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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

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

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 7622. Отображено 100.
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: 1
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: 2
09-02-2012 дата публикации

Thermal control system for fault detection and mitigation within a power generation system

Номер: US20120031581A1
Автор: Adil Ansari, Eric J. Kauffman, Julio E. Mestroni, Rahul Jaikaran Chillar
Принадлежит: General Electric Co

A system includes a radiation sensor configured to direct a field of view toward at least one conduit along a fluid flow path into a heat exchanger. The radiation sensor is configured to output a signal indicative of a temperature of the at least one conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, to compare the temperature to a threshold range, and to adjust a fluid flow through the fluid flow path or the at least one conduit if the temperature deviates from the threshold range.

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Номер записи: 3
16-02-2012 дата публикации

Method for compensating for combustion efficiency in fuel control system

Номер: US20120036861A1
Автор: Michael John Hughes, William Forrester Seely
Принадлежит: General Electric Co

Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency differences between the starting and ending operating mode that otherwise can lead to severe swings in combustion reference temperature and lean blowout.

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Номер записи: 4
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: 5
19-04-2012 дата публикации

Method of operating an electronic engine control (eec) to compensate for speed changes

Номер: US20120090330A1
Автор: David L. Chapski
Принадлежит: Hamilton Sundstrand Corp

A method of operating an electronic engine control to compensate for speed changes. The method includes receiving a fuel flow request, sensing actual engine rotor speed, calculating a fuel flow correction factor, establishing a final fuel flow request based on the fuel flow correction factor, and adjusting the actual set point of the MV to compensate for the actual engine rotor speed.

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Номер записи: 6
19-04-2012 дата публикации

Distributed small engine fadec

Номер: US20120095661A1
Автор: Kevin P. Roy, Thaddeus J. Zebrowski
Принадлежит: Hamilton Sundstrand Corp

A full authority digital engine controller (FADEC) controls an engine attached to an airframe. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital data bus electrically connecting the ADC to the EEC. The ADC is electrically connected to a plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data. The digital bus conducts the airframe sensor digital data to the EEC.

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Номер записи: 7
24-05-2012 дата публикации

Variable area fan nozzle fan flutter management system

Номер: US20120124965A1
Автор: Ray W. Carmichael, Robert J. Morris, Zbigniew M. Grabowski
Принадлежит: Individual

A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.

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Номер записи: 8
14-06-2012 дата публикации

Gas turbine engine control using acoustic pyrometry

Номер: US20120150413A1
Автор: Richard H. Bunce, Upul P. Desilva
Принадлежит: Individual

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

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Номер записи: 9
05-07-2012 дата публикации

Method of controlling a combined-cycle system in single-shaft configuration, and combined-cycle system in single-shaft configuration

Номер: US20120167581A1
Автор: Marco Alecci, Paolo Pesce
Принадлежит: Ansaldo Energia SpA

A combined-cycle system includes a compressor, a gas turbine, a steam turbine, and an electric generator, which are coupled to the same shaft. A method of controlling the system envisages detecting a current compression ratio of the compressor, calculating a normalized compression ratio on the basis of the current compression ratio, and determining a load condition of the gas turbine on the basis of the normalized compression ratio. Moreover, a setpoint is selected, for at least one operating quantity of the gas turbine, and regulating signals are applied to actuators of the gas turbine so that the operating quantity of the gas turbine tends to reach the setpoint.

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Номер записи: 10
01-11-2012 дата публикации

Automated tuning of gas turbine combustion systems

Номер: US20120275899A1
Автор: Christopher Chandler
Принадлежит: Gas Turbine Efficiency Sweden AB

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

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Номер записи: 11
06-12-2012 дата публикации

Engine for thrust or shaft output and corresponding operating method

Номер: US20120304619A1
Автор: Michael Alan Beachy Head
Принадлежит: Individual

An engine and a method of operating the engine are provided. The engine includes a gas turbine and fan that rotate together to provide an exhaust gas flow stream, which flows over a free turbine that is connected to a power take-off. The free turbine can extract energy from the exhaust gas flow stream and transfer it as shaft power to the power take-off and the amount of energy extracted by the free turbine is controlled by varying the pitch of the free turbine's blades and/or by varying the pitch or stator vanes of a stator upstream of the free turbine. The control over the amount of energy extracted by the free turbine allows the engine to be used to provide thrust from the gas turbine and fan or to provide shaft power at the power take-off, or a combination of thrust and shaft power.

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Номер записи: 12
10-01-2013 дата публикации

Method of controlling speed transients in a turbine engine

Номер: US20130008171A1
Автор: Cedrik Djelassi
Принадлежит: SNECMA SAS

A method of controlling an engine in which a fuel flow setpoint is determined, the method comprising: a step of implementing a steady speed regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a setpoint parameter that depends on the position of a control lever and an operating parameter of the engine; wherein the method comprises: a detection step of detecting an intended speed transient; and in response to said detection step, a step of implementing a speed transient regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a speed of the engine and a speed setpoint varying over time with the speed trajectory as generated in predetermined manner.

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Номер записи: 13
07-03-2013 дата публикации

Limit stop device and charging unit

Номер: US20130056325A1
Автор: Volkhard Ammon
Принадлежит: Bosch Mahle Turbo Systems GmbH and Co KG

A limit stop device for limiting an adjustment path of a mobile component relative to a stationary component may include a sleeve body configured to be inserted into an opening formed in the stationary component. The sleeve body may include a retaining segment disposed in the interior of the opening. A core body may be disposed in the interior of the sleeve body and be configured to radially brace the retaining segment against an inner wall of the stationary component thereby axially fixing the sleeve body on the stationary component. A stop surface may protrude into the adjustment path of the mobile component and be configured to limit the adjustment path of the mobile component.

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Номер записи: 14
11-04-2013 дата публикации

METHOD FOR SWITCHING OVER A COMBUSTION DEVICE

Номер: US20130086918A1
Автор: BOTHIEN Mirko Ruben, PENNELL Douglas Anthony, ZAJADATZ Martin
Принадлежит: ALSTOM Technology Ltd

An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames. 1. A method for switching over a combustion device from operation with a first premix fuel to a second premix fuel comprising:reducing and stopping a first premix fuel supply;operating the combustion device with at least one pilot fuel that generates diffusion flames; andstarting a second premix fuel supply following generation of the diffusion flames.2. The method according to claim 1 , wherein the pilot fuels include first and second pilot fuels claim 1 , which are fed to the combustion device during operation of the combustion device.3. The method according to claim 2 , wherein in an intermediate phase claim 2 , after the first premix fuel supply stops and before the second premix fuel supply starts claim 2 , the combustion device is operated with the at least one pilot fuel generating only diffusion flames.4. The method according to claim 3 , wherein only the first and second pilot fuels support combustion device operation during the intermediate phase.5. The method according to claim 2 , comprising:injecting the first and the second pilot fuels together with the first premix fuel and the second premix fuels.6. The method according to claim 3 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.7. The method according to claim 5 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.8. The method according to claim 3 , comprising:terminating the first pilot fuel supply before the second pilot fuel supply terminates.9. The method according to claim 5 , ...

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Номер записи: 15
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: 16
18-04-2013 дата публикации

Fuel System

Номер: US20130091857A1
Автор: Qin Yong, Thornton Paul Robert
Принадлежит: ROLLS-ROYCE GOODRICH ENGINE CONTROL SYSTEMS LTD.

A fuel system comprises a fuel actuation arrangement operable to split a metered flow of fuel into at least a first stream and a second stream, a control unit controlling the operation of the fuel actuation arrangement and wherein the control unit controls the operation of the fuel actuation arrangement in response to the output of a temperature sensor sensitive to a gas temperature downstream of the high pressure compressor of an associated engine and the output of a gas sensor sensitive to at least one parameter of the composition of a gas downstream of a combustor of the engine. 1. A fuel system comprising a fuel actuation arrangement operable to split a metered flow of fuel into at least a first stream and a second stream , a control unit controlling the operation of the fuel actuation arrangement , and wherein the control unit controls the operation of the fuel actuation arrangement in response to the output of a temperature sensor sensitive to a gas temperature downstream of the high pressure compressor of an associated engine and the output of a gas sensor sensitive to at least one parameter of the composition of a gas downstream of a combustor of the engine.2. A system according to claim 1 , wherein the temperature sensor is sensitive to the temperature at the exit of the high pressure compressor.3. A system according to claim 1 , wherein the parameter to which the gas sensor is sensitive is the oxygen claim 1 , carbon dioxide and/or carbon monoxide content of the gas downstream of the combustor.4. A system according to claim 1 , wherein the gas sensor is located adjacent the exit of the low pressure turbine stage.5. A system according to claim 4 , wherein the gas sensor is located at the gas path of the low pressure turbine outlet guide vane or its exit.6. A system according to claim 1 , wherein the gas sensor is of the laser-detector type.7. A system according to claim 6 , wherein the gas sensor comprises a probe located in the engine claim 6 , and an ...

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Номер записи: 17
25-04-2013 дата публикации

DETECTION OF THE OVERSPEED OF A FREE TURBINE BY MEASURING USING A TORQUE METER

Номер: US20130098042A1
Автор: FREALLE Jean-Luc Charles Gilbert, Perbos Alain Michel
Принадлежит: TURBOMECA

An overspeed protection device includes at least one torque measurement unit supported by an output shaft coupled mechanically to a free turbine of a turbine engine and a signal processing unit able to transmit to a turbine engine regulating system a command to reduce a flow of fuel injected if it is detected that the torque has dropped below a first datum value. The signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger the reduction being taken during a rotation corresponding to a fraction of a revolution of the output shaft. 114-. (canceled)15. An overspeed protection device for a free turbine of a turbine engine comprising a gas generator comprising at least one compressor , a combustion chamber , at least one coupled turbine and a system for regulating the amount of fuel injected into said combustion chamber , the gases from said generator being directed onto said free turbine , said device comprising:at least one torque measurement means supported by an output shaft coupled mechanically to said free turbine; anda signal processing unit able to transmit to the turbine engine regulating system a command to reduce the flow of fuel injected if it is detected that the torque has dropped below a first datum value,wherein the signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger said reduction being taken during a rotation corresponding to a fraction of a revolution of said output shaft.16. The protection device as claimed in claim 15 , in which the measurement means is a phonic wheels torque meter claim 15 , the fraction of a revolution being defined by the sector comprised between two consecutive teeth of one of the two said phonic wheels.17. The protection device as claimed in claim 15 , in which said torque ...

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Номер записи: 18
25-04-2013 дата публикации

Method for Operating a Gas Turbine

Номер: US20130098054A1
Автор: Guethe Felix, Gumprecht-Liebau Meike, STANKOVIC Dragan
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for operating a gas turbine (), a CO2-containing gas is compressed in a compressor (), the compressed gas is used to burn a fuel in at least one subsequent combustion chamber (), and the hot combustion gases are used to drive at least one turbine (). Improved control and performance can be achieved by measuring the species concentration of the gas mixture flowing through the gas turbine () at several points within the gas turbine () by a distributed plurality of species concentration sensors (-), and utilizing the measured concentration values to control the gas turbine () and/or optimize the combustion performance of the gas turbine (). 1. A method for operating a gas turbine , in which turbine a CO-containing gas is compressed in a compressor , the compressed gas is used to burn a fuel in at least one subsequent combustion chamber to form hot combustion gases , and the hot combustion gases are used to drive at least one turbine , the method comprising:measuring the species concentration of the gas mixture flowing through the gas turbine at several points within the gas turbine with a distributed plurality of species concentration sensors; andcontrolling the gas turbine, optimizing the combustion performance of said gas turbine, or both, based on the measured species concentration values.2. A method according to claim 1 , wherein measuring comprises:{'sub': '2', 'measuring at least the Oconcentration with said plurality of species concentration sensors.'}3. A method according to claim 1 , wherein said species concentration sensors comprise ZrOsensors.4. A method according to claim 1 , wherein said species concentration sensors consist of ZrOsensors.5. A method according to claim 1 , in which the gas turbine is a sequential-combustion turbine with two combustors claim 1 , two turbines claim 1 , and flue gas recirculation claim 1 , and in which at least part of the flue gas at an exit of the gas turbine is recirculated and enters the compressor after ...

