stage being followed by a stage of progressively increasing the fuel flow rate by an amount that is smaller and slower than in the second stage.9. A procedure according to claim 8 , wherein the initial stage has a duration of about 5 to 8 seconds claim 8 , and in the second stage the rapid increase in the fuel flow rate takes place over a time of about 1 to 2 seconds.10. A procedure according to claim 8 , wherein the progressive increase in the fuel flow rate lasts for about 10 to 15 seconds.11. A procedure according to claim 10 , wherein the fuel flow rate from the injectors at an end of the progressive increase is greater than about 50% to 80% of the constant flow rate during the initial stage.12. A procedure according to claim 8 , wherein a speed of rotation of the engine increases progressively during the first and second stages.13. A procedure according to claim 8 , wherein all of the injectors are ...

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Номер записи: 61

16-05-2013 дата публикации

LEAF SEAL

Номер: US20130119612A1

Автор: JAHN Ingo Henry Johannes

Принадлежит: ROLLS-ROYCE PLC

A leaf seal is provided for effecting a seal between two coaxial, relatively rotating components. The leaf seal has a pair of annular packs of stacked leaves. Each pack is mountable to one of the components with its leaves extending towards the other component such that the leaf edges of at least one of the packs are presented for wiping contact with the other component. The packs are axially spaced from each other by a controlled axial clearance. Within each pack the leaves are stacked face-to-face such that neighbouring leaves are separated from each other by interleaf gaps which allow an axial leakage flow through the seal. Further, within each pack the packs are positioned such that, when viewed in the axial direction, the leaves of each pack of the pair substantially obscure the interleaf gaps of the other pack of the pair. The controlled axial clearance is the dominant flow restriction in the seal determining the amount of leakage flow through the seal. 1. A leaf seal for effecting a seal between two coaxial , relatively rotating components , the leaf seal having a pair of annular packs of stacked leaves , each pack being mountable to one of the components with its leaves extending towards the other component such that the leaf edges of at least one of the packs are presented for wiping contact with the other component , and the packs being axially spaced from each other by a controlled axial clearance;wherein within each pack the leaves are stacked face-to-face such that neighbouring leaves are separated from each other by interleaf gaps which allow an axial leakage flow through the seal, and the packs are positioned such that, when viewed in the axial direction, the leaves of each pack of the pair substantially obscure the interleaf gaps of the other pack of the pair; andwherein the controlled axial clearance is the dominant flow restriction in the seal determining the amount of leakage flow through the seal.2. A leaf seal according to claim 1 , wherein each ...

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Номер записи: 62

16-05-2013 дата публикации

LEAF SEAL

Номер: US20130119613A1

Автор: JAHN Ingo Henry Johannes

Принадлежит: ROLLS-ROYCE PLC

A leaf seal is provided for effecting a seal between two coaxial, relatively rotating components. The leaf seal has an annular pack of leaves which are stacked face-to-face within the pack, and which are mountable to one of the components at respective root portions of the leaves such that the leaves extend towards the other component and respective edges of the leaves are presented for wiping contact with the other component. The pack includes a plurality of spacers, each spacer separating the root portions of neighbouring leaves to form therebetween interleaf gaps which allow an axial leakage flow through the pack. The spacers are distributed around the pack such that the leaves are divided into blocks of two or more leaves sandwiched at their root portions between nearest-neighbour spacers. 1. A leaf seal for effecting a seal between two coaxial , relatively rotating components , the leaf seal having an annular pack of leaves which are stacked face-to-face within the pack , and which are mountable to one of the components at respective root portions of the leaves such that the leaves extend towards the other component and respective edges of the leaves are presented for wiping contact with the other component;wherein the pack includes a plurality of spacers, each spacer separating the root portions of neighbouring leaves to form therebetween interleaf gaps which allow an axial leakage flow through the pack; andwherein the spacers are distributed around the pack such that the leaves are divided into blocks of two or more leaves sandwiched at their root portions between nearest-neighbour spacers.2. A leaf seal according to claim 1 , wherein within each block the leaves make face-to-face contact with their nearest-neighbour leaves in the block over substantially their entire lengths from their respective root portions to their respective wiping contact edges.3. A leaf seal according to claim 1 , wherein the spacers are distributed such that the number of leaves in ...

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Номер записи: 63

16-05-2013 дата публикации

Flexible seal system for a gas turbine engine

Номер: US20130121813A1

Автор: Jocelyn C. Damgaard, Steven D. Roberts, Timothy Dale

Принадлежит: United Technologies Corp

A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

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Номер записи: 64

23-05-2013 дата публикации

PREHEATING A SPARK PLUG

Номер: US20130125558A1

Автор: Chatenet Luc Henri, Schaeffer Christian, Stifanic David

Принадлежит: SNECMA

A method of igniting a turbine engine using a spark plug including a first electrode, a second electrode, and a semiconductor body between the first electrode and the second electrode, the semiconductor body having an exposed surface, the ignition method including: generating a spark adjacent to the exposed surface by applying a voltage difference greater than a first predetermined threshold between the first electrode and the second electrode; and prior to generating a spark, a preheating applying a voltage difference less than a second predetermined threshold between the first electrode and the second electrode, the second predetermined threshold being less than the first predetermined threshold. 110-. (canceled)11. A method of igniting a turbine engine using a spark plug including a first electrode , a second electrode , and a semiconductor body between the first electrode and the second electrode , the semiconductor body having an exposed surface , the ignition method comprising:generating a spark adjacent to the exposed surface by applying a voltage difference greater than a first predetermined threshold between the first electrode and the second electrode; andprior to generating a spark, a preheating including applying a voltage difference less than a second predetermined threshold between the first electrode and the second electrode, the second predetermined threshold being less than the first predetermined threshold.12. An ignition method according to claim 11 , wherein the preheating has a predetermined duration greater than 5 seconds.13. An ignition method according to claim 11 , wherein the first predetermined threshold is greater than 900 V.14. An ignition method according to claim 11 , wherein the second predetermined threshold is less than 900 V.15. An ignition method according to claim 14 , wherein the second predetermined threshold is less than or equal to 100 V.16. An ignition method according to claim 11 , wherein claim 11 , during the preheating ...

