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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 3536. Отображено 100.
26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1
Автор: Brian Patrick Hansen, Christopher Edward LaMaster, David August Snider, Timothy Edward DeJoris
Принадлежит: General Electric Co

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

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Номер записи: 1
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: 2
21-03-2013 дата публикации

CONTROL SYSTEM FOR GAS TURBINE IN MATERIAL TREATMENT UNIT

Номер: US20130067929A1
Автор: Carin Christianne, Fedkenheuer Alvin W., Gorbell Brian N., Jonasson John S., Starosud Alexander
Принадлежит: EarthRenew, Inc.

This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine. 1. A material treatment apparatus comprising:a gas turbine having combustion air and fuel inlets;a dryer vessel connected to and adapted for receiving exhaust gases from the gas turbine and adapted for receiving material for treatment in the dryer vessel with heat from the exhaust gases;a temperature sensor for detecting the temperature at a desired location in the dryer vessel; anda controller responsive to the temperature sensor for controlling the combustion air flow or the fuel flow to the turbine.2. The apparatus according to wherein the gas turbine comprises a gas turbine generator.3. The apparatus according to further comprising a moisture sensor adapted for sensing at a desired location the moisture content of the heat treated material and wherein the controller is also responsive to the moisture sensor.4. The apparatus according to wherein the controller is responsive to the temperature sensor without regard to electrical output of the generator.5. The apparatus according to wherein the controller is primarily responsive to the temperature sensor and secondarily responsive to the electrical output of the generator.6. The apparatus ...

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Номер записи: 3
28-03-2013 дата публикации

METHOD OF ESTIMATING THE MAXIMUM POWER GENERATION CAPACITY AND FOR CONTROLLING A SPECIFIED POWER RESERVE OF A SINGLE CYCLE OR COMBINED CYCLE GAS TURBINE POWER PLANT, AND A POWER GENERATING SYSTEM FOR USE WITH SAID METHOD

Номер: US20130074513A1
Автор: MUELLER Eric Andre
Принадлежит: ALSTOM Technology Ltd

An estimation unit can estimate, on a real-time basis, a maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. For example, the actual power output and the maximum power generation capacity can be calculated relying on a mathematical process model. Subsequently, the calculated actual power output can be compared with the measured power output yielding a model-estimation error. Based on the model-estimation error, a correction signal can be deduced, to correct the calculated maximum power generation capacity. A controller can maintain a specified power reserve. The controller can use an estimate of the maximum power generation capacity as a reference, subtract a load offset, and apply the resulting signal as upper limit of the load set-point. 1. A method for controlling a specified power reserve of a gas turbine power plant having an input means which generates a load set-point signal for the gas turbine power plant and a controller which receives the load set-point signal and regulates a power output of the gas turbine power plant , the method comprising:continuously updating an estimate of the maximum power generation capacity of the gas turbine power plant;calculating a load offset by specifying a power reserve and determining the load offset from the specified power reserve;calculating a load limit as a difference of the estimate of the maximum power generation capacity and the load offset; andapplying the load limit as an upper limit of the load set-point signal to obtain a limited load set-point signal.2. A method according to claim 1 , wherein the estimate of the maximum power generation capacity is calculated by:calculating an actual power output and a maximum power generation capacity of the gas turbine power plant based on a mathematical model of the gas turbine power plant;measuring the actual power output of the gas turbine power plant;comparing the calculated actual power output and the measured power output to ...

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Номер записи: 4
25-04-2013 дата публикации

Method for heating a catalytic converter in an engine system and for diagnosing the effectiveness of measures for heating the catalytic converter

Номер: US20130097999A1
Автор: Damien Bouvier, Joerg Linke
Принадлежит: ROBERT BOSCH GMBH

A method for operating an internal combustion engine in a catalytic converter heating operation, the internal combustion engine being able to be operated in a normal operation, including the following steps: ascertaining a first exhaust gas temperature reading, which gives the exhaust gas temperature of the exhaust gas in a first catalytic converter, particularly in an oxidation catalytic converter; operating the internal combustion engine in a first operating mode, in which, in contrast to the normal operation, the exhaust gas, having an increased exhaust gas temperature, is exhausted from at least one cylinder of the internal combustion engine, as long as the first exhaust gas temperature reading has not reached a specified first temperature threshold value. This method enables a robust and simple diagnosis of the effectiveness of the catalytic converter heating operation according to the requirements of CARE Title 13 CCR Section 1968.2 Chapter.