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Номер записи: 19
25-04-2013 дата публикации

VARIABLE VANE ASSEMBLY FOR A GAS TURBINE ENGINE HAVING AN INCREMENTALLY ROTATABLE BUSHING

Номер: US20130101385A1
Автор: Schilling Jan Christopher
Принадлежит:

A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions. 1. A variable vane assembly for a gas turbine engine including a casing , said variable vane assembly comprising:(a) a variable vane including a platform and a vane stem extending outwardly from said platform;(b) a bushing surrounding said vane stem;(c) a lever for moving said vane between a closed position and an open position; and,(d) a mechanism for incrementally rotating said bushing to a new circumferential position with respect to said vane stem as said vane is cycled each time between said closed and open positions.2. The variable vane assembly of claim 1 , said bushing including a plurality of stepped portions circumferentially spaced about a top surface of said bushing.3. The variable vane assembly of claim 2 , further comprising a plurality of pawls associated with said lever claim 2 , wherein said pawls engage one of said stepped portions of said bushing top surface to cause said bushing to rotate in a first direction a predetermined amount as said vane moves from said closed position to said open position.4. The variable vane assembly of claim 2 , said bushing including a plurality of indented stops circumferentially spaced about a side surface of said bushing.5. The variable vane assembly of claim 4 , further comprising at least one pawl associated with said casing which engages one of said indented stops of said bushing side surface to prevent said bushing from rotating in a second direction opposite said first direction more than a second predetermined amount as said vane moves from ...

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Номер записи: 20
02-05-2013 дата публикации

Gas turbine engine with two-spool fan and variable vane turbine

Номер: US20130104521A1
Автор: Daniel B. Kupratis
Принадлежит: Individual

A gas turbine engine and a method of operating the gas turbine engine according to an exemplary aspect of the present disclosure includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.

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Номер записи: 21
23-05-2013 дата публикации

Method for operating a combustion device during transient operation

Номер: US20130125547A1
Автор: Douglas Anthony Pennell, Martin Zajadatz, Mirko Ruben Bothien
Принадлежит: Alstom Technology AG

A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).

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Номер записи: 22
23-05-2013 дата публикации

Systems and Methods For Optimizing Stoichiometric Combustion

Номер: US20130125555A1
Автор: Huntington Richard A., Mittricker Franklin F.
Принадлежит:

Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor. 1. A gas turbine system , comprising:an oxidant system;a fuel system;a control system;a plurality of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas;a plurality of oxidant-flow adjustment devices, wherein each of the plurality of oxidant-flow adjustment devices is operatively associated with one of the plurality of combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into an associated combustor; andan exhaust sensor in communication with the control system, wherein the exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and wherein the control system is configured to independently adjust one of the plurality of oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.2. The system of claim 1 , wherein the oxidant comprises oxygen and a diluent.3. The system of claim 1 , further comprising a diluent supply provided to each of ...

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Номер записи: 23
23-05-2013 дата публикации

Method and apparatus for optimizing the operation of a turbine system under flexible loads

Номер: US20130125557A1
Автор: Alston I. Scipio, Douglas Corbin Warwick, Joseph Klosinski, Michael Anthony Cocca, Mike Yarnold, Ryan Eric Obenhoff, Sanji Ekanayake, Thomas John Freeman
Принадлежит: Individual

A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.

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Номер записи: 24
30-05-2013 дата публикации

Method for monitoring the clearance of a kinematic link between a control member and a receiving member

Номер: US20130136575A1
Автор: Hichem Belghagi, Nicolas Potel
Принадлежит: SNECMA SAS

The method consists, based on an operating parameter of the turbojet engine, in: displacing said control member ( 11 ) in a direction as far as a first position (P 1 ) for which the receiving members ( 5 ) are rotated so as to take up the clearance of the kinematic link ( 12 ), then displacing said control member in the direction opposing the previous direction, as far as a second position (P 2 ) when a variation of the selected operating parameter is observed, and in ascertaining the travel of the control member ( 11 ) between the two positions corresponding to the total clearance of the kinematic link ( 12 ), and comparing the ascertained value of said travel of the control member with a predetermined limit value and, if it is observed that the ascertained value of the travel of the control member is greater than said limit value, to carry out monitoring of the kinematic link ( 12 ).

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Номер записи: 25
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: 26
06-06-2013 дата публикации

Method of positioning a control surface to reduce hysteresis

Номер: US20130142620A1
Автор: Jonathan Michael Moore, Simon Kenneth Haydn-Smith
Принадлежит: Rolls Royce PLC

A method of determining the actual position of a control surface ( 27 ). The method comprises receiving a signal ( 34 ) representative of a required position of the control surface ( 27 ), repositioning the control surface ( 27 ) in response to the signal ( 34 ) by moving an actuator ( 26 ), measuring a secondary position indicator, calculating the actual position of the control surface ( 27 ) on the basis of the secondary position indicator and, comparing the actual position with the required position.

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Номер записи: 27
13-06-2013 дата публикации

Gas turbine engine with fan variable area nozzle for low fan pressure ratio

Номер: US20130145745A1
Автор: Frederick M. Schwarz, Gregory A. Kohlenberg, Sean P. Zamora
Принадлежит: Individual

A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

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Номер записи: 28
13-06-2013 дата публикации

Method for optimizing the control of a free turbine power package for an aircraft, and control for implementing same

Номер: US20130151112A1
Автор: Jean-Michel Haillot
Принадлежит: Turbomeca SA

A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.

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Номер записи: 29
20-06-2013 дата публикации

System and method for warming up a steam turbine

Номер: US20130152587A1
Автор: Harold Lamar Jordan, JR., John Edward Sholes, JR., Tsungpo Lin
Принадлежит: General Electric Co

A system for warming up a steam turbine includes a gas turbine and a controller operably connected to the gas turbine. The controller is programmed to receive a plurality of measured input signals and control the gas turbine to produce an exhaust having a desired energy. A first measured input signal is reflective of a measured operating parameter of the gas turbine and a second measured input signal is reflective of an operating parameter of the steam turbine. A method for warming up a steam turbine includes sending a plurality of measured input signals to a controller, wherein a first measured input signal reflects a measured operating parameter of a gas turbine and a second measured input signal reflects an operating parameter of the steam turbine. The method further includes controlling the gas turbine based on the plurality of measured input signals and producing an exhaust from the gas turbine, wherein the exhaust has a desired energy.

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Номер записи: 30
20-06-2013 дата публикации

DETECTION OF THE INGRESS OF WATER OR HAIL INTO A TURBINE ENGINE

Номер: US20130158831A1
Автор: DJELASSI Cedrik, Riou Alexandra
Принадлежит: SNECMA

A detection method for detecting ingestion of water or hail in a gas turbine engine, the engine including at least a compressor, a combustion chamber, and a turbine, the method including: estimating a value of a first indicator representative of water or hail being ingested; estimating a value of a second indicator representative of water or hail being ingested, the second indicator being different from the first indicator; and calculating a value of a global indicator by summing at least the first indicator and the second indicator. 113-. (canceled)14. A detection method for detecting ingestion of water or hail in a gas turbine engine , the engine including at least a compressor , a combustion chamber , and a turbine , the method comprising:estimating a value of a first indicator representative of water or hail being ingested;estimating a value of a second indicator representative of water or hail being ingested, the second indicator being different from the first indicator; andcalculating a value of a global indicator by summing at least the first indicator and the second indicator.15. A detection method according to claim 14 , further comprising:measuring temperature at an inlet of the combustion chamber; andestimating a temperature modeling the measured temperature;wherein the value of the first indicator is estimated as a function of a difference between a drop in the measured temperature and a drop in the estimated temperature, and the value of the second indicator is estimated as a function of a difference between the measured temperature and the estimated temperature.16. A detection method according to claim 15 , wherein the value of the first indicator is estimated while taking account of a normalization function that minimizes an importance of small drops in the measured temperature.17. A detection method according to claim 15 , further comprising:measuring a speed of rotation of the compressor and of the turbine;wherein the value of the second indicator ...

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Номер записи: 31
27-06-2013 дата публикации

Dual Gain Digital Engine Control

Номер: US20130166169A1
Автор: James M. McCollough
Принадлежит: BELL HELICOPTER TEXTRON INC

An engine control system having an engine, a digital engine control, and a gain logic disposed within the digital engine control for use with an aircraft. The digital engine control is configured to receive and process inputs from systems within the aircraft. Gain logic uses the inputs to generate command data to regulate the performance of the engine so as to allow rotor speed deviations from a set point.

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Номер записи: 32
04-07-2013 дата публикации

Automated tuning of multiple fuel gas turbine combustion systems

Номер: US20130173074A1
Автор: Christopher Chandler
Принадлежит: Gas Turbine Efficiency Sweden AB

Provided herein is a method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources. The method further includes sensing the operational parameters of a turbine and determining whether the operational parameters are within preset operational limits. The method also adjusting the ration of the first fuel source to the second fuel source, based on whether the operational parameters are within the preset operational limits.

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Номер записи: 33
11-07-2013 дата публикации

Fuel Flow Control Method and Fuel Flow Control System of Gas Turbine Combustor for Humid Air Gas Turbine

Номер: US20130174571A1
Автор: ABE KAZUKI, KOGANEZAWA Tomomi
Принадлежит: Hitachi, Ltd.

Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent. 1. A fuel flow control method of a gas turbine combustor provided in a humid air gas turbine comprising a compressor , the gas turbine combustor , in which a fuel is burned with the use of a compressed air compressed by the compressor to generate a combustion gas , a turbine driven by a combustion gas generated in the gas turbine combustor , and a humidifier for humidifying a compressed air compressed by the compressor and supplied to the gas turbine combustor , the gas turbine combustor comprising a plurality of combustion sections comprised of a plurality of fuel nozzles for supplying of a fuel and a plurality of air flow passages for supplying of a combustion air , a part of the plurality of combustion sections provided in the gas turbine combustor being formed into a combustion section or sections , which are more excellent in flame holding performance than the remaining combustion sections , in which method fuel ratios of fuels , respectively , supplied to the plurality of combustion sections of the gas turbine combustor are controlled on the basis of deviation between a load command and electric power generation ,the method comprising controlling a fuel flow rate to the combustion sections in the gas turbine combustor through evaluating a moisture content in a combustion air supplied to the gas turbine combustor on the basis of a humidification water quantity and an air temperature after humidification in the humidifier, using a combustion air flow rate supplied to the gas turbine combustor to evaluate a combustion temperature in the combustion sections, and regulating a fuel ratio of a fuel flow rate supplied to the combustion section or sections of excellent flame holding performance and a fuel ...

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Номер записи: 34
18-07-2013 дата публикации

Methods and systems for managing power of an engine

Номер: US20130184961A1
Автор: Aditya Kumar, Avinash Vinayak Taware, Pierino Gianni Bonanni, Santanu Chatterjee
Принадлежит: General Electric Co, General Electric Global Research Center

A method and system for online power management of a turbine engine is provided. The method includes operating an engine control system on a first bandwidth, filtering at least one data input from the engine control system to a second bandwidth, and receiving, by a power management system operating on the second bandwidth, the at least one filtered data input. The method also includes predicting an engine operating condition using the at least one filtered data input using a closed-loop engine model, determining an optimal engine power management based on the prediction, solving a constrained optimization for a desired optimization objective, and outputting the optimal engine power management to the engine control system.

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Номер записи: 35
25-07-2013 дата публикации

Fluid flow control device and method

Номер: US20130186098A1
Автор: Bruce Paradise
Принадлежит: Hamilton Sundstrand Corp

A fluid flow control system includes a fluid inlet, a central chamber, a first nozzle extending from a first side of the central chamber and comprising a first throat, a second nozzle extending from a second side of the central chamber opposite the first side and comprising a second throat, and a flow control shuttle. The flow control shuttle includes a first needle having a first tapered portion positioned within the first throat for controlling flow through the first nozzle and a second needle having a second tapered portion positioned within the second throat for controlling flow through the second nozzle.

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Номер записи: 36
08-08-2013 дата публикации

Method of automatically regulating an aircraft power plant, a device, and an aircraft

Номер: US20130199198A1
Автор: Alban Corpron
Принадлежит: Eurocopter SA

A method of automatically regulating a power plant ( 3 ′) of an aircraft ( 1 ), said power plant comprising at least one turbine engine ( 3 ), said aircraft ( 1 ) having at least one rotary wing ( 300 ) provided with a plurality of blades ( 301 ) having variable pitch and driven in rotation by said power plant ( 3 ′), it being possible for each engine ( 3 ) to operate in an idling mode of operation and in a flight mode of operation. During a selection step (STP 0 ), a two-position selector ( 60 ) is operated either to stop each engine ( 3 ) or to set each engine ( 3 ) into operation. During a regulation step (STP 1 ), each engine ( 3 ) is controlled automatically so as to implement the idling mode of operation if the collective pitch (CLP) of said blades is less than a threshold and if the aircraft ( 1 ) is standing on the ground.