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Номер записи: 65

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: 66

23-05-2013 дата публикации

LATERAL TURBOJET IMPROVED IN ORDER TO LIMIT THE DEFORMATION THEREOF

Номер: US20130125560A1

Автор: BELLABAL François Robert

Принадлежит: SNECMA

A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a coaxial relationship by arms with at least some of the arms being shaped and/or arranged to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure in opposition to opposing stress generated by the thrust. 19-. (canceled)10. A two-stream turbojet for attaching laterally to a fuselage of an airplane via two longitudinally spaced apart suspensions including a front suspension and a rear suspension , the turbojet comprising:an intermediate casing outer shroud attached to the front suspension; anda propulsion primary structure attached to the rear suspension;the intermediate casing outer shroud and the primary structure being held in a coaxial relationship by a set of arms, each arm including a right section that is hollow and being fastened by its ends to the shroud and to the primary structure; andwherein at least some of the arms are shaped and/or arranged so as to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure, the deforming torque having a direction opposite to stress that is generated under effect of the turbojet thrust by a lever arm between the thrust axis and the front suspension.11. A turbojet according to claim 10 , wherein the at least some of the arms are configured to provide coupling between shear and twisting so that a center of torsion of a right section of the arm is situated outside a midplane of the arm claim 10 , on a side opposite from the front suspension relative to the midplane.12. A turbojet according to claim 10 , wherein at least some of the arms include a slot extending from the shroud to the primary structure.13. A turbojet according to claim 12 , wherein the slot is closed by an elastomer seal.14. A turbojet ...

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Номер записи: 67

30-05-2013 дата публикации

Starter Control Valve Prediction System to Predict and Trend Starter Control Valve Failures in Gas Turbine Engines Using a Starter Control Valve Health Prognostic, Computer Readable Medium and Related Methods

Номер: US20130133306A1

Автор: Iyer Naresh Sundaram, Qiu Hai, Yan Weizhong

Принадлежит: LOCKHEED MARTIN CORPORATION

Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors. 1. A computer implemented method to predict starter control valve failures in gas turbine engines using a starter control valve health prognostic , the method comprising the steps of:extracting one or more health index features from operational gas turbine engine startup data received for one or more gas turbine engine startups of one or more gas turbine engines of a certain gas turbine engine model;calculating a starter control valve health index for each of the one or more gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data to thereby define one or more health indices;comparing each of the one or more health indices to a starter control valve health prognostic for the certain gas turbine engine model; anddetermining, responsive to the step of comparing, a potential predictive starter control valve failure point, the potential predictive starter control ...

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Номер записи: 68

30-05-2013 дата публикации

SEAL ARRANGEMENT AND A METHOD OF REPAIRING A SEAL ARRANGEMENT

Номер: US20130134682A1

Автор: Shaw Benjamin, TAYLOR Jonathan M.

Принадлежит: ROLLS-ROYCE PLC

The seal arrangement is arranged between the casing portions and a fluoropolymer O-ring seal is positioned between the casing portions. A first protecting member is positioned between the fluoropolymer O-ring seal and the casing portion and the first protecting member consists of a polymer and hydroxyapatite. The first protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities. The first protecting member is located in an annular groove and is thus arranged between the casing portion and the fluoropolymer O-ring seal. The first protecting member is substantially U-shaped in cross-section and the fluoropolymer O-ring seal is positioned between the legs of the U-shaped cross-section first protecting member. The first protecting member prevents corrosion of the casing portion by the fluoropolymer O-ring seal. 1. A seal arrangement between a first component and a second component , a fluoropolymer seal member is positioned between the first component and the second component and a first protecting member is positioned between the fluoropolymer seal member and the first component , the first protecting member consisting of a polymer and hydroxyapatite or apatite , wherein the first component comprises a metal.2. A seal arrangement as claimed in wherein a second protecting member is positioned between the fluoropolymer seal member and the second component claim 1 , the second protecting member consisting of a polymer and hydroxyapatite or apatite claim 1 , wherein the second component comprises a metal.3. A seal arrangement as claimed in wherein the first protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities.4. A seal arrangement as claimed in wherein the second protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities.5. A seal arrangement as claimed in wherein the polymer consists of polyimide.6. A seal ...

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Номер записи: 69

06-06-2013 дата публикации

FUEL NOZZLE AND METHOD OF REPAIR

Номер: US20130139513A1

Автор: Greer John, PATEL Bhawan B., Sampath Parthasarathy, Stastny Honza

Принадлежит: PRATT & WHITNEY CANADA CORP.

A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body. 1. A modular fuel nozzle tip for a gas turbine engine , the modular fuel nozzle tip comprising:a fuel conveying body defining one or more fuel conveying passages extending between an inlet end and an outlet end of the body, the outlet end having a head portion with a peripheral end surface, the head portion having web portions extending radially therefrom, and at least two projections extending from the end of said web portions;an annular cap circumscribing only the outlet of said fuel conveying body and having a radially inner shoulder surface interfacing with the peripheral end surface of the fuel conveying body, the peripheral end surface and the shoulder surface defining a plurality of air channels extending through the head portion of the modular fuel nozzle tip; andat least two fasteners fastening the annular cap to the fuel conveying body, said fasteners being circumferentially distributed about the annular cap, each of said fasteners extending through the annular cap and into one of the projections.2. The modular fuel nozzle tip according to claim 1 , wherein the at least two projections each contain a hole claim 1 , the annular cap contains at least two holes and the holes of the projections and the holes of the annular cap are circumferentially spaced and aligned.3. The modular fuel nozzle tip according to claim 2 , wherein each fastener extends through both the hole of one of the projections and one of the holes of the cap.4. The modular fuel nozzle tip according to claim 1 , wherein a concentric annular rim extends from the shoulder surface of the ...

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Номер записи: 70

06-06-2013 дата публикации

COMBUSTOR LINER SUPPORT AND SEAL ASSEMBLY

Номер: US20130139514A1

Автор: PETTY, Smiley Vickie Rae, SR. Jack Dwane, Taylor Todd S., Varney Bruce Edward

Принадлежит:

A method is disclosed herein for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner. The method comprises the step of disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement. 1. A method for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner comprising the of:disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement while substantially preventing relative circumferential movement.2. The method of further comprising the step of:limiting the extent of relative radial displacement between the combustor liner and the free-standing ring to a predetermined design amount.3. The method of further comprising the step of:disposing a seal of variable width between the combustor liner and the free-standing ring, the variable width varying in at least one of a radial direction and a circumferential direction relative to an axis along which the gas turbine engine extends.4. The method of wherein the rolling assembly rolls radially along a length of a surface defined by one of the combustor liner and the free-standing ring during the relative radial displacement.5. The method of wherein the rolling assembly substantially prevents relative circumferential movement between the combustor liner and the free-standing ring while permitting the relative radial displacement between the combustor liner and the free-standing ring in a radial direction.6. The method of wherein the rolling assembly is rotatably engaged with both the combustor liner and the free-standing ring.7. The method of wherein the rolling assembly includes a plurality of pins engaged between the combustor liner and the free-standing ring.8. The method of wherein the plurality of pins are each received in one of a plurality of slots ...