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Номер записи: 5
16-05-2013 дата публикации

Twin-Shaft Gas Turbine

Номер: US20130118146A1
Автор: KUROKI Hidetoshi, MURATA Hidetaro, NANATAKI Kenji
Принадлежит:

A twin-shaft gas turbine can be used for 50 and 60 Hz power generation without using a reducer. A gas generator includes a compressor that generates compressed air, a burner that burns a fuel mixed with the compressed air received from the compressor so as to generate combustion gas, and a high-pressure turbine that is rotationally driven by the combustion gas received from the burner and generates driving force for the compressor. An output turbine includes a low-pressure turbine that is driven by exhaust gas received from the high-pressure turbine and a power generator that is driven by the low-pressure turbine. A control device reduces opening degree of IGV of the compressor and thereby reduces power of the compressor, and the rotational frequency of the gas generator is increased in a full-speed no-load operating state of the power generator. 1. A twin-shaft gas turbine comprising:a gas generator that includes a compressor that generates compressed air, a burner that burns a fuel mixed with the compressed air received from the compressor to generate combustion gas, and a high-pressure turbine that is rotationally driven by the combustion gas received from the burner and generates driving force for the compressor;an output turbine that includes a low-pressure turbine that is driven by exhaust gas received from the high-pressure turbine and a power generator that is driven by the low-pressure turbine; anda control device adapted for, during full-speed no-load operation of the power generator, increasing the rotational frequency of the gas generator in association with the rotational frequency of the low-pressure turbine.2. The twin-shaft gas turbine according to claim 1 ,wherein the control device increases the rotational frequency of the gas generator during full-speed no-load operation of the power generator by reducing power of the compressor.3. The twin-shaft gas turbine according to claim 1 ,wherein the control device increases the rotational frequency of the ...

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Номер записи: 6
13-06-2013 дата публикации

Method of operating a combined cycle power plant

Номер: US20130145772A1
Автор: Hamid Olia, Jan Schlesier, Martin Liebau, Martin Schoenenberger
Принадлежит: Alstom Technology AG

A method is provided for operating a combined cycle power plant. Flue gas of a gas turbine is used for producing steam for a steam turbine. A reliable and flexible black start network restoration is achieved by: a) in island mode, supplying internal consumers by the gas turbine, the operating point of which is selected so that a minimum steam temperature is achieved; b) in island mode, the steam turbine is synchronized and ramped up to an operating point where a maximum power increase is achieved, the resulting steam turbine load change is compensated by the gas turbine; c) consumer loads are connected blockwise; d) the increase in the demanded load being provided by the steam turbine; e) the load of the steam turbine is gradually reduced increasing its load-increasing capacity; and steps c)-e) are repeated until the power plant's base load is achieved.

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Номер записи: 7
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: 8
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: 9
25-07-2013 дата публикации

GAS TURBINE ENGINE CONTROL

Номер: US20130191004A1
Автор: BACIC Marko, BEECROFT Peter, LEWIS Leo Vivian
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine control apparatus comprises a controller a memory associated with the controller and inputs for measurement data from an engine. The controller determines the start of a monitoring cycle at receives measurement data at the inputs during the monitoring cycle, manipulates the measurement data to provide an incremental deterioration value representing deterioration occurring within the engine and during the monitoring cycle, and uses the incremental deterioration value at to update a deterioration value stored in the memory and determines the start of a further monitoring cycle. 2. Apparatus according to claim 1 , wherein the deterioration value represents deterioration relating to tip clearance of a rotating blade.3. Apparatus according to claim 2 , wherein the rotating blade is a turbine blade.4. Apparatus according to claim 1 , wherein the controller is further operable to retrieve from memory the deterioration value in the memory at the start of the monitoring cycle claim 1 , and to provide the retrieved deterioration value to a further control system for use during the monitoring cycle for providing compensation for the deterioration represented by the retrieved deterioration value.5. Apparatus according to claim 1 , wherein the controller receives measurement data relating to a plurality of parameters.6. Apparatus according to claim 1 , wherein the controller is operable to manipulate data relating to each of a plurality of factors relating to deterioration claim 1 , to provide a factor value relating to each factor claim 1 , the factor values being combined to provide the incremental deterioration value.7. Apparatus according to claim 6 , wherein the factors relate to tip clearance of a rotating blade and include at least one of the following factors:oxidation of a seal segment relative to which the blade rotates;blade creep of the rotating blade; andrubbing of a seal segment by the tip of the blade.8. Apparatus according to claim 6 , ...