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Номер записи: 37
22-08-2013 дата публикации

COMBUSTION DEVICE WITH PULSED FUEL SPLIT

Номер: US20130213052A1
Автор: Brickwood Gavin, Bulat Ghenadie
Принадлежит:

It is described a combustion device control unit and a combustion device, e.g. a gas turbine, which determine on the basis of at least one operating parameter whether the combustion device is in a predefined operating stage. In response hereto, there is generated a control signal configured for setting a ratio of at least two different input fuel flows to a predetermined value (psc, psc) for a predetermined time (dt) in case the combustion device is in the predefined operating stage. 18.-. (canceled)9. A control unit of a combustion device , comprising:an control input for receiving at least one operating parameter indicating an operation of the combustion device; andan control output for outputting a control signal for controlling at least two different input fuel flows to the combustion device;wherein the control unit is configured to determine whether the combustion device is in a predefined operating stage based on the at least one operating parameter,wherein the control unit is configured to generate the control signal to set a ratio of the at least two different input fuel flows to a predetermined value for a predetermined time in case the combustion device is in the predefined operating stage,wherein the ratio of the at least two different input fuel flows is set to the predetermined value by changing the ratio of the at least two different input fuel flows from a present value to the predetermined value in a stepwise manner, andwherein the ratio of the at least two different input fuel flows is set to the predetermined value for the predetermined time comprising a pulse shaped temporal change of the ratio of the at least two different input fuel flows.10. The control unit according to claim 9 , wherein after the predetermined time the ratio of the at least two different input fuel flows is set to a value that corresponds to a control regime applied before setting the ratio of the at least two different input fuel flows to the predetermined value.11. The ...

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Номер записи: 38
22-08-2013 дата публикации

CONTROL OF A FUEL METERING DEVICE FOR TURBOMACHINE

Номер: US20130213053A1
Автор: GAULLY Bruno Robert, MAROT Cécile
Принадлежит: SNECMA

A control of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint includes responding to at least one validity criterion to select a weight flow rate from among: a weight flow rate calculated as a function of a position signal; a weight flow rate calculated as a function of the position signal and of at least one temperature measurement signal; a weight flow rate calculated as a function of the position signal and of at least one permittivity measurement signal; a weight flow rate calculated as a function of the position signal, of at least one temperature measurement signal, and of at least one permittivity measurement signal; and a weight flow rate calculated as a function of a temperature measurement signal, of a permittivity measurement signal, and of a volume flow rate measurement signal. 110-. (canceled)11. A method of controlling a position of a slide of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint , the method comprising:obtaining a position signal coming from a sensor configured to measure a position of the slide;obtaining at least one measurement signal coming from a flow meter configured to measure a fuel flow rate in the flow meter;estimating at least one validity criterion for the at least one measurement signal;determining a fuel weight flow rate through the flow meter; andcontrolling the position of the slide as a function of the determined weight flow rate and of the weight flow rate setpoint;the at least one measurement signal comprises first and second fuel temperature measurement signals, first and second fuel permittivity measurement signals, and first and second fuel volume flow rate measurement signals; and a weight flow rate calculated as a function of the position signal;', 'a weight flow rate calculated as a function of the position signal and of at least one of the temperature measurement signals;', 'a weight flow rate calculated as a function of the position ...

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Номер записи: 39
22-08-2013 дата публикации

GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE POSITIONED FOR STARTING

Номер: US20130213055A1
Автор: Wehmeier Eric J.
Принадлежит:

A gas turbine engine has a compressor section, a low spool, and a fan. The fan delivers air into the compressor section and into a bypass duct having a variable area nozzle. The compressor section compresses air and delivers it into a combustion section. The combustion section mixes air with fuel, igniting the fuel, and driving the products of the combustion across a turbine. The turbine drives the low spool. A control for the gas turbine engine is programmed to position the nozzle at startup of the engine to increase airflow across the fan. A variable inlet guide vane is positioned upstream of the compressor section. The control also positions the variable inlet guide vane at start-up to increase air flow across the compressor section. 1. A gas turbine engine comprising:a compressor section;a low spool;a fan;said fan delivering air into said compressor section and into a bypass duct having a variable area nozzle, and said compressor section compressing air and delivering it into a combustion section;the combustion section mixing air with fuel, igniting the fuel, and driving the products of the combustion across a turbine, said turbine driving said low spool;a control system for said gas turbine engine, programmed to position said variable area nozzle at startup of the engine to increase airflow across said fan; anda variable inlet guide vane is positioned upstream of said compressor section, and said control system also positioning said variable inlet guide vane at start-up to increase air flow across said compressor section.2. The engine as set forth in claim 1 , wherein said compressor section includes a high pressure compressor and a low pressure compressor claim 1 , and said turbine includes a low turbine driving said low spool and said low pressure compressor.3. The engine as set forth in claim 2 , wherein said fan is driven with said low pressure compressor by said low spool claim 2 , and there being a gear reduction between said fan and said low spool.4. The ...

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Номер записи: 40
29-08-2013 дата публикации

Methods of Operation of A Gas Turbine With Improved Part Load Emissions Behavior

Номер: US20130219904A1
Автор: Eroglu Adnan, Flohr Peter, Geng Weiqun, Knapp Klaus, Knoepfel Hans Peter
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (λ) of the operative burners () of the second combustor () is kept below a maximum air ratio (λ) at part load In order to reduce the maximum air ratio (λ), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes () before engaging the second combustor (). For engaging the second combustor, the row of variable compressor inlet guide vanes () is quickly closed and fuel is introduced in a synchronized manner into the burner () of the second combustor (). A further modification is the deactivating of individual burners () at part load. 1. A method for the low-CO emissions operation of a gas turbine with sequential combustion , wherein the gas turbine includes a first turbine , a second turbine , at least one compressor , a first combustor which is connected downstream to the compressor and the hot gases of which first combustor are admitted to the first turbine , and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine , the second combustor including operative burners each having an air ratio (λ) , the method comprising:{'sub': 'max', 'maintaining the air ratio (λ) of the operative burners of the second combustor below a maximum air ratio (λ).'}2. The method as claimed in claim 1 , further comprising:{'b': '2', 'shutting off a fuel feed to at least one burner of the second combustor at part load so that, with an unaltered turbine inlet temperature of the second turbine (TIT), an air ratio (λ) of the burners in operation is reduced.'}3. The method as claimed in claim 2 , wherein:the second combustor includes a parting plane; andshutting off a fuel feed to at least one burner of the second combustor at part load comprises first shutting ...

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Номер записи: 41
29-08-2013 дата публикации

AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS

Номер: US20130219906A1
Автор: Chandler Christopher
Принадлежит: Gas Turbine Efficiency Sweden AB

A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter. 1. A system for tuning the operation of a gas turbine , the turbine having sensors for measuring operational parameters of the turbine , the operational parameters including combustor dynamics , and turbine exhaust emissions , the turbine also having operational controls for adjusting various operational control elements of the turbine , the operational control elements comprising the turbine fuel distribution splits , the inlet fuel temperature , and fuel-air ratio , and a communication link for the sensors and controls , the system comprising: receiving operational data regarding the operational parameters including combustor dynamics and turbine exhaust emissions from the sensors,', 'comparing the operational data to stored operational standards and determining if turbine operation conforms to the operational standards, the operational standards based on operational priorities,', 'communicating with the operational controls to perform a selected adjustment in an operational control element of the turbine,', 'receiving operational data from the sensors upon communicating the selected adjustment to determine if an additional incremental adjustment is desired, and', 'upon completing a series of ...

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Номер записи: 42
29-08-2013 дата публикации

Exhaust temperature based threshold for control method and turbine

Номер: US20130219910A1
Автор: Claudio Botarelli
Принадлежит: Individual

A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.

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Номер записи: 43
29-08-2013 дата публикации

Variable area turbine

Номер: US20130223974A1
Автор: Daniel Bernard Kupratis, Frederick M. Schwarz
Принадлежит: Individual

A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

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Номер записи: 44
05-09-2013 дата публикации

GAS TURBINE ENGINE CONFIGURED TO SHAPE POWER OUTPUT

Номер: US20130227954A1
Автор: Bohinsky Brian J., Marini Bonnie D.
Принадлежит:

A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid. 1. A gas turbine engine system configured for power generation , the gas turbine engine system comprising:a compressor, a combustor and a turbine, the compressor providing compressed air to the combustor for combustion with a fuel to produce a hot working gas and the turbine receiving the hot working gas to produce power;the compressor and turbine being configured with reference to a reference engine, the reference engine defining a configuration having a predetermined mass flow for a predetermined turbine inlet temperature to produce an optimum efficiency at a predetermined compressor inlet condition at a maximum power output for the reference engine;the turbine comprising a configuration substantially identical to the turbine of the reference engine;the compressor having a configuration different than the compressor of the reference engine, wherein the compressor is sized larger than the compressor of the reference engine to provide a maximum flow capability of the compressor greater than an upper flow capability of the compressor of the reference engine;including inlet guide vanes (IGVs) at an inlet to the compressor, the IGVs having a predetermined position for reducing the mass flow of air into the compressor to a flow less than the maximum flow capability for operating the engine at an optimum efficiency at the predetermined turbine inlet temperature of the reference engine.2. The gas turbine engine system of claim 1 , wherein the predetermined position of the IGVs defines a ...

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Номер записи: 45
12-09-2013 дата публикации

Apparatus for Releasing a Flow Cross Section of a Gas Line

Номер: US20130232990A1
Автор: Martin Lenz, Sascha Stoll
Принадлежит: MAN Diesel and Turbo SE

An apparatus is described for the controlled release of a flow cross section of a gas line which is connected to a combustion chamber of a gas engine. The apparatus has a check valve and a flexible device. The flexible device is provided for absorbing a force occurring as a result of a thermal expansion of the check valve.

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Номер записи: 46
12-09-2013 дата публикации

SYSTEM AND METHOD FOR TURBOMACHINE MONITORING

Номер: US20130236290A1
Автор: Shinkle William Randolph, Singh Hardev
Принадлежит: GENERAL ELECTRIC COMPANY

A system for monitoring a turbomachine is provided. The system includes a turbomachine component having a variable geometry, a first sensor disposed to sense a condition of the turbomachine component, a second sensor disposed to sense an operational condition of the turbomachine, the operational condition being associated with an operation of the turbomachine component and a controller operably coupled to the first and second sensors, the controller being configured to execute a turbomachine process in accordance with a result of sensing by the second sensor with respect to the operational condition regardless of whether the first sensor detects the condition. 1. A system for monitoring a turbomachine , comprising:a turbomachine component having a variable geometry;a first sensor disposed to sense a condition of the turbomachine component;a second sensor disposed to sense an operational condition of the turbomachine, the operational condition being associated with an operation of the turbomachine component; anda controller operably coupled to the first and second sensors, the controller being configured to execute a turbomachine process in accordance with a result of sensing by the second sensor with respect to the operational condition regardless of whether the first sensor detects the condition.2. The system according to claim 1 , wherein the turbomachine component comprises a variable stator vane (VSV) system.3. The system according to claim 2 , wherein the VSV system comprises:compressor inlet vanes disposed to occupy a predefined vane angle to thereby control an amount of air permitted to flow through a compressor of the turbomachine;an actuation system configured to control the compressor inlet vanes to assume the predefined vane angle; anda system controller operably disposed to respond to a failure of the compressor inlet vanes to assume the predefined vane angle by a predefined threshold for more than a predefined time period.4. The system according to ...

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Номер записи: 47
19-09-2013 дата публикации

Hybrid gas turbine engine-electric motor/generator drive system

Номер: US20130239577A1
Автор: Robert Eleazar Mendoza, Roy Thomas Collins, Steven Howard DeMoss
Принадлежит: Solar Turbines Inc

A method of operating a drive system for a load is disclosed. The drive system may have an electric motor/generator and a gas turbine engine. The engine may have a combustor, and main and pilot flow paths via which fuel is supplied to the combustor. The engine may be operable in low and standard emissions modes. A proportion of the fuel that is supplied to the combustor via the pilot flow path may be greater in the standard emissions mode than in the low emissions mode. The method may include determining an engine power requirement of the load, and whether the engine power requirement of the load is sufficiently large to operate the engine in the low emissions mode. Additionally, the method may include operating the electric motor/generator if the engine power requirement of the load is not sufficiently large to operate the engine in the low emissions mode.