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Номер записи: 71

06-06-2013 дата публикации

Multi-spool intercooled recuperated gas turbine

Номер: US20130139519A1

Автор: James Kesseli, James S. Nash, John D. Watson, Thomas Wolf

Принадлежит: ICR Turbine Energy Corp USA

A method and apparatus are disclosed for a multi-spool gas turbine engine with a variable area turbine nozzle and a motor/alternator device on the highest pressure turbo-compressor spool for starting the gas turbine and power extraction during engine operation. During power down of the engine, the variable area turbine nozzle may be used in conjunction with power extraction to maintain a near constant combustor outlet temperature while controlling turbine inlet temperatures on the turbines downstream of the highest pressure turbine and controlling spool speed on the highest pressure turbine.

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Номер записи: 72

06-06-2013 дата публикации

METHOD FOR MONITORING A CONTROL DEVICE OF A FUEL METERING VALVE OF A TURBOJET ENGINE

Номер: US20130139520A1

Автор: Janati Idrissi Hicham, Lamoureux Benjamin Pierre, Marquisseau Francis, MASSE Jean-Rémi André, Sif Aziz

Принадлежит: SNECMA

A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current) to a servo valve in order to modify the position of the fuel metering valve, the method comprising: 1. Method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine , the control device supplying a control current to a servo valve in order to modify the position of the fuel metering valve , the method comprising:a step for determining the position of the fuel metering valve during a flight of the aircraft;a step for determining the travelling speed of the fuel metering valve;a step for determining the control current when the travelling speed of the fuel metering valve is zero;a step for calculating a mean control current when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration of the control device;a step for comparing the deterioration indicator with a reference base of indicators with deterioration so as to infer the type of deterioration from it;a step for calculating an abnormality score for the deterioration indicator;a step for comparing the abnormality score with a decision threshold of abnormality characteristic of the type of deterioration; anda step for releasing an alarm in case of violation of the decision threshold of abnormality.2. Method according to claim 1 , in which the deterioration indicator is normalized according to its standard deviation and average obtained over a plurality of flights during a learning phase.3. Method according to claim 2 , in which the abnormality score of the deterioration indicator is a function of the absolute value of the said normalized deterioration indicator.4. Method according to claim 1 , in which the reference base of indicators with deterioration comprises an indicator of deterioration of a positive drift and an indicator of deterioration of a negative drift.5. Method ...

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Номер записи: 73

06-06-2013 дата публикации

MULTI-LAYER ACOUSTIC TREATMENT PANEL

Номер: US20130142624A1

Автор: Julliard Jacques Michel Albert, Mardjono Jacky Novi, Poirier Benjamin Andre Francois, Riou Georges Jean Xavier, Ville Jean-Michel Jean-Francois

Принадлежит:

A multilayer acoustic treatment panel including a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; and a second cellular-structure core sandwiched between the intermediate skin and a continuous skin. The perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with the two ends of a soundwave flow channel arranged in the second cellular-structure core. 113-. (canceled)14. A multilayer acoustic treatment panel comprising:a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; anda second cellular-structure core sandwiched between the intermediate skin and a continuous skin;wherein the perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone that are longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with two ends of a soundwave flow channel arranged in the second cellular-structure core.15. A panel according to claim 14 , wherein the high-porosity zones of a given pair communicate with the soundwave flow channel via wells passing both through the first cellular-structure core and the intermediate skin.16. A panel according to claim 14 , wherein the high-porosity zones of a given pair communicate with the soundwave flow channel via wells passing through the first cellular-structure core and via a plurality of orifices formed through the intermediate skin.17. A panel according to claim 14 , wherein ...

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Номер записи: 74

06-06-2013 дата публикации

AIRFOIL SEAL SYSTEM FOR GAS TURBINE ENGINE

Номер: US20130142630A1

Автор: Diakunchak Ihor S.

Принадлежит: SIEMENS POWER GENERATION, INC.

A turbine airfoil seal system of a turbine engine having a seal base with a plurality of seal strips extending therefrom for sealing gaps between rotational airfoils and adjacent stationary components. The seal strips may overlap each other and may be generally aligned with each other. The seal strips may flex during operation to further reduce the gap between the rotational airfoils and adjacent stationary components. 1. An airfoil seal system for airfoils of a gas turbine engine , comprising:a seal base configured to be received within a channel of a rotational airfoil proximate to a platform extending from the airfoil, wherein the seal base is generally an arcuate segment and wherein the seal base is configured to extend a length at least substantially equal to a length along an intersection between a rotational airfoil and an adjacent stationary component;a plurality of seal strips generally aligned with each other and overlapping each other, wherein the plurality of seal strips are attached to the seal base and extend generally radially inward from the seal base a length sufficient to seal a gap between the platform of the rotational airfoil and the adjacent stationary component;wherein the plurality of seal strips are flexible such that the seal strips may be flexed during operation of the gas turbine engine thereby sealing the gap between the platform of the rotational airfoil and the adjacent stationary component.2. The airfoil seal system for airfoils of a gas turbine engine of claim 1 , wherein the plurality of seal strips are formed from alloys.3. The airfoil seal system for airfoils of a gas turbine engine of claim 1 , wherein the plurality of seal strips are curved out of plane from the seal base such that when the seal base is attached to the channel of a rotational airfoil claim 1 , ends of the plurality of seal strips curve toward adjacent stationary components.4. The airfoil seal system for airfoils of a gas turbine engine of claim 3 , wherein the ...

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Номер записи: 75

13-06-2013 дата публикации

SUBSTITUTION DEVICE FOR AIRCRAFT ENGINE

Номер: US20130145770A1

Автор: GARRIC Stephane, Vigneau Philippe

Принадлежит: AIRBUS OPERATIONS SAS

A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft. 2. The substitution device according to claim 1 , wherein the bearing portions are arranged substantially in an arc.5. The substitution device according to claim 1 , wherein the bearing portions are at least partially retractable.6. The substitution device according to claim 1 , further comprising a hydraulic unit and cylinders adapted for connecting the substitution device to at least the pair of covers.7. The substitution device according to claim 1 , further comprising wheels and a drawbar.8. The substitution device according to claim 1 , arranged in such a way that its center of gravity is located at or near the center of gravity of the engine which it replaces in the propulsion system.9. The substitution device according to claim 1 , further comprising lifting yokes. The present invention relates to substitution devices for an aircraft engine, in particular for turbojet engines.These substitution devices can be considered as support tools to assist with aircraft construction and maintenance. Under normal circumstances, such aircraft engines are usually attached to a supporting mast and protected by a nacelle which includes cowls (protective covers) surrounding the engine.According to known prior art, one (or several) engines must sometimes be removed for maintenance on said engine or for engine replacement. However, in order to remove an ...