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Номер записи: 10
08-08-2013 дата публикации

COMBUSTOR HEAD ARRANGEMENT

Номер: US20130199194A1
Автор: Carlisle Michael Lawrence
Принадлежит: ROLLS-ROYCE PLC

A combustor head arrangement including a heatshield including an aperture therethrough. A meter panel having a cold side and a hot side, an aperture and a slot. At least one of the meter panel and the heatshield has a retaining feature on the cold side; one of the meter panel and the heatshield has an anti-rotation feature. The arrangement includes a burner seal sized to fit through the aperture in the meter panel from the hot side towards the cold side. The burner seal has a tang configured to pass through the slot when the burner seal is in a first orientation and to be retained by the retaining feature and the anti-rotation feature when the burner seal is rotated to a second orientation. Also a method of assembling the combustor head. 132-. (canceled)33. A combustor head arrangement , the arrangement comprising:a meter panel having a cold side and a hot side, the meter panel having an aperture and a slot each extending through the meter panel between the hot and cold sides;a heatshield comprising an aperture therethrough;at least one of the meter panel and the heatshield comprising a retaining feature on the cold side;one of the meter panel and the heatshield comprising an anti-rotation feature; anda burner seal sized to fit through the aperture in the meter panel from the hot side towards the cold side and rotatable between a first orientation and a second orientation, the burner seal comprising a tang configured to pass through the slot when the burner seal is in the first orientation and to be retained by the retaining feature and the anti-rotation feature when the burner seal is in the second orientation.34. A combustor head arrangement as claimed in wherein there is more than one tang spaced around the burner seal.35. A combustor head arrangement as claimed in wherein the tangs are equally spaced around the burner seal.36. A combustor head arrangement as claimed in wherein the anti-rotation feature comprises a pair of members that circumferentially abut the ...

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Номер записи: 11
08-08-2013 дата публикации

DEVICE AND A METHOD FOR REGULATING A TURBINE ENGINE, AND AN AIRCRAFT

Номер: US20130199197A1
Автор: Beaud Southdary, Martin Laurent
Принадлежит: EUROCOPTER

A regulator device () for reducing the risk of surging in a turbine engine () that includes a gas generator (), air extraction means (), and mechanical power take-off means (). An engine computer () includes storage means () that store a plurality of acceleration regulation relationships, each acceleration regulation relationship corresponding to air extraction in a first range, and to mechanical power take-off in a second range, said regulator device () including first measurement means () for measuring current air extraction, and second measurement means () for measuring current mechanical power take-off, said engine computer () controlling acceleration of the engine () by implementing the acceleration regulation relationship corresponding to the current air extraction and to the current mechanical power take-off. 1. A method of reducing the risk of a surge phenomenon appearing in a turbine engine , said engine including a gas generator , air extraction means for extracting air from the gas generator , and mechanical power take-off means that co-operate mechanically with said gas generator , wherein:a plurality of acceleration regulation relationships are established before the engine is used and they are stored in an engine computer by the manufacturer, each acceleration regulation relationship corresponding to air extraction performed by said air extraction means in a first range, and to mechanical power take-off performed by the mechanical power take-off means in a second range;while the engine is being used, current air extraction and current mechanical power take-off is measured continuously; andacceleration of the engine is controlled by implementing the acceleration regulation relationship corresponding to the current air extraction and to the current mechanical power take-off.2. A method according to claim 1 , wherein claim 1 , in order to measure said air extraction claim 1 , the air extraction flow rate is measured.3. A method according to claim 1 , ...

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Номер записи: 12
08-08-2013 дата публикации

Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine

Номер: US20130199204A1
Автор: Emmanuel Camhi, Guido Borchers
Принадлежит: Eurocopter SA

A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS 1 ) and by verifying that a first amplitude (A 1 ) of the signal filtered in this way does not exceed a first threshold defined by the manufacturer, by performing second filtering of each signal by a high-pass filter over a short second duration (TPS 2 ) in parallel with said first filtering by a high-pass filter, and by verifying that a second amplitude (A 2 ) of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration (TPS 2 ) being less than the first duration (TPS 1 ), and the second amplitude (A 2 ) being less than the first amplitude (A 1 ).