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Номер записи: 48
17-10-2013 дата публикации

Systems and Methods for Detecting Fuel Leaks in Gas Turbine Engines

Номер: US20130269364A1
Автор: Bryan Wesley Romig, Derrick Simons, Douglas Dean
Принадлежит: General Electric Co

Embodiments can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak.

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Номер записи: 49
24-10-2013 дата публикации

Gas turbine inlet system and method

Номер: US20130276458A1
Автор: Michael Corey Mullen, Rex Allen Morgan
Принадлежит: General Electric Co

A gas turbomachine inlet system includes a duct member having an inlet portion fluidically coupled to an outlet portion through an intermediate portion. The inlet portion, outlet portion, and intermediate portion define a fluid flow zone. A throttling system is arranged in the duct member at one of the inlet portion, outlet portion and intermediate portion. The throttling system is configured and disposed to selectively establish a pressure drop through the fluid flow zone. A method of controlling inlet pressure drop through an inlet system for a gas turbomachine is also described herein.

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Номер записи: 50
31-10-2013 дата публикации

Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

Номер: US20130283811A1
Автор: Nicolas Potel, Sébastien Gameiro
Принадлежит: SNECMA SAS

A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

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Номер записи: 51
07-11-2013 дата публикации

AERO COMPRESSION COMBUSTION DRIVE ASSEMBLY CONTROL SYSTEM

Номер: US20130291550A1
Автор: Fuchs Michael J., Weinzierl Steven M.
Принадлежит: ENGINEERED PROPULSION SYSTEMS, INC.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included. 1. A control method for an aero compression combustion drive assembly , the aero compression combustion drive assembly having an engine member , a transmission member and a propeller member , the control system comprising:sensing a pressure parameter in each of a plurality of compression chambers of the engine member;providing the sensed pressure parameter to a control system device;providing a plurality of control programs to the control system device; andthe control system device acting on the sensed pressure parameter to effect a control strategy in the engine member.2. The control method of claim 1 , including implementing the control strategy in the engine member by affecting the operation of at least one fuel injector.3. The control method of claim 2 , including affecting a fuel pulse timing of at least one fuel injector.4. The control method of claim 2 , including affecting a fuel pulse duration of at least one fuel injector.5. The control method of claim 2 , including affecting the operation of at least one turbocharger.6. A control method for an aero compression combustion drive assembly claim 2 , the aero compression combustion drive assembly having an engine member claim 2 , a transmission member and a propeller member claim 2 , the control system comprising:sensing a pressure parameter in each of ...

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Номер записи: 52
21-11-2013 дата публикации

GAS TURBINE SYSTEM

Номер: US20130305735A1
Автор: Ahn Chul-Ju
Принадлежит:

Provided is a gas turbine including: a first compressor which compresses air; a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture; a combustor which combusts the generated fuel mixture from the mixer; a plurality of flow meters which adjusts an amount of the air or the fuel injected into the mixer; and a control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index rang. 1. A gas turbine system comprising:a first compressor which compresses air;a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture;a combustor which combusts the generated fuel mixture from the mixer;a plurality of flow meter which adjust an amount of the air or the fuel injected into the mixer; anda control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index range.2. The gas turbine system of claim 1 , wherein the first compressor compresses the air supplied from an external source.3. The gas turbine system of claim 1 , further comprising a second compressor which compresses the air supplied from an external source claim 1 , and supplies the compressed air from the second compressor to at least one of the combustor and the first compressor.4. The gas turbine system of claim 1 , wherein the plurality of flow meters comprise a fuel flow meter which adjusts an amount of the fuel supplied to the mixer.5. The gas turbine system of claim 4 , further comprising a first sensor unit which measures at least one of a temperature claim 4 , a pressure claim 4 , and a flux of fuel ejected from the fuel flow meter.6. The gas turbine system of claim 1 , further comprising a heat exchanger which heats at least one of the air ejected from the first compressor and the fuel supplied to the mixer.7. The gas turbine system of claim 6 , further comprising a turbine which operates by a combustion gas ejected from the combustor claim 6 ,wherein the heat ...

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Номер записи: 53
05-12-2013 дата публикации

Protecting operating margin of a gas turbine engine

Номер: US20130319009A1
Автор: Wayne P. PARENTE
Принадлежит: Individual

A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject to a control parameter. The control parameter is selectively modified in response to the aerodynamic distortion.

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Номер записи: 54
12-12-2013 дата публикации

Fuel metering valve fail-fixed and back-up control system

Номер: US20130327044A1
Автор: Brad McRoberts, David Tuttle, Greg Lafferty, Gregory Kline, Larry Portolese, Paul W. Futa
Принадлежит: Honeywell International Inc

A system provides “fail fixed” functionality and allows a user to manually manipulate fuel flow to a gas turbine engine in the unlikely event the primary control means is unavailable. The fuel metering unit includes a fuel metering valve, a flow increase valve, and a flow decrease valve. The flow increase valve and flow decrease valves are both in fluid communication with the fuel metering valve and are each adapted to selectively receive fuel flow commands from a primary fuel flow command source and from a secondary fuel flow command source. The flow increase and decrease valves are responsive to the fuel flow commands to selectively control the position of the fuel metering valve.

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Номер записи: 55
26-12-2013 дата публикации

Gas fuel turbine engine for reduced oscillations

Номер: US20130340436A1
Автор: Mario E. Abreu
Принадлежит: Solar Turbines Inc

A gas fuel turbine engine may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors, and the second main fuel supply may provide gaseous fuel to a second plurality of fuel injectors. The turbine engine may also include a flow restriction provided in the first main fuel supply. The second main fuel supply may be free of the flow restriction.

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Номер записи: 56
09-01-2014 дата публикации

LIQUID FUEL ASSIST IGNITION SYSTEM OF A GAS TURBINE AND METHOD TO PROVIDE A FUEL/AIR MIXTURE TO A GAS TURBINE

Номер: US20140007585A1
Автор: Liu Kexin
Принадлежит:

A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase includes a high pressure tank, a vacuum pump connected to the high pressure tank, a liquid fuel inlet connected to the high pressure tank, an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine. 117-. (canceled)18. A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase , comprisinga high pressure tank,a vacuum pump connected to the high pressure tank,a liquid fuel inlet connected to the high pressure tank,an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine.19. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an air pump connected to the air inlet for providing air to the high pressure tank.20. The liquid fuel assist ignition system according to claim 18 , wherein the vacuum pump and/or the liquid fuel inlet and/or the air inlet and/or the outlet and/or the pipes between the vacuum pump claim 18 , the liquid fuel inlet claim 18 , the air inlet and/or the outlet comprise(s) one or more control elements.21. The liquid fuel assist ignition system according to claim 20 , wherein the connection elements comprise switchable valves.22. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel inlet comprises a needle like pipe.23. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an external heat source to heat up the high pressure tank.24. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source is an electric heater.25. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source comprises a temperature controller and/or ...

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Номер записи: 57
06-02-2014 дата публикации

Controller for Gas Turbine Power Plant

Номер: US20140033720A1
Автор: Eunkyeong Kim, Kazuhito Koyama, Kazuo Takahashi, Naohiro Kusumi, Shigeo Hatamiya, Takuya Yoshida, Yukinori Katagiri
Принадлежит: HITACHI LTD

A controller for use in a gas turbine power plant includes a compressor that compresses combustion air; a water-atomization cooling apparatus that sprays water drops of atomized water supplied via a water-atomization flow-rate regulating valve over a flow of air drawn in the compressor; a combustor that mixes the compressed combustion air with fuel to thereby burn a fuel-air mixture and generate combustion gas at high temperature and performs combustion switching during operation; a turbine that uses the combustion gas to drive the compressor and a generator; the water-atomization flow-rate regulating valve that controls a flow rate of the atomized water; and a compressor inlet inner blade that controls a flow rate of air drawn in the compressor. The controller includes control means that calculates a fuel-air ratio correction command signal for compensating for reduction in a fuel-air ratio in the combustor occurring during the combustion switching.

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Номер записи: 58
06-02-2014 дата публикации

Method for fuel temperature control of a gas turbine

Номер: US20140033731A1
Автор: RACKWITZ Leif
Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

The present invention relates to a method for controlling the fuel temperature of a gas turbine, where parameters are determined as input values, where the parameters are compared with emission-optimized nominal values and an optimum fuel temperature is determined, and where the fuel to be supplied to a combustion chamber is heated or cooled. 1. Method for controlling the fuel temperature of a gas turbine , where parameters are determined as input values , where the parameters are compared with emission-optimized nominal values and an optimum fuel temperature is determined , and where the fuel to be supplied to a combustion chamber is heated or cooled.2. Method in accordance with claim 1 , characterized in that when an acceleration or deceleration state of the gas turbine is detected claim 1 , the nominal value of the fuel temperature is set to the value prevailing before implementation of the method claim 1 , and/or the additional fuel heating or fuel cooling is switched off.3. Method for controlling the fuel temperature of a gas turbine claim 1 , where the issue of an ignition command by a pilot or by an electronic engine control system is determined claim 1 , where the maximum permissible temperature of the fuel is determined for an ignition process and the fuel is heated to the maximum temperature.4. Method for controlling the fuel temperature of an aircraft gas turbine claim 1 , in particular in accordance with claim 1 , where the issue of an ignition command by a pilot or by an electronic engine control system is determined claim 1 , where the maximum permissible temperature of the fuel is determined for an ignition process and the fuel is heated or cooled to the maximum temperature.5. Method in accordance with claim 1 , characterized in that the optimum or the maximum nominal temperature of the fuel is then compared with a maximum permissible fuel temperature claim 1 , and when the maximum permissible fuel temperature is exceeded the fuel is not heated to a ...

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Номер записи: 59
13-03-2014 дата публикации

Fuel metering system electrically servoed metering pump

Номер: US20140072457A1
Автор: Dwayne Michael Benson
Принадлежит: Honeywell International Inc

A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

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Номер записи: 60
20-03-2014 дата публикации

Method for the elimination of rotational stall in a turbine engine

Номер: US20140075952A1
Автор: Cedrik Djelassi
Принадлежит: SNECMA SAS

A method for eliminating rotational stall in a compressor of a turbine engine, includes automatically detecting surge in the turbine engine; automatically shutting-down the turbine engine; in the event surge is detected, automatically restoring a surge margin; and automatically re-igniting the turbine machine.

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Номер записи: 61
27-03-2014 дата публикации

STROKE TRANSMITTER FOR GAS TURBINE

Номер: US20140083104A1
Автор: Bachmaier Georg, Höge Michael, Nordin Joachim
Принадлежит:

A stroke transmitter is presented. The stroke transmitter includes a conduit for providing a passage to a fluid, an actuating unit for increasing pressure in an hydraulic fluid, a valve unit configured to operate depending on the pressure of the hydraulic fluid, the valve unit arranged inside the conduit to regulate a flow of the fluid, and a pipe connecting the actuating unit and the valve unit for communicating the pressure of the hydraulic fluid between the actuating unit and the valve unit. The actuating unit is arranged outside the conduit. 115.-. (canceled)16. A stroke transmitter , comprising:a conduit for providing a passage to a fluid;an actuating unit comprising a first block and a first piston, wherein the first piston is guided into the first block thereby increasing a pressure in an hydraulic fluid;a valve unit comprising a second block, a dosing valve and a second piston, wherein the second piston is guided into the second block, the valve unit configured to operate depending on the pressure of the hydraulic fluid to regulate a flow of the fluid; anda pipe connecting the actuating unit and the valve unit for communicating the pressure of the hydraulic fluid between the actuating unit and the valve unit,wherein the actuating unit is arranged outside the conduit, andwherein the valve unit is arranged inside the conduit.17. The stroke transmitter according to claim 16 , wherein the actuating unit and the valve unit are arranged at an angle relative to each other.18. The stroke transmitter according to claim 17 , wherein the angle is from 45 degrees to 135 degrees.19. The stroke transmitter according to claim 16 , wherein the actuating unit and the valve unit are arranged perpendicular to each other.20. The stroke transmitter according to claim 16 , wherein the first block of the actuating unit is mechanically coupled to an actuator.21. The stroke transmitter according to claim 20 , wherein the actuator is a piezoelectric actuator.22. The stroke ...