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Номер записи: 76

13-06-2013 дата публикации

AIR RIDING SEAL ARRANGEMENT

Номер: US20130147123A1

Автор: Davies Christopher, JAHN Ingo Henry Johannes

Принадлежит: ROLLS-ROYCE PLC

An air riding seal arrangement comprises two components which are relatively rotatable so that aerodynamic forces causes a supporting air film to be generated between them. At least one of the components comprises a cylindrical surface provided with a rib The rib serves to restrict the flow of liquid, such as lubricant, deposited on the cylindrical surface towards the gap between the components The rib further serves to draw lubricant away from the gap by surface tension effects, when both of the components are stationary. 1. An air riding seal arrangement between two components that are rotatable relatively to each other about a rotational axis , the components comprising respective seal surfaces which are parallel to each other and are axially spaced apart , in operation of the seal arrangement , with respect to the rotational axis , at least one of the components having an axially extending circumferential surface extending from the radially outer periphery of the respective seal surface , the circumferential surface having a circumferential rib which extends freely from the circumferential surface at an axial position spaced from the seal surface.2. An air riding seal arrangement according to claim 1 , in which the component provided with the rib is cylindrical claim 1 , the seal surface of the respective component being perpendicular to the rotational axis.3. An air riding seal arrangement according to claim 1 , in which the axially extending circumferential surface is disposed radially outward of the radially outer periphery of the respective seal surface.4. An air riding seal arrangement according to claim 1 , in which the axial width of the circumferential rib is not greater than 25% of the axial length of the axially extending circumferential surface.5. An air riding seal arrangement according to claim 1 , in which the distance between the circumferential rib and the respective seal surface is not more than 25% of the axial length of the axial extending ...

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Номер записи: 77

20-06-2013 дата публикации

LEAF SEAL

Номер: US20130154199A1

Автор: WILLIAMS David Stephen

Принадлежит: ROLLS-ROYCE PLC

A leaf seal assembly provides a fluidic seal between a first and second member and includes first and second cover plates defining a channel, with a first and second edge, respectively. A plurality of leaf elements are located within the channel, each element having first and second edges adjacent to the first and second cover plates, respectively and a projecting portion of each element extends beyond both edges. A fluid flow in a first direction causes the leaf elements to move away from the first member to create a fluid passage between the elements and the member, allowing a flow through the seal in the first direction; and a fluid flow in a second direction causes the leaf elements to move towards the first member such that a third edge of the projecting portion of each element contacts the member, opposing the flow through the seal in the second direction. 1. A leaf seal assembly for providing a fluidic seal between a first member and a second member , comprising:first and second cover plates defining a channel therebetween, the first cover plate having a first inner edge and the second cover plate having a second inner edge;a plurality of leaf elements located within the channel, each leaf element having first and second leaf edges adjacent to the first and second cover plates respectively, wherein a projecting portion of each leaf element extends beyond the first and second inner edges;wherein the seal assembly is configured such that when it is located between a first member and a second member;a fluid flow in a first direction from the first cover plate side of the seal assembly to the second cover plate side of the seal assembly causes the plurality of leaf elements to move away from the first member to create a fluid passage between the plurality of leaf elements and the first member, thereby allowing a flow of fluid through the seal in the first direction; anda fluid flow in a second direction from the second cover plate side of the seal assembly to the ...

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Номер записи: 78

27-06-2013 дата публикации

Rigid raft

Номер: US20130160460A1

Автор: Gary Alan Skinner, Justin Dalton, Paul Broughton, Richard Peace, Robin Charles Kennea

Принадлежит: Rolls Royce PLC

The present invention provides a rigid raft formed of rigid composite material. The raft has an electrical system and/or a fluid system embedded therein. The raft further has a tank for containing liquid integrally formed therewith. The tank can be formed of the rigid composite material. The tank can be for a gas turbine engine.

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Номер записи: 79

27-06-2013 дата публикации

ELECTRONIC UNIT MOUNTING

Номер: US20130160461A1

Автор: BROUGHTON Paul, KENNEA Robin Charles, PEACE Richard, SKINNER Gary Alan

Принадлежит: ROLLS-ROYCE PLC

An electrical assembly comprising an electrical raft and an electronic unit is provided to a gas turbine engine . The electrical raft has electrical conductors embedded in a rigid material , which may be a rigid composite material. The electrical conductors are in electrical contact with the electronic unit . When the electronic unit is installed, at least a part of it forms a part of a gas-washed surface of the engine . The electronic unit is then easily accessible from the engine , and potentially complex and/or heavy access doors/panels may not be required. 1. A gas turbine engine having an electrical assembly that comprises:an electrical raft having a rigid material with at least one electrical conductor embedded therein; andan electronic unit mounted on the electrical raft and in electrical connection with the electrical raft, wherein:the electrical raft is mechanically fixed to another component of the gas turbine engine; andthe electronic unit forms at least a part of a gas-washed surface of the gas turbine engine.2. A gas turbine engine according to claim 1 , wherein:the electrical raft is provided with a first electrical connector in electrical contact with at least one of said embedded electrical conductors, the first electrical connector being fixed relative to the electrical raft;the electronic unit is provided with a second electrical connector, that is complimentary to the first electrical connector, the second electrical connector being fixed relative to the electronic unit; andthe electrical raft and the electronic unit are in electrical connection through the first and second electrical connectors.3. A gas turbine engine according to claim 1 , wherein the electronic unit is mechanically fixed to another component of the gas turbine engine.4. A gas turbine engine according to claim 3 , wherein the electronic unit and the electrical raft are mechanically fixed to different components of the gas turbine engine.5. A gas turbine engine according to claim ...

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Номер записи: 80

27-06-2013 дата публикации

Gas turbine engine part

Номер: US20130160462A1

Автор: Gary Alan Skinner, Paul Broughton, Richard Peace, Robin Charles Kennea

Принадлежит: Rolls Royce PLC

The present invention provides a gas turbine engine part which has a primary purpose in the engine which is structural and/or aerodynamic. The part is formed of rigid composite material, and has an electrical system comprising electrical conductors permanently embedded in the composite material. This provides advantages in terms of weight, complexity, and build time.