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Номер записи: 13
08-08-2013 дата публикации

Gas turbine engine thermal management system

Номер: US20130202406A1
Автор: Ethan K. Stearns, Federico Papa, Justin W. Heiss, Kathleen R. Phillips, Thomas G. Phillips
Принадлежит: United Technologies Corp

A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

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Номер записи: 14
22-08-2013 дата публикации

CONTROL SYSTEM

Номер: US20130212999A1
Автор: Antonanzas Xabier, Bollhalder Heinz, LANG Wolfgang, Zinn Hanspeter
Принадлежит: ALSTOM Technology Ltd

A control system for at least one of steam turbines, gas turbines or power plants includes a sensor system configured to monitor predefined operating parameters, the sensor system including redundant sensors. A central processor arrangement of the control system has an input side configured to receive measurement data from the sensor system and an output side configured to communicate with operation control elements of the turbines or power plants. A sensor side processor circuit is assigned at least to the redundant sensors, the processor circuit being configured to continuously check the sensors for error-free operation, to protect or block the input side of the central processor arrangement from erroneous signals, and to only respectively forward or further process signals from a sensor that has been identified as error-free in one channel. 1: A control system for at least one of steam turbines , gas turbines or power plants , the control system comprising:a sensor system configured to monitor predefined operating parameters and including redundant sensors;a central processor arrangement having an input side configured to receive measurement data from the sensor system and an output side configured to communicate with operation control elements of the turbines or power plants;a sensor side processor circuit assigned at least to the redundant sensors, the processor circuit being configured to continuously check the sensors for error-free operation, to protect or block the input side of the central processor arrangement from erroneous signals, and to only respectively forward or further process signals from a sensor that has been identified as error-free in one channel.2: The control system recited in claim 1 , wherein the sensor-side processor circuit is configured to transform the signals from a sensor operating in an error-free manner according to a predefined requirement profile of the central processor arrangement.3: The control system recited in claim 1 , ...

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Номер записи: 15
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: 16
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: 17
05-09-2013 дата публикации

GENERATOR ARRANGEMENT AND OPERATING METHOD

Номер: US20130227944A1
Автор: Denholm Tim, Nishiyama Toshihiko, Ryder Owen Alistair
Принадлежит: Cummins Ltd

A method of operating a generator arrangement comprises selecting an operating mode as a function of at least one of: a speed of an engine, a temperature of at least a portion of the engine, a property of an exhaust fluid of the engine, and whether an engine braking command signal is received by the controller; controlling the flow of fluid from a first engine outlet to a first turbine by setting, based on the selected operating mode, an operating condition of a first flow control mechanism, the first turbine being part of a turbocharger having a compressor in fluid flow communication with an engine inlet; and controlling the flow of fluid from a second engine outlet to a second turbine by setting, based on the selected operating mode, an operating condition of a second flow control mechanism, the second turbine being parallel to the first turbine and being part of an electrical generator. 1. A method of operating a generator arrangement comprising:selecting an operating mode as a function of at least one of: a speed of an engine, a temperature of at least a portion of the engine, a property of an exhaust fluid of the engine, and whether an engine braking command signal is received by the controller;controlling the flow of fluid from a first engine outlet to a first turbine by setting, based on the selected operating mode, an operating condition of a first flow control mechanism, the first turbine being part of a turbocharger having a compressor in fluid flow communication with an engine inlet; andcontrolling the flow of fluid from a second engine outlet to a second turbine by setting, based on the selected operating mode, an operating condition of a second flow control mechanism, the second turbine being parallel to the first turbine and being part of an electrical generator.2. A method according to claim 1 , wherein the first engine outlet and the second engine outlet are one and the same.3. A method according to claim 1 , wherein the first flow control mechanism ...

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Номер записи: 18
19-09-2013 дата публикации

METHOD OF CONTROLLING ENGINE PERFORMANCE

Номер: US20130239579A1
Автор: Girouard Jacqueline R., Girouard Raymond, Moffat Robert J.
Принадлежит:

The present invention provides a method of controlling engine performance that includes obtaining at least one optical wavelength-dependent measurement from at least one combustion event in at least one combustion chamber. The method further includes analyzing the optical wavelength-dependent measurement for determining adjustments to the at least one combustion event. Additionally, the method includes adjusting the at least one combustion event or at least a next combustion event by changing at least one physical parameter, at least one constituent parameter, or at least one physical parameter and at least one constituent parameter to control the engine performance, where the physical parameter includes adjusting a turbine blade angle using a vane-adjust actuator in response to a signal from a controller. The engine can include steady-flow engines or periodic flow engines, and the engine performance can be selected by an engine user. 1a. obtaining at least one optical wavelength-dependent measurement from at least one combustion event in at least one combustion chamber of an engine;b. analyzing said at least one optical wavelength-dependent measurement for determining adjustments to said at least one combustion event; andc. adjusting said at least one combustion event or at least a next combustion event by changing at least one physical parameter, at least one constituent parameter, or at least one physical parameter and at least one constituent parameter to control said engine performance, wherein said physical parameter comprises adjusting a turbine blade angle using a vane-adjust actuator in response to a signal from a controller.. A method of controlling engine performance comprising: This application is a continuation of U.S. patent application Ser. No. 12/590373 filed Nov. 6, 2009, which is incorporated herein by reference.The invention relates to managing engine and turbine performance. In particular, the invention relates to using optical wavelength- ...