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Номер записи: 62
03-04-2014 дата публикации

Adaptive fuel manifold filling function for improved engine start

Номер: US20140095051A1
Автор: Sylvain Lamarre
Принадлежит: Pratt and Whitney Canada Corp

There is described a system and method for filling an engine fuel manifold. An adaptive filling function is used to determine a flow rate at which fuel is to be delivered to the fuel manifold. The filling function receives as an input a present measurement of the engine's speed and computes the flow rate accordingly. The fuel manifold may then be filled according to the computed flow rate so as to match the engine's speed. Appropriate fuel/air ration conditions can therefore be achieved for successful engine start.

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Номер записи: 63
01-01-2015 дата публикации

METHOD FOR DETERMINING AT LEAST ONE FIRING TEMPERATURE FOR CONTROLLING A GAS TURBINE AND GAS TURBINE FOR PERFORMING THE METHOD

Номер: US20150000297A1
Автор: ARIAS CHAO Manuel, LILLEY Darrel Shayne, Nemet Anton, STEIGER Ulrich Robert
Принадлежит:

The invention relates to a method for determining at least one firing temperature for controlling a gas turbine that comprises at least one compressor, at least one combustion chamber and at least one turbine, compressed air being drawn off at the compressor in order to cool the turbine and being fed to the turbine via at least one external cooling duct and via a control valve arranged in the cooling duct, in which method a plurality of temperatures and pressures of the working medium being measured in various positions of the gas turbine and the at least one firing temperature being derived from the measured temperatures and pressures. A more flexible and more accurate control is achieved additionally by determining the cooling air mass flow via the external cooling duct and by taking said flow into account when deriving the at least one firing temperature. 1. A method for determining at least one firing temperature for controlling a gas turbine having at least one compressor , at least one combustion chamber and at least one turbine; the method comprising:for cooling the turbine, compressed air is extracted at the compressor and is fed to the turbine via at least one external cooling line and a controlling valve arranged in the cooling line, in which method a plurality of temperatures and pressures of the working medium are measured at various points in the gas turbine and the at least one firing temperature is derived from the measured temperatures and pressures, characterized in that, in addition, the cooling air mass flow rate through the external cooling line is determined and is taken into account when deriving the firing temperature.2. The method as claimed in claim 1 , wherein the firing temperature has a correction factor which is determined by the change in the turbine inlet pressure as a function of the moisture content relative to a reference value of the turbine inlet pressure.3. The method as claimed in claim 2 , wherein the moisture content is used ...

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Номер записи: 64
02-01-2020 дата публикации

PROPELLER BLADE SYNCHROPHASING USING PHONIC WHEEL

Номер: US20200001978A1
Автор: JARVO James R., TABAR Roja, YAKOBOV Ella
Принадлежит:

Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel is coupled to a first propeller of a first engine of the aircraft. A sensor is disposed and configured for producing a signal in response to passage of first and second position markers on the phonic wheel. A control system is communicatively coupled to the sensor for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker; determining, based on a particular time at which the particular pulse associated with the second position marker was produced, that a rotational position of the first propeller corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller. 1. A system for synchrophasing a multi-engine aircraft , comprising:a phonic wheel coupled to a first propeller of a first engine of the aircraft, the phonic wheel comprising a plurality of circumferentially uniformly-spaced first position markers disposed on an outer circumferential surface of the phonic wheel and a second position marker disposed on the outer surface, the second position marker disposed circumferentially closer to a selected one of the first position markers than to the remaining first position markers and being indicative of a reference position of the propeller, the phonic wheel configured to rotate during operation of the first engine;a sensor adjacent the phonic wheel and configured for producing a signal in response to passage of the first position markers and the second position marker, the signal comprising a plurality of signal pulses corresponding to the passage of the plurality of first position markers and of the second position marker during rotation of the phonic wheel; and ...

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Номер записи: 65
03-01-2019 дата публикации

Propulsion system for an aircraft

Номер: US20190002116A1
Автор: Michael Thomas Gansler, Robert Charles HON
Принадлежит: General Electric Co

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

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Номер записи: 66
05-01-2017 дата публикации

METHOD OF CONTROLLING A POSITION ACTUATION SYSTEM COMPONENT FOR A GAS TURBINE ENGINE

Номер: US20170002681A1
Автор: DESAI Premal, MEINERS Kenneth Paul, STRIKER John A.
Принадлежит:

A method for controlling a position actuation system component in a gas turbine engine based on a modified proportional and integral control loop is provided. The method includes determining an error value between a demand signal for the position actuation system component and a position signal for the position actuation system component. The method also includes determining an integral gain scaler as a function of a scheduling parameter value and determining an integral gain based on the determined error value and the determined integral gain scaler. Additionally the method includes determining a proportional gain scaler as a function of the scheduling parameter value and determining a proportional gain based on the determined error value and the determined proportional portion gain scaler. The method adds the determined integral gain with the determined proportional gain to determine a null current value for the position actuation system component. 1. A method for controlling a position actuation system component in a gas turbine engine , the method comprising:determining an error value between a demand signal for the position actuation system component and a position signal of the position actuation system component;determining a scheduling parameter value of the gas turbine engine; anddetermining a null current value for the position actuation system component, wherein determining the null current value includesdetermining an integral gain scaler as a function of the scheduling parameter value;determining an integral gain based on the determined error value and the determined integral gain scaler;determining a proportional gain scaler as a function of the scheduling parameter value;determining a proportional gain based on the determined error value and determined proportional gain scaler; andadding the determined integral gain and the determined proportional gain to determine the null current value.2. The method of claim 1 , wherein the scheduling parameter is a ...

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Номер записи: 67
04-01-2018 дата публикации

SYSTEM AND METHOD FOR A GAS TURBINE ENGINE

Номер: US20180003083A1
Автор: Dhanuka Sulabh K., Huntington Richard A.
Принадлежит:

A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas, a differential temperature monitor configured to monitor a differential temperature between a first temperature of the portion of exhaust gas upstream of the catalyst bed and a second temperature of the treated exhaust gas downstream of the catalyst bed, and an oxidant-to-fuel ratio system configured to adjust a parameter to maintain an efficacy of the catalyst bed based at least in part on the differential temperature in order to maintain a target equivalence ratio. 1. A method , comprising:combusting an oxidant and a fuel in a gas turbine engine to generate an exhaust gas;treating a portion of the exhaust gas from the gas turbine engine in a catalyst bed to generate a treated exhaust gas;determining a differential temperature between a first temperature of the portion of the exhaust gas upstream of the catalyst bed and a second temperature of the treated exhaust gas downstream of the catalyst bed using a differential temperature monitor;monitoring a gas composition of the treated exhaust gas downstream of the catalyst bed using a gas composition sensor; andadjusting an oxidant flow rate of the oxidant, or a fuel flow rate of the fuel, or both, using an oxidant-to-fuel ratio system to achieve a target equivalence ratio of the gas turbine engine based on the differential temperature and the gas composition.2. The method of claim 1 , comprising monitoring an equivalence ratio of the portion of exhaust gas upstream of the catalyst bed using an oxidant-to-fuel sensor.3. The method of claim 2 , comprising comparing the equivalence ratio monitored with the oxidant-to-fuel sensor to the target equivalence ratio and adjusting the oxidant flow rate of the oxidant claim 2 , or the fuel flow rate of the fuel claim 2 , or both claim 2 , based ...

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Номер записи: 68
07-01-2021 дата публикации

GAS TURBINE ENGINE WITH MORPHING VARIABLE COMPRESSOR VANES

Номер: US20210003030A1
Автор: Chaudhry Zaffir A., Evans Simon W., Joly Michael M., Medic Gorazd, Prasad Dilip
Принадлежит:

A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed. 1. A stator vane for a gas turbine engine section comprising:a stator vane having an airfoil extending between a leading edge and a trailing edge, said airfoil having a suction side and a pressure side, and there being at least one piezoelectric actuator for changing a shape of at least one of said leading edge and said trailing edge.2. The stator vane as set forth in claim 1 , wherein at least one piezoelectric actuator is mounted on each of said suction and pressure sides claim 1 , with one of said piezoelectric actuators being controlled to contract and the other being controlled to expand to change the position of said leading edge relative to said trailing edge.3. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are mounted within pockets in said suction and pressure sides.4. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said leading edge about a virtual hinge axis while changing the position of the trailing edge to a lesser extent.5. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said trailing edge about a virtual hinge axis while changing the position of the leading edge to a lesser extent.6. The stator vane as set forth in claim 2 , wherein said airfoil is connected to inner and outer platforms.7. The stator vane as set forth in claim 6 , wherein there is an elastomeric material between said airfoil and said radially inner and outer platforms to accommodate movement of at least one of said leading and trailing edges.8. The stator vane as ...

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Номер записи: 69
07-01-2021 дата публикации

Systems and Methods for Controlling Liquid Flow to a Turbine Fogging Array

Номер: US20210003077A1
Автор: Ammons Mark, Scoggins Brian, Shepherd Donald W.
Принадлежит:

Methods and apparatus for controlling liquid flow to a turbine fogging array. Some implementations are generally directed toward adjusting the output of a variable output pump that supplies water to the turbine fogging array. In some of those implementations, the output is adjusted based on a determined target pump output value that is indicative of a pump output required to change the moisture content of intake air of a combustion turbine to meet a target humidity value. Some implementations are generally directed toward actuating at least one control valve of a plurality of control valves that control liquid throughput to one or more fogging nozzles of a fogging array. 1. A system for controlling output of a fogging array positioned upstream of a combustion turbine , the system comprising:one or more weather sensors measuring one or more conditions of intake air of the combustion turbine and providing weather sensor data responsive to the measurements, the weather sensor data enabling determination of relative humidity of the intake air;a variable output pump supplying liquid to a fogging array positioned upstream of the combustion turbine, the variable output pump operable at a plurality of speeds;memory storing instructions;a controller receiving the weather sensor data and coupled to a drive for the pump, the controller operable to execute the instructions stored in the memory; identify a target humidity value for the intake air;', 'determine, based on the weather sensor data and the target humidity value, a target pump output value indicative of a pump output required to change the moisture content of the intake air to meet the target humidity value; and', 'adjust the speed for the variable output pump based on the target pump output value., 'wherein the instructions comprise instructions to2. The system of claim 1 , further comprising:a temperature sensor measuring temperature of the liquid and generating temperature sensor data, the temperature sensor ...

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Номер записи: 70
07-01-2021 дата публикации

COMPACT AERO-THERMO MODEL BASED ENGINE POWER CONTROL

Номер: US20210003078A1
Автор: Case Thomas E., Donald Matthew, Karpman Boris, Meisner Richard P.
Принадлежит:

Systems and methods for controlling a fluid-based system are disclosed. The systems and methods may include generating a model output using a model processor, processing a model input vector and setting a model operating mode, and setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. Synthesized parameters are generated as a function of the dynamic states and the model input vector based on a series of utilities, where at least one of the utilities is a configurable utility including one or more sub-utilities. An estimated state of the model is determined based on at least one of a prior state and the synthesized parameters. An actuator associated with the control device is directed as a function of a model output, where the model output includes an estimated thrust value for the control device. 1. A control system , comprising:an actuator operable to adjust a control device; and process a model input vector and set a model operating mode;', 'set dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;', 'generate a plurality of synthesized parameters as a function of the dynamic states and the model input vector based on a series of utilities, wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities;', 'determine an estimated state of the model based on at least one of a prior state and the synthesized parameters; and', 'process at least the synthesized parameters of the model to determine the model output comprising an estimated thrust value for the control device., 'a computer processor configured to execute a control law to control the actuator as a function of a model output and generate the model output using a model processor, wherein the model processor comprises a plurality of executable instructions to2. The control system of claim 1 , wherein the control law compares the ...

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Номер записи: 71
03-01-2019 дата публикации

PROPULSION SYSTEM FOR AN AIRCRAFT

Номер: US20190003397A1
Автор: Gansler Michael Thomas, Hon Robert Charles
Принадлежит:

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine in a steady-state flight operating condition, the turbomachine rotating the propulsor when operated in the steady-state flight operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the steady-state flight operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine. 1. A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a propulsor , a turbomachine , and an electrical system , the electrical system comprising an electric machine coupled to the turbomachine , the method comprising:operating, by one or more computing devices, the turbomachine in a steady-state flight operating condition, the turbomachine rotating the propulsor when operated in the steady-state flight operating condition;receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the steady-state flight operating condition; andproviding, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.2. The method of claim 1 , further comprising:maintaining, by the one or more computing devices, a fuel flow to a combustion section of the turbomachine substantially constant for an initial time period in response to the received command to accelerate the ...