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Номер записи: 81

27-06-2013 дата публикации

ANTI-VIBRATION MOUNT

Номер: US20130160464A1

Автор: BROUGHTON Paul, KENNEA Robin Charles, MASZCZK Dariusz Robert, PEACE Richard, SKINNER Gary Alan

Принадлежит: ROLLS-ROYCE PLC

An anti-vibration mount is provided for mounting a first component to a second component. The mount has an elastomeric body which provides a recess into which the first component is received. The mount further has pair of brackets which fit to opposing sides of the elastomeric body sandwiching the first component received in the recess therebetween. At least one of the brackets is arranged to connect the anti-vibration mount and second component together. The mount further has a clamping arrangement which applies clamping pressure across the brackets and thereby compresses the elastomeric body to secure the first component in the recess. 1. An anti-vibration mount for mounting a first component to a second component , the mount having:an elastomeric body which provides a recess into which the first component is received;a pair of brackets which fit to opposing sides of the elastomeric body sandwiching the first component received in the recess therebetween, at least one of the brackets being arranged to connect the anti-vibration mount and second component together; anda clamping arrangement which applies clamping pressure across the brackets and thereby compresses the elastomeric body to secure the first component in the recess.2. An anti-vibration mount according to claim 1 , wherein the elastomeric body is in two parts which are separable from each other when the clamping pressure is removed claim 1 , the first part providing one of the opposing sides of the elastomeric body and one side of the recess and the second part providing the other opposing side of the elastomeric body and an opposing side of the recess.3. An anti-vibration mount according to claim 2 , wherein the first component has a through-hole and the first part has a projection which extends through the through-hole and is received in a matching cavity formed in the second part.4. An anti-vibration mount according to claim 1 , wherein the first component is planar and the recess is a slot.5. An ...

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Номер записи: 82

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: 83

27-06-2013 дата публикации

HINGING CRADLE FOR FAN COWLS SUPPORTED BY SAID COWLS IN CLOSED POSITION

Номер: US20130161446A1

Автор: Letay Benoit, Toro Andrés, Venet Adrien

Принадлежит: AIRBUS OPERATIONS (S.A.S)

The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure. 1. Engine assembly for aircraft comprising an engine , a coupling device of the engine as well as a nacelle surrounding the engine and provided with fan cowls as well as an air intake , said coupling device comprising a rigid structure as well as a fore aerodynamic structure , the latter having a cradle equipped with an aerodynamic cowling , said cradle being hinge mounted at its fore end on an entity comprising a fan housing of said engine as well as the air intake , and said fan cowls being mounted to move on said cradle so as to be able to occupy an open position and a closed position in which they are supported at the fore by said entity and at the aft by a thrust reverser system ,characterised in that the assembly is designed such that when the fan cowls are in open position, said cradle adopts a first configuration in which its aft end is retained by a span of the engine mounting structure, and such that when the fan cowls are in closed position, said cradle, borne by the fan cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure.2. Engine assembly ...

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Номер записи: 84

27-06-2013 дата публикации

System and method for production of fischer-tropsch synthesis products and power

Номер: US20130165534A1

Автор: Benjamin H. CARRYER, Bruce E. McComish, Bryan C. Borum, Eric R. ELROD, Harold A. Wright, Mark D. Ibsen, Mark K. Robertson, Sim Weeks, Weibin Jiang

Принадлежит: Rentech Inc

A method for generation of power and Fischer-Tropsch synthesis products by producing synthesis gas comprising hydrogen and carbon monoxide, producing Fischer-Tropsch synthesis products and Fischer-Tropsch tailgas from a first portion of the synthesis gas, and generating power from a second portion of the synthesis gas, from at least a portion of the Fischer-Tropsch tailgas, or from both. The method may also comprise conditioning at least a portion of the synthesis gas and/or upgrading at least a portion of the Fischer-Tropsch synthesis products. A system for carrying out the method is also provided.

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Номер записи: 85

04-07-2013 дата публикации

Apparatus for mixing fuel and air in a combustion system

Номер: US20130167538A1

Автор: Colore Elizabeth R., Laster Walter R., Little David A.

Принадлежит:

A fuel shroud assembly () into which fuel () is injected for mixing with an air stream () in a fuel manifold. The shroud assembly () comprises a plurality of parallel fuel scoops () each receiving the injected fuel (). The fuel stream () flows through each scoop (), exiting at an open scoop end (A). The air stream () flows between scoops, creating a shear region proximate each scoop end (A) where the fuel exits. The shear causes mixing of the air () and the fuel () streams, wherein the degree of mixing is not dependent on the momentum ratio of the air () or fuel () streams. 1. A fuel delivery apparatus for use within a fuel manifold of a gas turbine , the apparatus comprising:laterally spaced apart fuel scoops, each fuel scoop having a rectangular cross section with the fuel scoops arranged in a parrallel configuration, and each defining a plurality of first openings on an external surface thereof for receiving fuel, each one of the fuel scoops directing fuel flow therethrough and the fuel exiting each fuel scoop at a second opening;adjacent ones of the fuel scoops defining an open channel therebetween, wherein an air stream flows only through the channel in a direction toward the second openings; andwherein the air stream creates a shear region proximate the second openings, and wherein the air stream and the fuel stream mix in the shear region.2. The fuel delivery apparatus of wherein the second opening of each one of the fuel scoops is defined by a straight edge.3. The fuel delivery apparatus of wherein the second opening of each one of the fuel scoops is defined by an arcuate edge.4. (canceled)5. (canceled)6. The fuel delivery apparatus of wherein each of the fuel scoops extends between an upper surface and a lower surface of the fuel manifold.7. The fuel delivery apparatus of wherein each of the fuel scoops extends about ⅔ of a distance between an upper surface and a lower surface of the fuel manifold.8. A manifold for mixing fuel and air claim 1 , the manifold ...

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Номер записи: 86

04-07-2013 дата публикации

HYPERSTATIC TRUSS COMPRISING CONNECTING RODS

Номер: US20130167553A1

Автор: BELLABAL François Robert, Vincent Thomas Alain Christian

Принадлежит: SNECMA

A hyperstatic truss including connecting rods, used for suspension of a first ring, forming part of an engine case, inside a second ring concentric to the first ring, the connecting rods being secured at one end to the first ring and at the other end to the second ring. The tensile stiffness of the connecting rods is greater than the compressive stiffness thereof. The truss for example can be used for suspension of a ducted-fan turbine engine with an elongate bypass duct. 110-. (canceled)11. A hyperstatic truss comprising:connecting rods applied to suspending a first ring, that forms part of an engine casing, inside a second ring concentric with the first ring, the connecting rods being secured by one end to the first ring and by an other end to the second ring,wherein the connecting rods have a tensile strength that is higher than their compressive strengths, and comprise one or more parts configured to transmit compressive and tensile loads between the ends and one or more other parts configured to transmit only the tensile loads between the ends.12. The truss as claimed in claim 11 , wherein the connecting rods comprise an internal rod and a shroud surrounding the internal rod claim 11 , the internal rod configured to work in compression and in tension claim 11 , the shroud working only in tension.13. The truss as claimed in claim 12 , wherein the internal rod and the shroud of the connecting rods include a pair of surfaces bearing against one another when tension is applied to the internal rod claim 12 , the tensile loads then being transmitted between the two ends by the internal rod and the shroud.14. The truss as claimed in claim 13 , wherein the connecting rods comprise at least two pairs of bearing surfaces distributed along the axis of the rod.15. The truss as claimed in claim 12 , wherein the connecting rods include means for bearing radially against an internal surface of the shroud claim 12 , to prevent the internal rod from buckling when subjected to ...