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Номер записи: 19
26-09-2013 дата публикации

CONTROL METHOD FOR AN OVERSPEED SAFETY SYSTEM, AND AN ASSOCIATED SYSTEM AND AIRCRAFT

Номер: US20130247577A1
Автор: Rossotto Regis, Vieira Hilario
Принадлежит: EUROCOPTER

A control method for controlling an overspeed safety system () of an aircraft () having at least a first engine () and a second engine (), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold. 1. A control method for controlling an overspeed safety system of an aircraft having at least a first engine and a second engine , wherein an engine is shut down when a monitoring parameter of that engine exceeds a first threshold , and another engine distinct from said engine is shut down when the monitoring parameter for said other engine exceeds a second threshold , said second threshold being greater than said first threshold.2. A method according to claim 1 , wherein each engine has a free turbine claim 1 , and said monitoring parameter of an engine is the speed of rotation of the free turbine of the engine.3. A method according to claim 1 , wherein each engine has safety means acting on blades of a turbine claim 1 , said safety means being activated from a predetermined limit of the monitoring parameter of said engine claim 1 , and said second threshold is lower than said predetermined limit.4. A method according to claim 1 , wherein each engine is fed with fuel by a respective booster pump claim 1 , and the booster pump of an engine is shut down when the engine is shut down.5. A method according to claim 1 , wherein a first control unit controls a first engine and a second control unit controls a second engine claim 1 , and when an engine exceeds the first threshold claim 1 , the associated control unit:shuts down that engine at the first threshold if the other control unit informs it that the other engine has not been shut down; andshuts down the engine at the second threshold if the other control unit informs it ...

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Номер записи: 20
03-10-2013 дата публикации

METHOD OF CONTROLLING A TURBOMACHINE

Номер: US20130255221A1
Автор: DJELASSI Cedrik, GAULLY Bruno Robert, McGrath Darragh, ROUX Jean-Michel
Принадлежит: SNECMA

A method of controlling a turbine engine, including: measuring a first temperature by a first temperature sensor; measuring a second temperature by a second temperature sensor; estimating a third temperature modeling the first temperature; and determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature. The first sensor presents a time constant longer than a time constant of the second sensor. The method further detects ingestion of water or hail as a function of a drop in the measured second temperature; and when water or hail ingestion is detected, determines the control setpoint as a function of the estimated third temperature. 17-. (canceled)8. A method of controlling a turbine engine , the method comprising:measuring a first temperature by a first temperature sensor;measuring a second temperature by a second temperature sensor;estimating a third temperature modeling the first temperature;determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature;the first sensor presents a time constant longer than a time constant of the second sensor; and the method further comprising:detecting ingestion of water or hail as a function of a drop in the measured second temperature; andwhen water or hail ingestion is detected, determining the control setpoint as a function of the estimated third temperature.9. A control method according to claim 8 , wherein the first temperature is a temperature at an inlet of a compressor of the turbine engine and the second temperature is a temperature at an outlet from the compressor.10. A control method according to claim 9 , wherein the first temperature sensor does not present an inertial separator.11. A control method according to claim 9 , wherein the control setpoint is an angle setpoint for a set of variable-pitch stator vanes of the ...

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Номер записи: 21
17-10-2013 дата публикации

Turbine fault prediction

Номер: US20130274898A1
Автор: Ravi Kanth Sai Thatikonda, Subhash Nemani
Принадлежит: General Electric Co

A system is provided. The system includes an industrial controller configured to control and obtain current parameter data from one or more components of an industrial system. Further, a storage is included and is configured to store historical data comprising parameter data from the one or more components. The system also includes a prediction controller configured to receive the current parameter data from the industrial controller, receive the historical data from the storage, and to generate an overall predictive score based at least in part upon the current parameter data and the historical data. The overall predictive score represents a likelihood of a fault within the industrial process control system.

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Номер записи: 22
24-10-2013 дата публикации

Gas turbine purge process

Номер: US20130276452A1
Автор: Pierre Montagne
Принадлежит: GE ENERGY PRODUCTS FRANCE SNC

This purge process of a gas turbine supply pipe network provided with fuel (diesel or natural gas) at least partly containing synthesis gas comprises of injection of inert gas in intervalve portions or collectors of the pipe network likely to contain fuel when the fuel supply is stopped. This injection of gas is implemented in the said portions of the network according to a sequence of respective injection.