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Номер записи: 72
03-01-2019 дата публикации

GAS TURBINE ENGINE VARIABLE AREA FAN NOZZLE CONTROL

Номер: US20190003422A1
Автор: Blackwell Geoffrey T., McVey Wililam J., Tempelman William G.
Принадлежит:

A method of managing a gas turbine engine includes the steps of detecting an airspeed and detecting a fan speed. A parameter relationship is referenced related to a desired variable area fan nozzle position based upon at least airspeed and fan speed. The detected airspeed and detected fan speed is compared to the parameter relationship to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted in response to the determination of the target area fan nozzle position and at least one threshold. 1. A method of managing a gas turbine engine comprising the steps of:detecting an airspeed;detecting a fan speed;referencing a parameter relationship related to a desired variable area fan nozzle position based upon at least airspeed and fan speed, and comparing the detected airspeed and detected fan speed to the parameter relationship to determine a target variable area fan nozzle position; andadjusting an actual variable area fan nozzle position in response to the determination of the target area fan nozzle position and at least one threshold.2. The method according to claim 1 , wherein the fan speed detecting step includes detecting a low speed spool rotational speed claim 1 , and correcting the fan speed based upon an ambient temperature.3. The method according to claim 2 , wherein the fan speed detecting step includes calculating the fan speed based upon a gear reduction ratio.4. The method according to claim 1 , wherein the referencing and comparing steps include providing a target variable area fan nozzle position for a range of air speeds based upon the fan speed.5. The method according to claim 4 , wherein the air speed range is 0.35-0.55 Mach claim 4 , and the data table includes first and second thresholds corresponding to lower and upper fan speed limits claim 4 , the target variable area fan nozzle position selected based upon the first and second thresholds.6. The method according to claim 5 , wherein the upper ...

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Номер записи: 73
04-01-2018 дата публикации

Metering Valve

Номер: US20180005743A1
Автор: PLUCINSKI Wojciech
Принадлежит:

A metering valve comprising a solenoid having: a coil mounted on a core; and an armature moveable axially with respect to the core and against a return bias in response to a current in the coil; a variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core. The metering valve comprises an electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor. A reference capacitor may be provided having opposing third and fourth plates at a set separation. A valve body may house the solenoid, the variable capacitor and the reference capacitor. 1. A metering valve comprising: a coil mounted on a core; and', 'an armature moveable axially with respect to the core and against a return bias in response to a current in the coil;, 'a solenoid havinga variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core; andan electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor.2. The metering valve as claimed in claim 1 , further comprising:a reference capacitor having third and fourth plates at a set separation; anda valve body which houses the solenoid, the variable capacitor and the reference capacitor.3. The metering valve as claimed in claim 2 , further comprising a controller for controlling the current in the coil and the movement of the armature claim 2 , the controller being responsive to the feedback signal to adjust the current in the coil.4. The metering valve as claimed in claim 2 , wherein the electronic feedback loop is configured to:observe a ratio of the capacitances of the variable and reference capacitors; anduse the ratio of the capacitances to produce a feedback signal corresponding to a displacement of the armature.5. The metering valve ...

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Номер записи: 74
08-01-2015 дата публикации

POWER GENERATION APPARATUS, POWER GENERATION METHOD, DECOMPOSITION-GAS TURBINE AND DECOMPOSITION-GAS BOILER

Номер: US20150007568A1
Автор: Chaen Shigehiro, HABU Hiroto, Kawaguchi Junichiro, Sone Yoshitsugu
Принадлежит: SHOWA DENKO K.K.

A power generation apparatus, a power generation method, a decomposition-gas boiler, and a decomposition-gas turbine with which nitrous oxide may be used as an environmentally friendly energy source. A fuel gas including nitrous oxide (NO) is supplied to a decomposition reactor () in which a catalyst () for decomposing nitrous oxide is disposed. Steam is generated by a decomposition-gas boiler by heat recovery from decomposition gas (N, O) generated by decomposing the nitrous oxide, the steam generated by the decomposition-gas boiler is used to drive the rotation of a steam turbine to obtain motive power, and the motive power is subsequently used to drive a generator to obtain electrical power. Alternatively, the decomposition gas (N, O) generated by decomposing the nitrous oxide is used to drive the rotation of a decomposition-gas turbine to obtain motive power. 1. (canceled)2. (canceled)3. A power generation apparatus , comprising:a decomposition-gas boiler, generating steam by heat recovery from a decomposition gas produced by decomposition of nitrous oxide,a steam turbine, rotationally driven by the steam generated by the decomposition-gas boiler, andan electric generator, generating electric power by driving the steam turbine;ora decomposition-gas turbine, rotationally driven by decomposition gas produced by decomposition of nitrous oxide andan electric generator, generating electric power by driving the decomposition-gas turbine;wherein the decomposition-gas turbine or the decomposition-gas boiler comprise a decomposition reaction unit, in which a nitrous oxide decomposition catalyst for decomposition of the nitrous oxide is placed; anda fuel gas supply device, which supplies a fuel gas comprising nitrous oxide to the decomposition reaction unit, andin the decomposition reaction unit, after decomposition of the nitrous oxide contained in the fuel gas using the nitrous oxide decomposition catalyst, decomposition of a nitrous oxide contained in a fuel gas which ...

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Номер записи: 75
12-01-2017 дата публикации

CONTROL DEVICE AND CONTROL METHOD

Номер: US20170009606A1
Автор: Fujii Takashi, Koyama Yoshinori, MURAYAMA Masato, TAMURA Ken, TSUTSUMI Takanori
Принадлежит:

A control device for a power generation system whereby power is generated by a first power source that operates by burning a fuel. The control device identifies, on the basis of a pressure difference in a prior-stage mechanism that supplies the fuel to the first power source, a fuel capacity that compensates for the pressure difference in the prior-stage mechanism. The pressure difference is the difference between a pressure set for the fuel before a load change in the prior-stage mechanism and a pressure set for the fuel after the load change in the prior-stage mechanism. The control device calculates a fuel supply command value, which is a command value for adjusting the amount of fuel supplied to a fuel supply device that supplies the fuel to the first power source, and is output to the fuel supply device using a fuel supply acceleration command value. 1. A control device of a power generation system which generates power by a first power source which operates by burning a fuel ,wherein the control device identifies, on the basis of a pressure difference between a pressure of the fuel which is set before a load change in a prior-stage mechanism which supplies the fuel to the first power source and a pressure of the fuel which is set after the load change in the prior-stage mechanism, a volume of fuel which maintains the pressure of the fuel which is set after the load change, and the control device calculates a fuel supply command value which is a command value for adjusting the amount of the fuel supplied to a fuel supply device which supplies the fuel to the first power source, and is output to the fuel supply device using a fuel supply acceleration command value which accelerates adjustment of the identified volume of fuel.2. The control device of a power generation system according to claim 1 ,wherein the control device of a power generation system further includes a second power source in which an output response is slower than that of the first power source ...

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Номер записи: 76
12-01-2017 дата публикации

COMPRESSOR CONTROL DEVICE, COMPRESSOR CONTROL SYSTEM, AND COMPRESSOR CONTROL METHOD

Номер: US20170009664A1
Автор: Jahami Kazuhiro, Nakagawa Yosuke, YONEMURA Naoto
Принадлежит:

With regard to a load running system that comprises a plurality of compressors that compress a fuel gas and supply the compressed fuel gas to a load apparatus, this compressor control device comprises: a feedforward control signal generation unit that, on the basis of a value that is found by dividing the total load of the load apparatus by the number of running compressors, generates a first control signal that is for controlling the amount of fuel gas supplied by the compressors; and a control unit that, on the basis of the first control signal, controls the amount of fuel gas supplied by the compressors. 1. A load running system which includes a plurality of compressors which compress a fuel gas and supply the compressed fuel gas to a load apparatus ,wherein a compressor control device comprises:a feedforward control signal generation unit which generates a first control signal which controls an amount of the fuel gas supplied by the compressors, on the basis of a value which is obtained by dividing the total load of the load apparatus by the number of running compressors; anda control unit which controls the amount of the fuel gas supplied by the compressors, on the basis of the first control signal.2. The compressor control device according to claim 1 , further comprising:a feedback control signal generation unit which performs a feedback control, on the basis of a deviation between a target value and a measured value of a header pressure of the fuel gas, and generates a second control signal,wherein the control unit controls the supply amount of the fuel gas, on the basis of a value which is obtained by adding the second control signal to the first control signal.3. The compressor control device according to claim 2 ,wherein the feedback control signal generation unit generates a new second control signal which has a calculated value obtained by dividing the value of the generated second control signal by the number of running compressors as a value.4. The ...

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Номер записи: 77
14-01-2016 дата публикации

SHAFT STIFFNESS

Номер: US20160010494A1
Автор: ERLUND Mark Nicholas, Rowe Arthur Laurence
Принадлежит:

A method to determine shaft stiffness of a rotating shaft, the shaft coupling a turbine to drive the rotation and a load to be driven by the rotation. For a given operational temperature and rotational speed of the shaft, the method including steps to determine polar moments of inertia of the load and the turbine. Determine natural torsional vibration frequency of the shaft. Determine the shaft stiffness by calculation using the inertias and vibration frequency. 1. A method to determine shaft stiffness of a rotating shaft , the shaft coupling a turbine to drive the rotation and a load to be driven by the rotation; for a given operational temperature and rotational speed of the shaft , the method comprising steps to:determine polar moment of inertia of the load;determine polar moment of inertia of the turbine;determine natural torsional vibration frequency of the shaft; anddetermine the shaft stiffness by squaring the product of 2π and the natural torsional vibration frequency of the shaft and dividing the result by the sum of the inverse inertias.2. A method as claimed in wherein the load comprises a fan claim 1 , a compressor or a propeller.3. A method as claimed in further comprising a step to model inertia in terms of operating temperature and rotational speed of the shaft.4. A method as claimed in wherein the steps to determine the inertias comprise looking up the load inertia and the turbine inertia in the model.5. A method as claimed in further comprising steps to:measure axial distribution of the load and turbine;apply an axial factor to the load inertia and to the turbine inertia to accommodate axial distribution of inertia along the shaft; andexpress the shaft stiffness as an axial distribution along the shaft.6. A method as claimed in wherein the step of determining the natural torsional vibration frequency of the shaft comprises steps to:measure rotational speed of the shaft;perform a fast Fourier transform on the rotational speed to obtain its frequency ...

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Номер записи: 78
14-01-2016 дата публикации

METHOD FOR THE CONTROL AND PROTECTION OF A GAS TURBINE AND GAS TURBINE USING SUCH METHOD

Номер: US20160010495A1
Автор: Belzner Andreas, MUELLER Eric Andre
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for the control and protection of a gas turbine a gas turbine performance and lifetime indicative process quantity is estimated from a set of available process signals. The gas turbine performance and lifetime indicative process quantity is simultaneously evaluated by two different estimation methods, whereby a first estimation method has a high prediction accuracy, and a second estimation method has a high availability, a continuous adaptation of the second estimation method is conducted in order to align the output signals of the two estimation methods, and in case of a failure detected in the supervision of the first estimation method the adaptation of the second estimation method is stopped, and the output of the first estimation method is switched to the output of the second estimation method. 119111212151115121214141212111513161414121211151212. Method for the control and protection of a gas turbine () , whereby a gas turbine performance and lifetime indicative process quantity (IPQ) is estimated from a set of available process signals , characterized in that in order to circumvent the trade-off between estimation accuracy and availability said gas turbine performance and lifetime indicative process quantity is simultaneously evaluated by two different estimation methods ( , , ′ , ) , whereby the first estimation method ( , ) has a high prediction accuracy , and a second estimation method ( , ′) has a high availability , a continuous adaptation ( , ′) of said second estimation method ( , ′) is conducted in order to align the output signal (T , T′) of said second estimation method with the output signal (T , T) of said first estimation method , and in case a fault (F) in the evaluation of said first estimation method ( , ) is detected in the supervision ( , ) , said adaptation ( , ′) of said second estimation method ( , ′) is stopped , and the output of said first estimation method ( , ) is switched to the output of said second estimation method ( , ...