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Номер записи: 87

04-07-2013 дата публикации

Mounting device and method of assembling the same

Номер: US20130168129A1

Автор: Adam Benjamin Cox, Bruce D. Markert, William Ward Owens

Принадлежит: Unison Industries LLC

A method of assembling a mounting device for an electrical harness of a gas turbine engine is provided. The electrical harness has a wire bundle. The method includes providing a first shell and providing a second shell. The method further includes coupling the first shell to the second shell with the wire bundle disposed between the first shell and the second shell such that movement of the first shell and the second shell along the wire bundle is restricted.

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Номер записи: 88

04-07-2013 дата публикации

Methods and systems for turbine line replaceable unit fault detection and isolation during engine startup

Номер: US20130173135A1

Автор: Kyusung Kim

Принадлежит: Honeywell International Inc

Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule. The values at these key events are used for comparing at the anomaly detector.

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Номер записи: 89

11-07-2013 дата публикации

SYSTEM FOR INJECTING FUEL IN A GAS TURBINE ENGINE

Номер: US20130174558A1

Автор: Stryapunin Sergey Aleksandrovich

Принадлежит: GENERAL ELECTRIC COMPANY

Embodiments of the present disclosure provide a turbine combustor having a primary fuel injection system, a first wall portion disposed about a primary combustion zone downstream from the primary fuel injection system, and a second wall portion disposed downstream from the first wall portion. The turbine combustor also has a secondary fuel injection system disposed between the first wall portion and the second wall portion, where the secondary fuel injection system is removable form the first and second wall portions. 1. A system , comprising: a primary fuel injection system;', 'a first wall portion disposed about a primary combustion zone downstream from the primary fuel injection system;', 'a second wall portion disposed downstream from the first wall portion; and', 'a secondary fuel injection system disposed between the first wall portion and the second wall portion, wherein the secondary fuel injection system is removable from the first and second wall portions., 'a turbine combustor, comprising2. The system of claim 1 , wherein the first wall portion comprises a liner and the second wall portion comprises a transition piece.3. The system of claim 2 , wherein the first wall portion comprises a sleeve or case disposed about the liner claim 2 , and the second wall portion comprises an impingement sleeve disposed about the transition piece.4. The system of claim 1 , comprising a first seal disposed between the first wall portion and the secondary fuel injection system claim 1 , wherein the first seal is configured to enable movement of the first wall portion relative to the secondary fuel injection system.5. The system of claim 1 , comprising a second seal disposed between the second wall portion and the secondary fuel injection system claim 1 , wherein the second seal is configured to enable movement of the second wall portion relative to the secondary fuel injection system.6. The system of claim 1 , wherein the secondary fuel injection system comprises a ...

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Номер записи: 90

11-07-2013 дата публикации

Method for cooling a thermal protection floor of an aft aerodynamic fairing of a structure for mounting an aircraft propulsion system

Номер: US20130174572A1

Автор: Emmanuelle Dumont, Fabien Raison

Принадлежит: AIRBUS OPERATIONS SAS

A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle.

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Номер записи: 91

11-07-2013 дата публикации

GAS TURBINE ENGINE BEARING CHAMBER SEALS

Номер: US20130174574A1

Автор: CLARK Lee Alan, HEATON Peter Ellison

Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine sealing air supply system comprising a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air. An air supply duct is coupled to the bearing chamber seal to provide the sealing air. A first duct is coupled between a starter air system of the gas turbine engine and the air supply duct to supply sealing air during gas turbine engine starting. 1. A gas turbine engine sealing air supply system comprising:a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air;an air supply duct coupled to the bearing chamber seal to provide the sealing air;a starter air system of the gas turbine engine; anda first duct coupled between the starter air system and the air supply duct to supply the sealing air during gas turbine engine starting.2. A sealing air supply system as claimed in further comprising a second air source and a second duct coupled between the second air source and the air supply duct to supply the sealing air during other periods of gas turbine engine operation.3. A sealing air supply system as claimed in wherein the second air source comprises a compressor bleed of the gas turbine engine and the second duct comprises a bleed duct.4. A sealing air supply system as claimed in further comprising a switching mechanism to switch the supply of sealing air between the starter air system and the second air source.5. A sealing air supply system as claimed in further comprising a control system arranged to control the switching mechanism.6. A sealing air supply system as claimed in wherein the control system is arranged to switch between the starter air system and the second air source dependent on the air pressure of the starter air system.7. A sealing air supply system as claimed in wherein the control system is arranged to switch between the starter air system and the second air source dependent on the air pressure of the ...

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Номер записи: 92

11-07-2013 дата публикации

TURBOMACHINE COMPONENT ALIGNMENT

Номер: US20130174576A1

Автор: Leconte Patrice, Lucas George M., Maier William C.

Принадлежит: DRESSER-RAND COMPANY

A rotating machine has a barrel casing and at least one component carrier disposed therein. The component carrier is aligned and supported within the barrel casing using a plurality of carrier alignment fixtures which have alignment shafts that extend through the barrel casing to the component carrier. Each alignment shaft has an eccentric key pin extending from a distal end thereof and an alignment key rotatably-mounted to each eccentric key pin. The alignment keys mate with corresponding keyway slots defined on the component carrier such that when the carrier alignment fixtures are rotated axially, the corresponding alignment keys bias against the keyway slot and shift the position of the component carrier. 1. A rotating machine , comprising:a barrel casing having a plurality of cylindrical bores extending between outer and inner circumferential surfaces of the barrel casing;a component carrier disposed within the barrel casing and defining a plurality of keyway slots;a plurality of carrier alignment fixtures arranged about the outer circumferential surface of the barrel casing, each carrier alignment fixture having an alignment shaft extending through a corresponding one of the plurality of cylindrical bores and having an eccentric key pin extending from a distal end of each alignment shaft; andan alignment key rotatably-mounted to each eccentric key pin of each corresponding carrier alignment fixture and configured to mate with a corresponding one of the plurality of keyway slots, whereby rotation of each carrier alignment fixture about a central axis of each corresponding alignment shaft adjusts a position of the component carrier with respect to the barrel casing.2. The rotating machine of claim 1 , wherein the barrel casing is unsplit and cylindrical.3. The rotating machine of claim 1 , further comprising a fluid expander component mounted within the component carrier.4. The rotating machine of claim 1 , further comprising a shaft arranged for rotation within ...