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Номер записи: 23
07-11-2013 дата публикации

DEVICE AND A METHOD OF REGULATING A POWER PLANT INCLUDING AT LEAST ONE TURBINE ENGINE, AND AN AIRCRAFT

Номер: US20130291549A1
Автор: Martin Laurent
Принадлежит: EUROCOPTER

A regulator device () for regulating a turbine engine (). The regulator device () includes mechanical power take-off means () for taking off power mechanically from a gas generator (), and an engine computer () controlling said engine () to comply with at least a first limitation (LimTET, LimT45) of a temperature (TET, T45) of the gas within the engine, and with a second limitation (LimNg) of a speed of rotation (Ng) of the gas generator (). The engine computer () determines whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45). An avionics computer () causes the mechanical power take-off means () to operate if the speed of rotation (Ng) of the gas generator () has reached said second limitation (LimNg), and if said temperature (TET, T45) has not reached said first limitation (LimTET, LimT45). 1. A method of regulating a power plant including at least one turbine engine , said engine including a gas generator and a turbine assembly , said power plant including mechanical power take-off means for taking off power mechanically from said gas generator of said engine , and an engine computer , said engine computer controlling said engine so as to comply with at least a first limitation (LimTET , LimT45) for a temperature (TET , T45) of the gas within said assembly , and with a second limitation (LimNg) for a speed of rotation (Ng) of the gas generator;wherein:{'b': '1', 'during an evaluation step (STP), it is determined whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg);'}{'b': '1', 'during an evaluation step (STP), it is determined whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45); and'}{'b': '2', 'during an optimization step (STP), if the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and if said temperature ( ...

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Номер записи: 24
14-11-2013 дата публикации

Gas turbine engine systems and related methods involving multiple gas turbine cores

Номер: US20130298565A1
Автор: Gary D. Roberge
Принадлежит: United Technologies Corp

Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly.

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Номер записи: 25
19-12-2013 дата публикации

METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET

Номер: US20130338898A1
Автор: Aurousseau Christian, Deldalle Régis Michel Paul, FLANDROIS Xavier, Lamoureux Benjamin Pierre, MASSE Jean-Rémi André, Sif Aziz
Принадлежит: SNECMA

A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature. 114-. (canceled)15. A monitoring method of monitoring a servo-control loop of an actuator system for actuating variable-geometry components of a turbojet fitted to an aircraft , the actuator system including a servovalve controlling first and second actuators , the method comprising: a category of parameters representative of positions;', 'a category of parameters representative of speeds of the actuators;', 'a category of parameters representative of coefficients of autoregressive models used for predicting actuator positions as a function of a control current of the servovalve; and', 'a category of parameters representative of the control current of the servovalve or an integral current of the servo-control loop;, 'estimating a plurality of monitoring parameters from operating data of the servo-control loop, the monitoring parameters being selected from at least one of the following parameter categoriesobtaining a plurality of indicators from the monitoring parameters;determining at least one signature from values of at least some of the indicators; anddetecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature.16. A monitoring method according to claim 15 , wherein at least one of the parameters is estimated from an autoregressive model depending on at least one exogenous variable selected from:air pressure of a combustion chamber of the turbojet;metered fuel flow rate through at least one injector of the combustion chamber of the turbojet; andspeed of rotation of a high-pressure shaft of the turbojet.17. A ...

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Номер записи: 26
02-01-2014 дата публикации

METHOD TO START UP AND MANAGE A COMBINED CYCLE THERMAL PLANT FOR ENERGY PRODUCTION AND RELATIVE PLANT

Номер: US20140000277A1
Автор: Pasqualon Ezio
Принадлежит:

A method to start up and manage a combined cycle thermal plant for energy production comprising the execution according to a set sequence of a plurality of functional groups. 111. A method to start up and manage a combined cycle thermal plant for energy production comprising a first gas turbine and generator group (TG) , a first steam generator (GRV) , a multistage steam turbine (TV) and a generator coupled to said steam turbine (TV) wherein:{'b': 1', '1, 'said first steam generator (GRV) is a recovery steam generator to regenerate the latent heat of the exhaust gases of said first gas turbine and generator group (TG);'}{'b': '1', 'said first steam generator (GRV) is in fluid communication through steam lines at high, medium and low pressure with corresponding stages at high, medium and low pressure of said steam turbine (TV) and'}said generator is kinematic coupled to said steam turbine to be rotationally operated;{'b': 1', '1, 'said plant comprises detection and check means to monitor and detect a plurality of parameters connected to the correct functioning and/or malfunctioning of said first gas turbine and generator group (TG), of said first steam generator (GRV) and, respectively of said steam turbine (TV), wherein the start-up phases of the plant starting from an off-state comprise, in order, the following sequence of functional groups{'b': 1', '1, 'GFA: prearranging said first gas turbine and generator group (TG) for start-up;'}{'b': 2', '1', '1, 'GFA: Start-up of said first gas turbine and generator group (TG) and pressurization of said first steam generator (GRV);'}{'b': 3', '1, 'GFA: Warm up and load increase of said steam turbine (TV) following the start-up of said first gas turbine and generator group (TG) and vacuum to the capacitor;'} [{'b': 1', '1', '2', '1', '1, 'verifying through said detection and check means the actual completion of said operating unit GFA for the prearrangement of the start-up of said first gas turbine and generator group (TG) ...

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Номер записи: 27
02-01-2014 дата публикации

REAL TIME LINEARIZATION OF A COMPONENT-LEVEL GAS TURBINE ENGINE MODEL FOR MODEL-BASED CONTROL

Номер: US20140005909A1
Автор: Chung Gi Yun, Dhingra Manuj, Meisner Richard P., Prasad Jonnalagadda V. R.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A method for model-based control of a gas turbine engine is disclosed. An operating point of the gas turbine engine is generated from measured parameters using a component-level model. The component-level model is analytically linearized by taking the first partial derivative of output parameters of each component with respect to input parameters of each component, and evaluating the result at the operating point. Components of the linearized component-level model are combined to form a combined perturbational model of the gas turbine engine, which is inverted to solve for control commands as a function of target parameters and measured parameters. 1. A method for model-based control of a gas turbine engine , the method comprising:generating an operating point of the gas turbine engine from measured parameters using a component-level model comprised of a plurality of components;analytically linearizing the component-level model by taking the first partial derivative of input parameters of each component with respect to output parameters of each component, and evaluating the result at the operating point;combining components of the linearized component-level model to form a combined perturbational model of the gas turbine engine;inverting the combined perturbational model to solve for control commands as a function of target parameters and the measured parameters; andapplying the target parameters and the measured parameters to the combined perturbational model to generate control commands.2. The method of claim 1 , further comprising reducing the order of the combined perturbational model by eliminating internal variables.3. The method of claim 1 , further comprising reducing the order of combined perturbational model by eliminating error terms corresponding to discontinuities between parameters of adjacent components of the gas turbine engine.4. The method of claim 1 , wherein the operating point is partially constructed of measured parameters claim 1 , and ...

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Номер записи: 28
23-01-2014 дата публикации

METHOD OF AUTOMATICALLY REGULATING AN AIRCRAFT POWER PLANT, A DEVICE, AND AN AIRCRAFT

Номер: US20140020396A1
Автор: Corpron Alban
Принадлежит: EUROCOPTER

The present invention relates to an automatic method of regulating a power plant (′) of an aircraft (), the power plant having at least one turbine engine (), each engine () being capable of operating in an idling mode of operation. A calculation system () executes stored instructions in order to implement the idling mode of operation as a function of operational and ordered conditions either via a first regulation mode by regulating a first speed of rotation (Ng) of said gas generator (), or via a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine (). 1. A method of automatically regulating a power plant of an aircraft having at least one turbine engine to operate in an idling mode of operation , each engine having a gas generator and a free turbine , wherein:{'b': '0', 'during a selection step (STP), an idling mode of operation is selected; and'}{'b': '1', 'during a regulation step (STP), if the aircraft is standing on the ground, the idling mode of operation is implemented as a function of operational and hierarchically ordered conditionseither through a first mode of regulation by regulating a first speed of rotation (Ng) of said gas generator;or through a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine.2. A method according to claim 1 , wherein said operational and hierarchically ordered conditions may be selected from a list including:generation of hot air from the engine for heating the aircraft as a function of outside conditions;generation of electricity from the gas generator for electrically powering the aircraft;minimization of noise emission; andminimization of fuel consumption.3. A method according to claim 2 , wherein an order of priorities is established as a function of the needs defined by the operator of the aircraft.4. A method according to claim 1 , wherein said operational and hierarchically ordered conditions are in the following order:generation of hot ...