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Номер записи: 79
14-01-2016 дата публикации

GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO

Номер: US20160010565A9
Автор: Kohlenberg Gregory A., Schwarz Frederick M., Zamora Sean P.
Принадлежит:

A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. 1. A gas turbine engine comprising:a core nacelle defined about an engine centerline axis;a core engine at least partially disposed within the core nacelle;a fan section with twenty (20) or less fan blades;a gear system driven by the core engine to drive said fan section;a fan nacelle mounted at least partially around said fan section and said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan bypass airflow having a fan pressure ratio of the fan bypass airflow during engine operation, said fan pressure ratio less than about 1.45;a variable fan nozzle axially movable relative to the fan nacelle, the variable fan nozzle including at least two sectors; anda controller for independently adjusting each of the at least two sectors.2. (canceled)3. The engine as recited in claim 1 , wherein the controller is operable to reduce said fan nozzle exit area at a cruise flight condition.4. The engine as recited in claim 1 , wherein said controller is operable to control said fan nozzle exit area to reduce a fan instability.5. The engine as recited in claim 1 , wherein said fan variable area nozzle defines a trailing edge of said fan nacelle.6. The engine as recited in claim 1 , wherein said fan variable area nozzle is axially movable relative to said fan nacelle.7. (canceled)8. The engine as recited in claim 1 , wherein said fan section defines a corrected fan tip speed less than about 1150 ft/second.9. The engine as recited in claim 1 , wherein said core engine includes a low pressure turbine which defines a low pressure turbine pressure ratio that is greater than about five (5).10. The engine as recited in claim 7 , wherein said core engine includes a low pressure turbine which defines a low pressure turbine pressure ratio that is greater than five (5).11. The engine as recited in claim 1 , further comprising a gear system ...

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Номер записи: 80
14-01-2016 дата публикации

METHOD FOR OPERATING A GAS TURBINE BELOW ITS RATED POWER

Номер: US20160010566A1
Автор: Böttcher Andreas, Deuker Eberhard, Kluge Andre, Kreutzer Philipp, Link Marco, Sternemann Ansgar, Tertilt Marc, Wilke Martin
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A method for operating a gas turbine below its rated power, in which CO emissions in the exhaust gas of the gas turbine increase with a reduction of the output gas turbine power, wherein, if a predefined threshold value, which can be selected as desired, for the CO emissions is reached or if a predefined threshold value, specified in relative or absolute terms, for the output gas turbine power is undershot, the combustion temperature in the combustion chamber of the gas turbine is increased. To operate the gas turbine with low emissions, for a constant power output, the exhaust-gas temperature increase generated at the outlet of the gas turbine as a result of the combustion temperature increase is at least partially compensated through the addition of a liquid or vaporous medium. 16.-. (canceled)7. A method for operating a gas turbine below its rated power ,wherein CO emissions in the exhaust gas of the gas turbine increase with a reduction of the output gas turbine power, the method comprising:if a predefined threshold value for the CO emissions is reached or if a predefined threshold value for the output gas turbine power is undershot, increasing the combustion temperature in the combustion chamber of the gas turbine,wherein the exhaust-gas temperature increase generated at the exhaust-gas outlet of the gas turbine as a result of the combustion temperature increase is at least partially compensated through the addition of a medium which is liquid or vaporous, andsupplying the medium to the exhaust gas downstream of the final turbine stage of the gas turbine.8. The method as claimed in claim 7 ,wherein, without a change in load, the combustion temperature is raised, and the added flow rate of medium selected, such that the exhaust-gas temperature that prevails after the addition of the medium is approximately equal to or slightly higher than the exhaust-gas temperature that arises at the same location in the case of rated power.9. The method as claimed in claim 7 , ...

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Номер записи: 81
14-01-2016 дата публикации

FUEL-AIR RATIO CONTROL OF GAS TURBINE ENGINES

Номер: US20160010567A1
Автор: Cline Curtis H., JR. Russell E., Phillips Steven D., Skertic Richard J., White
Принадлежит:

A turbine engine includes a fan connected to a fan shaft, a combustion chamber, and an electric motor/generator in communication with the fan shaft. A controller is configured to direct power into the electric motor/generator during engine accelerations from steady state such that air flow to the combustion chamber is increased. The controller is further configured to direct power out of the electric motor/generator during engine decelerations from steady state such that air flow to the combustion chamber is decreased. 1. A turbine engine comprising:a fan connected to a fan shaft;a combustion chamber;an electric motor/generator in communication with said fan shaft;a controller configured to direct power into said electric motor/generator during engine accelerations from steady state such that air flow to said combustion chamber is increased; andsaid controller configured to direct power out of said electric motor/generator during engine decelerations from steady state such that air flow to said combustion chamber is decreased.2. A turbine engine as described in claim 1 , wherein said controller is further configured to:increase fuel flow to said combustion chamber during engine accelerations from steady state; anddecrease fuel flow to said combustion chamber during engine decelerations from steady state;wherein power is directed into said electric motor/generator prior to increasing fuel flow during engine accelerations from steady state; andwhere fuel flow is decreased to said combustion chamber prior to directing power out of said electric motor/generator during engine decelerations.3. A turbine engine as described in claim 1 ,wherein said controller comprises a closed-loop control system wherein a speed demand signal is continually compared to a speed actual signal to calculate a power demand signal; andwherein said power demand signal is utilized to control the supply of power to said electric motor/generator during engine accelerations from steady state; ...

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Номер записи: 82
11-01-2018 дата публикации

Apparatus and process for converting an aero gas turbine engine into an industrial gas turbine engine for electric power production

Номер: US20180010476A1
Автор: Brostmeyer Joseph D., Jones Russell B.
Принадлежит:

An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine. 18-. (canceled)9: An industrial gas turbine engine converted from a twin spool turbofan aero gas turbine engine comprising:a low spool with a first low pressure turbine directly connected at one end and an electric generator connected at an opposite end, wherein the opposite end is a forward end of the industrial gas turbine engine and a first low pressure compressor removed from the low spool shaft;a high spool shaft rotatable over the low spool shaft with a high pressure compressor connected to a high pressure turbine;a combustor connected between the high pressure compressor and the high pressure turbine;a second low pressure turbine located downstream from the first low pressure turbine such that hot gas exhaust from the first low pressure turbine drives the second low pressure turbine with the low pressure compressor driven by the second low pressure turbine;a second low pressure compressor driven by the second low pressure turbine; and,a row of variable guide vanes located between the first low pressure turbine and the second low pressure turbine;wherein the second low pressure turbine is located at an aft end of the industrial gas turbine engine and air flows from the second low pressure compressor to the high pressure compressor at the forward end of the ...

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Номер записи: 83
11-01-2018 дата публикации

TURBINE ARRANGEMENT

Номер: US20180010479A1
Автор: Brown David E., Mason John R.
Принадлежит: ROLLS-ROYCE PLC

A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed. 1. A turbine arrangement for a gas turbine engine comprising:a turbine shaft;an axial array of turbine rotors, having a first axial end defined by a first of the turbine rotors and having a second axial end;a drive arm coupled between the turbine shaft and the first axial end; anda measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end.2. The turbine arrangement as claimed in claim 1 , wherein each turbine rotor is mounted to a disc claim 1 , the drive arm coupled to the disc of the first of the turbine rotors.3. The turbine arrangement as claimed in claim 1 , wherein the array comprises at least two turbine rotors.4. The turbine arrangement as claimed in claim 1 , wherein the array comprises at least three turbine rotors.5. The turbine arrangement as claimed in claim 1 , further comprising an interstage spacer between each adjacent pair of turbine rotors claim 1 , each spacer arranged to transmit drive.6. The turbine arrangement as claimed in claim 1 , wherein the measurement system comprises a phonic wheel and a magnetic inductance speed sensor.7. A gas turbine engine comprising the turbine arrangement as claimed in .8. The gas turbine engine as claimed in claim 7 , further comprising a controller configured to compare the measured parameter to a comparison parameter and to implement mitigation action if the measured parameter exceeds the comparison parameter.9. The gas turbine engine as claimed in claim 8 , wherein the mitigation action is any one or more of: reduce fuel flow to the ...

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Номер записи: 84
11-01-2018 дата публикации

Constant-volume combuston module for a turbine engine, comprising communication-based ignition

Номер: US20180010517A1
Автор: Matthieu Leyko
Принадлежит: Safran SA

The invention relates to a turbine engine combustion module ( 10 ), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers ( 12 A, 12 B) arranged about an axis, each chamber ( 12 A, 12 B, 12 C) comprising a compressed gas intake port ( 16 ) and a burnt gas exhaust port ( 18 ); and an ignition means that triggers combustion in the combustion chambers ( 12 A, 12 B, 12 C). The module ( 10 ) comprises at least one duct ( 80 ) which establishes a communication between a first combustion chamber ( 12 A) and at least one second combustion chamber ( 12 B) in order to inject burnt gases from the first combustion chamber ( 12 A) into the second combustion chamber ( 12 B) so as to trigger combustion in the second combustion chamber ( 12 B).

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Номер записи: 85
11-01-2018 дата публикации

Plant control apparatus, plant control method and power plant

Номер: US20180010526A1
Автор: Kazuna SAWATA, Masayuki Tobo, Takahiro Mori
Принадлежит: Toshiba Corp

In one embodiment, a plant includes a combustor to burn fuel with oxygen from an inlet guide vane (IGV) to generate a gas for a gas turbine (GT), and a heat recovery steam generator to use an exhaust gas from GT to generate steam for a steam turbine (ST). An apparatus controls an IGV opening degree to a first degree and a GT output value to a value larger than a first value between GT start and ST start. The first value is an output value at which exhaust gas temperature can be kept at a first temperature that depends on ST metal temperature, when the IGV opening degree is the first degree. The apparatus increases the IGV opening degree from the first degree based on steam temperature or the GT output value, while the GT output value is controlled to the value larger than the first value.

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Номер записи: 86
11-01-2018 дата публикации

SYSTEM OF OPERATING A GAS TURBINE ENGINE

Номер: US20180010527A1
Автор: ROWE Arthur L.
Принадлежит: ROLLS-ROYCE PLC

A system for operating a gas turbine engine to mitigate the risk of ice formation within the engine, the system including a controller arranged to control at least one operational parameter of the engine such that the engine operates in a safe zone; and, a processor configured to function as a determining module to make a comparison between values and determine whether the engine is operating within a safe zone based on at least a core pressure parameter relating to the pressure within the engine and a core temperature parameter relating to the temperature within the engine, wherein the safe zone is defined by the product (multiplied) of the core pressure parameter and core temperature parameter being above a safe threshold. 1. A system for operating a gas turbine engine to mitigate the risk of ice formation within the gas turbine engine , the system comprising:a controller configured to control at least one operational parameter of the gas turbine engine such that the gas turbine engine operates in a safe zone; and,a processor configured to function as a determining module to make a comparison between values and determine whether the gas turbine engine is operating within the safe zone based on at least a core pressure parameter relating to the pressure within the gas turbine engine and a core temperature parameter relating to the temperature within the gas turbine engine,wherein the safe zone is defined by the product (multiplied) of the core pressure parameter and core temperature parameter being above a safe threshold.2. A system for operating a gas turbine engine according to claim 1 , wherein the core pressure parameter relates to the static pressure within the gas turbine engine.3. A system for operating a gas turbine engine according to claim 1 , wherein the core temperature parameter relates to the stagnation temperature within the gas turbine engine.4. A system for operating a gas turbine engine according to claim 1 , wherein the core pressure parameter is ...

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Номер записи: 87
11-01-2018 дата публикации

METHOD OF CONTROLLING A GAS TURBINE ASSEMBLY

Номер: US20180010528A1
Автор: BOLAÑOS-CHAVERRI Felipe, MARCHIONE Teresa Ernesto, Meeuwissen Thiemo
Принадлежит: ANSALDO ENERGIA IP UK LIMITED

A method for controlling a gas turbine assembly includes: a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor, in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses, and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from the first combustor occurs; an intermediate turbine in which a partial expansion of the hot gasses arriving from the first combustor occurs; and a second combustor in which combustion of a mixture of fuel and hot gasses arriving from the intermediate turbine occurs; the method further includes, on a start-up transient operating phase of the gas turbine assembly, the step of controlling the fuel mass flow-rate supplied to the first and/or the second combustor on the basis of the flame temperature inside the first combustor. 1. A method for controlling a gas turbine assembly having a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor , in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses , and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from said first combustor occurs;the method being characterized by comprising:on a start-up transient operating phase of the gas turbine assembly, controlling a fuel mass flow-rate supplied to said first combustor on the basis of the a flame temperature (TFL1) inside said first combustor.2. Method according to claim 1 , wherein the fuel mass flow-rate supplied to said first combustor is controlled according to a predetermined TFL1 schedule.3. Method according to claim 2 , wherein said TFL1 ...