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Номер записи: 93

11-07-2013 дата публикации

GAS TURBINE ENGINE BEARING CHAMBER SEALS

Номер: US20130177406A1

Автор: BOLGAR Crispin David, HEATON Peter Ellison

Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine sealing air system including a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air. The system includes an air vent duct coupled to the bearing chamber seal. An ejector is located within the air vent duct to pump sealing air from the bearing chamber seal and through the air vent duct. A first duct is coupled between a starter air system of the gas turbine engine and the ejector to provide motive fluid to the ejector during gas turbine engine starting. 1. A gas turbine engine sealing air system comprising:a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air;an air vent duct coupled to the bearing chamber seal;a starter air system of the gas turbine engine;an ejector located within the air vent duct to pump sealing air from the bearing chamber seal and through the air vent duct; anda first duct coupled between the starter air system and the ejector to provide motive fluid to the ejector during gas turbine engine starting.2. A sealing air system as claimed in further comprising a second air source and a second duct coupled between the second air source and the ejector to provide the motive fluid during other periods of gas turbine engine operation.3. A sealing air system as claimed in wherein the second air source comprises a compressor bleed of the gas turbine engine and the second duct comprises a bleed duct.4. A sealing air system as claimed in wherein the ejector is configured as a restriction of the air vent duct.5. A sealing air system as claimed in further comprising a restriction of the air vent duct.6. A sealing air system as claimed in further comprising an air/oil separator located in the air vent duct.7. A sealing air system as claimed in wherein the air/oil separator is located between the bearing chamber seal and the ejector.8. A sealing air system as claimed in further comprising a switching ...

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Номер записи: 94

18-07-2013 дата публикации

Fastening element and de-icing device of an aircraft gas-turbine engine

Номер: US20130180227A1

Автор: ARAUJO Gustavo, Todorovic Predrag

Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

The present invention relates to a fastening element, in particular to its use in a de-icing device of an aircraft gas-turbine engine, for connecting two components, with the fastening element ensuring a connection of the components with a predetermined relative movability to each other, with the fastening element including two struts arranged at an angle to each other, where two first end areas, spacedly arranged to each other, can be fastened to one of the components, and the two other second end areas can be connected to each other and fastened to the other component. 1. Fastening element for connecting two components , with the fastening element ensuring a connection of the components with a predetermined relative movability to each other , with the fastening element including two struts arranged at an angle to each other , where two first end areas , spacedly arranged to each other , can be fastened to one of the components , and the two other second end areas can be connected to each other and fastened to the other component.2. Fastening element in accordance with claim 1 , characterized in that the struts are elastically bendable and/or are provided in the form of flat sheet-metal strips.3. Fastening element in accordance with claim 1 , characterized in that the second end areas can connect the other component by means of a carrier element claim 1 , attached to the second end areas and to the other component.4. De-icing device of an aircraft gas-turbine engine with an engine cowling enclosing at least one inflow region claim 1 , with the engine cowling having a double-walled design and including at least one annular tube element extending in the circumferential direction and being provided with outlet openings for passing hot air to an inflow region claim 1 , in order to de-ice it claim 1 , with the tube element in the circumferential direction being mounted on the engine cowling by several fastening elements in accordance .5. De-icing device in accordance ...

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Номер записи: 95

18-07-2013 дата публикации

SYSTEM FOR INJECTING A FLUID, COMPRESSOR AND TURBOMACHINE

Номер: US20130180249A1

Автор: HILLER SVEN

Принадлежит: MTU AERO ENGINES GMBH

A system for injecting a fluid into a wall boundary layer of a flow in a turbomachine is disclosed. The system has a plurality of nozzles which are disposed in a side wall limiting the flow and are oriented diagonally in the direction of flow. The nozzles each have a rectangular, flat nozzle cross-section. A compressor having such a system, as well as a turbomachine having such a compressor, are also disclosed. 1. A system for injecting a fluid in a wall boundary layer of a flow in a turbomachine , comprising:a nozzle, wherein the nozzle is disposed in a side wall of the turbomachine, wherein the side wall limits the flow, wherein the nozzle is oriented diagonally with respect to a direction of flow in the turbomachine, and wherein the nozzle has a rectangular, flat nozzle cross-section.2. The system according to claim 1 , further comprising an injection channel disposed upstream from the nozzle in the direction of flow claim 1 , wherein the injection channel has a constriction that forms a boundary surface.3. The system according to claim 2 , wherein the boundary surface defines the nozzle cross-section.4. The system according to claim 2 , wherein the injection channel has an expanded funnel-shape upstream from the constriction in the direction of flow.5. The system according to claim 1 , wherein the nozzle is flat in the direction of flow.6. The system according to claim 1 , wherein the nozzle is disposed at an angle of ≦40° with respect to the direction of flow.7. The system according to claim 1 , wherein an outlet area of the nozzle is oriented tangentially to a direction of rotation of the turbomachine.8. The system according to claim 1 , wherein an outlet area of the nozzle is disposed ±20° from the direction of rotation of the turbomachine.9. A compressor having a system according to .10. The compressor according to claim 9 , wherein the nozzle is disposed on a stator side in a trailing edge region of at least one blade row formed of rotor blades.11. A ...

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Номер записи: 96

18-07-2013 дата публикации

FUEL SUPPLY APPARATUS, FUEL-FLOW-RATE-CONTROL APPARATUS, AND GAS-TURBINE POWER PLANT

Номер: US20130180250A1

Автор: Harada Shoichi

Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A fuel supply apparatus is provided with a plurality of flow-rate regulating valves that regulate the flow rate of fuel flowing in a fuel supply line; a calculating section that calculates a required flow-rate coefficient on the basis of at least a fuel pressure in the fuel flow upstream of the flow-rate regulating valves, a pressure determined in advance as a fuel pressure downstream of the flow-rate regulating valves, and the flow rate of fuel to be supplied to one fuel nozzle among different kinds of fuel nozzles, the required flow-rate coefficient being the coefficient of the flow-rate regulating valve corresponding to the one fuel nozzle; and a valve control section that controls the degree-of-opening of the flow-rate regulating valve corresponding to the one fuel nozzle on the basis of the required flow-rate coefficient. 1. A fuel supply apparatus configured to control the flow rates of fuel to be supplied to fuel nozzles provided in a combustor of a gas turbine , the apparatus comprising:a plurality of flow-rate regulating valves which are provided in fuel supply lines that supply fuel to the fuel nozzles and which regulate the flow rates of fuel flowing through the fuel supply lines;a calculating section that calculates required flow-rate coefficients of the flow-rate regulating valves corresponding to the fuel nozzles on the basis of at least a fuel pressure in the fuel flow upstream of the flow-rate regulating valves, a pressure determined in advance as a fuel pressure downstream of the flow-rate regulating valves, and the flow rates of fuel to be supplied to the fuel nozzles; anda valve control section that controls the degrees-of-opening of the flow-rate regulating valves on the basis of the required flow-rate coefficients.2. The fuel supply apparatus according to claim 1 , further comprising:a pressure measuring unit that measures a fuel pressure upstream of the flow-rate regulating valves,wherein the pressure measured by the pressure measuring unit is ...