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Номер записи: 88
14-01-2021 дата публикации

Modulating fuel for a turbine engine

Номер: US20210010429A1
Автор: David Justin Brady
Принадлежит: General Electric Co

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA). The fuel supply system can include a fuel line that fluidly connects a fuel tank and the turbine engine. A fuel pump and a fuel metering valve can be fluidly connected to the fuel line. A bypass line can fluidly connect to the fuel line. Flow through the bypass line can be controlled using a bypass valve and a balancing pressure valve. The TCMA can then modulate the fuel flow using the valves.

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Номер записи: 89
14-01-2021 дата публикации

FEEDFORWARD CONTROL OF A FUEL SUPPLY CIRCUIT OF A TURBOMACHINE

Номер: US20210010430A1
Автор: De Wergifosse Huguette, Pora Loïc Michel Pierre
Принадлежит: SAFRAN AIRCRAFT ENGINES

A fuel supply system for a turbomachine, comprising a fuel circuit comprising pressurizer at the output of the circuit, a pump arranged to send into the circuit a fuel flow rate which is an increasing function of the rotational speed of a shaft of the pump, and a control circuit arranged to control the device to comply with a flow rate setpoint at the output of the fuel circuit. The system further comprises a feedforward corrector circuit configured to calculate an increment of the flow rate setpoint as a function of the engine speed of the turbomachine and of a variation in the engine speed of the turbomachine, and to add this increment to the flow rate setpoint. A method of regulating the pump is also described.

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Номер записи: 90
11-01-2018 дата публикации

Pressure balanced thermal actuator

Номер: US20180011501A1
Автор: Brian L. Goeller, James M. Leithauser, Patrick B. Reed
Принадлежит: Senior IP GmbH

A pressure balanced thermal actuator includes a flow housing having an inlet and an outlet, with the flow housing being affixed at opposing ends to two bellows housings, each of which contains a bellows. An actuation rod is operably coupled to each bellows and contains a fluid passage therewithin. When the temperature of the area surrounding the actuator increases, the pressure inside the bellows housings increases, and exerts a force on the bellows therein, compressing it. As a result, the actuation rod moves from a first position to a second position to align the fluid passage with the inlet and the outlet, enabling the controlled passage of a first fluid from the inlet, and through the fluid passage, to the outlet, to reduce the temperature of the area surrounding the valve assembly. The actuator is unaffected by changes in the ambient pressure, by working equally on two opposing bellows areas.

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Номер записи: 91
09-01-2020 дата публикации

APPARATUS FOR GAS TURBINE ENGINES

Номер: US20200011250A1
Автор: MAGUIRE Alan R., STRETTON Richard G.
Принадлежит: ROLLS-ROYCE PLC

Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box. 1. Apparatus for a gas turbine engine , the apparatus comprising;a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing;a plurality of guide vanes extending radially from the outer wall of the core engine casing;to a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; andan accessory gear box positioned within the second cavity of he torque box.2. Apparatus as claimed in claim 1 , wherein the torque box wholly overlaps axially with the plurality of guide vanes.3. Apparatus as claimed in claim 1 , wherein each of the plurality of guide vanes includes a root portion having a leading edge at a first axial position and a trailing edge at a second axial position claim 1 , the torque box comprising a first wall located at the first axial position and a second wall located at the second axial position.4. Apparatus as claimed in claim 1 , ...

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Номер записи: 92
10-01-2019 дата публикации

SYSTEM AND METHOD FOR A STOICHIOMETRIC EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEM

Номер: US20190013756A1
Автор: Huntington Richard A., Minto Karl Dean, Thatcher Jonathan Carl, Vorel Aaron Lavene, Xu Bin
Принадлежит:

A system includes a control system configured to control one or more parameters of an exhaust gas recirculation (EGR) gas turbine system to control a portion of electrical power for export from a generator driven by the turbine to an electrical grid. The control system includes a closed-loop controller configured to control parameters of the EGR gas turbine system and an open-loop controller configured to temporarily control the parameters of the EGR gas turbine system to increase the portion of the electrical power exported to the electrical grid to provide a Primary Frequency Response (PFR) in response to a transient event associated with the electrical power. The open-loop controller is configured to provide control signals to increase a concentration of an oxidant in a combustor to provide the PFR in response to the transient event when the EGR gas turbine system is operating in an emissions compliant mode. 1. A system , comprising: a combustor configured to receive and combust a fuel with an oxidant; and', 'a turbine driven by combustion products from the combustor;, 'an exhaust gas recirculation (EGR) gas turbine system, comprisinga generator driven by the turbine, wherein the generator is configured to generate electrical power and to export a portion of the electrical power to an electrical grid; and a closed-loop controller configured to control one or more parameters of the EGR gas turbine system; and', provide control signals to increase a flow rate of fuel to the combustor to provide the PFR in response to the transient event when the EGR gas turbine system is operating in a non-emissions compliant mode; and', 'provide control signals to increase a concentration of the oxidant in the combustor, or decrease a local consumption of the electrical power, or both, to provide the PFR in response to the transient event when the EGR gas turbine system is operating in an emissions compliant mode., 'an open-loop controller configured to temporarily control the one ...

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Номер записи: 93
03-02-2022 дата публикации

HYBRID GAS TURBINE ENGINE SYSTEM POWERED WARM-UP

Номер: US20220034262A1
Автор: Terwilliger Neil, Virtue John P.
Принадлежит:

An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state. 1. A hybrid gas turbine engine system of a hybrid electric aircraft , the hybrid gas turbine engine system comprising:a gas turbine engine comprising a low speed spool and a high speed spool;a generator operably coupled to the low speed spool of the gas turbine engine;a high spool electric motor operably coupled to the high speed spool; and monitor for a powered warm-up request;', 'initiate a powered warm-up state of the gas turbine engine based on detecting the powered warm-up request;', 'control the hybrid gas turbine engine system in the powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust; and', 'transition the gas turbine engine from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state., 'a controller configured to2. The hybrid gas turbine engine system of claim 1 , comprising one or more electric ...

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Номер записи: 94
19-01-2017 дата публикации

GAS TURBINE ENGINE FUEL SCHEDULING

Номер: US20170016401A1
Автор: STOCKWELL Mark Thomas
Принадлежит: ROLLS-ROYCE PLC

A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool, a high pressure spool and a fuel metering valve is disclosed. The method comprises scheduling the fuel metering valve in dependence upon the speed of the high pressure spool. 1. A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool , a high pressure spool and a fuel metering valve , the method comprising scheduling the fuel metering valve in dependence upon the speed of the high pressure spool.2. The method according to further comprising scheduling the fuel metering valve to an over-fuelling position with respect to a fuel flow necessary for ignition of the engine prior to an attempted ignition during an engine in-flight windmill start procedure.3. The method according to where the scheduling of the fuel metering valve to an over-fuelling position is employed following a failed ignition attempt during the in-flight engine windmill start procedure.4. The method according to where the position of the fuel metering valve is scheduled such that the degree of over-fuelling corresponding thereto is increased over time.5. The method according to where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration.6. The method according to where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration from ignition.7. The method according to where the scheduling in dependence upon the speed of the high pressure spool is employed during engine acceleration from ignition occurring during an in-flight engine windmill start procedure.8. The method according to where the scheduling of the fuel metering valve in dependence upon the speed of the high pressure spool is more specifically in dependence upon the rate of change of the high pressure spool speed.9. The method in accordance with where scheduling of the fuel metering ...

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Номер записи: 95
21-01-2016 дата публикации

EXPANDING SHELL FLOW CONTROL DEVICE

Номер: US20160017815A1
Автор: Izquierdo Felix, McAlice Timothy J.
Принадлежит:

A gas turbine engine includes a bypass flowpath between an outer engine case structure and a core engine. The bypass flow exits the engine through a nozzle. A flow control device that can expand or contract is arranged around the nozzle to control the bypass flow and includes a plurality of overlapping arcuate segments. A method of controlling a bypass flow includes providing a flow control device with overlapping segments that defines a bypass flow path, and actuating the segments to change the amount of overlap between segments and therefore the size of the bypass flow path.

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Номер записи: 96
21-01-2016 дата публикации

Fuel Cutoff Testing System

Номер: US20160017816A1
Автор: McDonald Darren Gordon, Welsh Bryan Douglas
Принадлежит:

A method and apparatus for controlling operation of an engine in an aircraft. A time when a cutoff speed for the aircraft will be reached at which a flow of fuel is to be stopped is identified. A delay between sending a command to move a switch to an off position and the time at which the engine ceases operation is also identified. The command is sent based on the predicted time and the delay. The command causes the switch to move to the off position moving a fuel control switch for the engine of the aircraft to a shut off position to stop the flow of fuel to the engine.

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Номер записи: 97
21-01-2016 дата публикации

METERING DEVICE FOR A FUEL FEED CIRCUIT OF AN ENGINE

Номер: US20160017817A1
Автор: Benezech Philippe Jean, Langford Stephen, Marie, Rene, SAMSON Rafael, SICAIRE Pierre
Принадлежит: TURBOMECA

A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position. 1. A metering device for an engine fuel feed circuit , the device comprising:a metering valve; anda pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve; a seat provided with an inlet orifice and an outlet orifice;', 'a shutter arranged within the seat; and', 'an actuator controlling the position of the shutter; and, 'wherein the metering valve compriseswherein, between the inlet orifice and the outlet orifice, the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position;{'b': '2', 'wherein the shutter is configured in such a manner that, firstly, the minimum section of said passage, and thus the flow rate of fuel passing through the valve, increases linearly as a function of the position coordinate of the shutter between the bottom abutment (b) and the threshold position, and that, secondly, the minimum section of said passage, and thus of the fuel flow rate, increases quadratically or more rapidly, as a function of the position coordinate of the shutter between the threshold position and the top abutment.'}2. A metering device according to claim 1 , wherein the ...

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Номер записи: 98
21-01-2016 дата публикации

METHOD OF OPERATING A GAS TURBINE WITH STAGED AND/OR SEQUENTIAL COMBUSTION

Номер: US20160018111A1
Автор: BERNERO Stefano, Eroglu Adnan, Geng Weiqun, Therkorn Dirk, Zhang Mengbin
Принадлежит:

The invention concerns a method of operating a gas turbine with staged and/or sequential combustion. The burners of a second stage or a second combustor are singularly and sequentially switched on during loading and switched off during de-loading. The total fuel mass flow and the compressor inlet guide vanes are adjusted at the same time to allow controlling gas turbine operation temperatures and engine power with respect to the required CO emission target.

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Номер записи: 99
18-01-2018 дата публикации

STATE DETERMINING DEVICE, OPERATION CONTROLLING DEVICE, GAS TURBINE, AND STATE DETERMINING METHOD

Номер: US20180016983A1
Автор: Nakamura Sosuke, SONODA Takashi, TAKENAKA Ryuji
Принадлежит: Mitsubishi Hitachi Power Systems, Ltd.

A state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas. 1. A state determining device that determines a state of a gas turbine connected to an electric generator , the gas turbine comprising a compressor that compresses intake air into compression air , a fuel supply device that supplies fuel , a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas , and a turbine that is rotated with the generated combustion gas , the state determining device comprising:an instruction-value detecting unit that detects a difference in an instruction value related to an output of the gas turbine;an output detecting unit that detects a difference in an output of the electric generator; anda determining unit that determines an operation of the gas turbine has departed from a predetermined relation when a difference between the difference in the instruction value and the difference in the output is equal to or larger than a threshold.2. The state determining device according to claim 1 , wherein the instruction value is a fuel-flow instruction value of fuel to be supplied from the fuel supply device to the combustor.3. The state determining device according to claim 1 , whereinthe instruction-value detecting unit detects a difference between a detected instruction value and an instruction value detected at a last time, andthe output detecting unit detects a difference between a detected output and an output detected at a last time.4. An operation ...

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Номер записи: 100