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Номер записи: 97

18-07-2013 дата публикации

SPRING LOADED SEAL ASSEMBLY FOR TURBINES

Номер: US20130181413A1

Автор: Demiroglu Mehmet, McMahan Kevin Weston, Repikov Timur Rustamovich

Принадлежит: GENERAL ELECTRIC COMPANY

A spring loaded seal assembly is disclosed for sealing a gap between adjacent turbine components. The seal assembly may generally include a turbine seal and a spring member. The turbine seal may extend between the adjacent turbine components and may be configured to seal the gap defined between the turbine components. The spring member may be configured to engage the turbine seal so as to maintain the seal in sealing engagement with the adjacent turbine components. 1. A spring loaded seal assembly for sealing a fluid leakage gap between adjacent turbine components , the spring loaded seal assembly comprising:a turbine seal extending between aligned seal grooves defined in adjacent stationary turbine components, said turbine seal configured to seal a fluid leakage gap defined between said turbine components; andat least one spring member configured to maintain said turbine seal in sealing engagement with said turbine components, said at least one spring member extending between said aligned seal grooves and being attached to said turbine seal.2. The spring loaded seal assembly of claim 1 , wherein said at least one spring member is biased against a forward surface of said aligned seal grooves.3. The spring loaded seal assembly of claim 1 , wherein said at least one spring member is bowed along its length.4. The spring loaded seal assembly of claim 3 , wherein said at least one spring member is attached to a side of said turbine seal such that said at least one spring member is bowed concavely with respect to said side.5. The spring loaded seal assembly of claim 3 , wherein said at least one spring member is attached to a side of said turbine seal such that said at least one spring member is bowed convexly with respect to said side.6. The spring loaded seal assembly of claim 1 , wherein said at least one spring member comprises a horizontal segment attached to said turbine seal and first and second arms extending from said horizontal segment claim 1 , said first and ...

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Номер записи: 98

18-07-2013 дата публикации

SEALING DEVICE HAVING A SLEEVE FOR THE PASSAGE OF A CONNECTING ROD OF A SYSTEM FOR CONTROLLING THE ORIENTATION OF THE BLOWER BLADES OF A TURBOPROP ENGINE THROUGH A PARTITION

Номер: US20130183143A1

Автор: Gallet Francois

Принадлежит: SNEMCA

A sealing device for passing a connecting rod of a system for controlling a pitch of fan blades of a turboprop through a partition. The device includes a tube for fastening to the partition that is to be sealed, and a frustoconical sheath through which the connecting rod is to pass, the sheath configured to slide axially inside the tube and including, at its wider end, a sealing mechanism co-operating with the tube, and, at its narrower end, a leaktight fastener fastening to a corresponding end of the connecting rod. 15-. (canceled)6. A sealing device for passing a connecting rod of a system for controlling pitch of fan blades of a turboprop through a partition , comprising:a tube for fastening to the partition that is to be sealed; anda frustoconical sheath through which the connecting rod is to pass,the sheath configured to slide axially inside the tube and including, at its wider end, sealing means co-operating with the tube, and, at its narrower end, leaktight fastener means for fastening to a corresponding end of the connecting rod.7. A device according to claim 6 , wherein the wider end of the sheath further includes a gasket at its periphery co-operating with an inside of the tube to provide sealing between the sheath and the tube.8. A device according to claim 6 , wherein the narrower end of the sheath is closed and pivotally mounted about a pivot pin of the corresponding end of the connecting rod to fasten the sheath to the connecting rod in a sealed manner.9. A system for controlling pitch of fan blades of a turboprop comprising:at least one set of adjustable-pitch fan blades, the set being constrained to rotate with a rotary ring mechanically connected to a rotary casing, each blade of the set being coupled for adjusting its pitch to a blade root support pivotally mounted on the rotary ring by a bevel gearing including a first toothed wheel secured to the blade root support and centered on an axis that is radial relative to the rotary ring, and a second ...

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Номер записи: 99

25-07-2013 дата публикации

METHOD FOR MONITORING A FUEL CIRCUIT SHUT-OFF VALVE

Номер: US20130186096A1

Автор: ANDRE Brice, Ayrault Virginie, GAULLY Bruno Robert

Принадлежит: SNECMA

The invention relates to a method for monitoring the operation of a fuel circuit shut-off valve comprising an LPSOV, a flow regulator, the shut-off valve, characterised in that it comprises: 1. A method for monitoring the operation of a shut-off valve of an aircraft turbine engine fuel circuit , the circuit comprising , from upstream to downstream in the direction of fuel circulation , a low-pressure pump , a Low Pressure Shut-Off Valve (LPSOV) , a high-pressure pump , said shut-off valve and a device for measuring the fuel flow rate in the circuit ,wherein a LPSOV closing time is greater than a closing time of said shut-off valve,wherein the method comprises:a step for ordering closure of valves in the fuel circuit;a step for measuring fuel flow rate in the fuel circuit carried out before the LPSOV is completely closed; anda diagnostic step including determining that said shut-off valve is defective if the fuel flow rate measured is not equal to zero and determining that said shut-off valve is operating correctly if the fuel flow rate measured is zero.2. The monitoring method according to claim 1 , wherein the fuel circuit comprises a metering valve arranged between the LPSOV and said shut-off valve claim 1 , wherein the closing rate is greater than the closing rate of the LPSOV claim 1 ,further comprising a step of ordering opening of the metering valve carried out after the step for ordering the closure of the valves and before the step for measuring the fuel flow rate.3. The monitoring method according claim 2 , wherein claim 2 , if claim 2 , following the diagnostic step claim 2 , said shut-off valve is determined to be defective claim 2 , the diagnostic step is followed by a step for ordering closure of the metering valve.4. The monitoring method according to claim 2 , wherein the step for ordering the opening of the metering valve includes ordering the opening of the metering valve so as to enable the flow of a predetermined fuel flow rate.5. The monitoring ...

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Номер записи: 100