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Номер записи: 29
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: 30
27-02-2014 дата публикации

SYSTEM AND METHOD FOR ON LINE MONITORING WITHIN A GAS TURBINE COMBUSTOR SECTION

Номер: US20140053568A1
Автор: Genc Yakup, Hatcher, Hatley Richard, JR. Clifford, Ruhge Forrest R.
Принадлежит:

An on-line optical inspection and monitoring system is externally mounted to existing man way service access within the combustor housing. A replacement man way cover having an optical window is mounted to the combustor housing. One or more optical cameras are oriented so that the camera field of view (FOV) is directed through the man way cover optical window. The camera FOV is moved to plural positions within the combustion section, such as under control of an automated motion control system, and images are captured. Multiple images are combined to form a composite image, which may include an image of an entire transition within the combustion section. Visual images and/or infrared (IR) thermal images may be captured. Thermal image information is correlated with component temperature. Image information is utilized to determine vibration characteristics of the imaged components. 1. A method for on-line optical operational monitoring of an industrial gas turbine combustion section , comprising:coupling a man way cover having an optical window to a combustion section service man way;directing the field of view (FOV) of an optical camera located outside the man way through the optical window, so that the FOV is capable of capturing images of areas of interest within the combustion section;moving the camera FOV to plural positions within the combustion section and capturing respective images at each position; andcombining the respective captured images in a composite image.2. The method of claim 1 , comprising moving the camera FOV along a length of a combustion section transition between its entrance and exit to form a composite image thereof.3. The method of claim 1 , further comprising remote monitoring temperature of areas of interest within an infrared camera FOV by correlating captured image infrared intensity with temperature.4. The method of claim 3 , the correlating step performed by comparing captured FOV image intensity with blackbody intensity calibration ...

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Номер записи: 31
06-03-2014 дата публикации

METHOD FOR OPERATING A GAS TURBINE IN THE CASE OF LOAD SHEDDING, A DEVICE FOR CONTROLLING THE OPERATION OF A GAS TURBINE AND A POWER PLANT

Номер: US20140060066A1
Автор: Hesse Holger
Принадлежит:

A method is provided for operating a gas turbine in the event of load shedding and/or rapid shutdown. The method includes operating the gas turbine by the combustion of fuel in a combustion chamber of the gas turbine with the addition of combustion air via an air passage, and driving a load. Upon or directly after the load shedding or rapid shutdown, an additional gas volume is supplied to the combustion chamber via the air passage in order to slow the drop in pressure level in the combustion chamber. 110-. (canceled)11. A method for operating a gas turbine in the event of load rejection and/or rapid shutdown , comprising:operating the gas turbine by the combustion of fuel in a combustion chamber of the gas turbine with the addition of combustion air via an air passage, anddriving a load,the method further comprising:upon or directly after the load rejection or rapid shutdown, supplying an additional gas volume to the combustion chamber via the air passage in order to slow the drop in pressure level in the combustion chamber.12. The method as claimed in claim 11 , wherein the gas volume is extracted from a gas store.13. The method as claimed in claim 11 , wherein compressed air is used as a gas volume.14. The method as claimed in claim 11 , further comprising extracting claim 11 , during the operation of the gas turbine claim 11 , a fraction of the air compressed in a compressor of the gas turbine from said compressor via an air extraction line claim 11 ,wherein, in the case of load rejection or rapid shutdown, the compressed air flowing in the air extraction line is used as a gas volume.15. The method as claimed in claim 11 , wherein claim 11 , during operation claim 11 , the gas turbine drives an electrical generator which is connected to an electricity distribution grid claim 11 , and wherein the load rejection takes place as a result of an abrupt reduction in the electrical power to be imparted by the generator or as a result of the separation of the generator ...

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Номер записи: 32
01-01-2015 дата публикации

SYSTEMS AND METHODS FOR CONTROLLING EXHAUST GAS FLOW IN EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEMS

Номер: US20150000293A1
Автор: Thatcher Jonathan Carl, Vorel Aaron Lavene, West James A.
Принадлежит:

A method of controlling an exhaust gas recirculation (EGR) gas turbine system includes adjusting an angle of a plurality of inlet guide vanes of an exhaust gas compressor of the EGR gas turbine system, wherein the plurality of inlet guide vanes have a first range of motion defined by a minimum angle and a maximum angle, and wherein the angle is adjusted based on one or more monitored or modeled parameters of the EGR gas turbine system. The method further includes adjusting a pitch of a plurality of blower vanes of a recycle blower disposed upstream of the exhaust gas compressor, wherein the plurality of blower vanes have a second range of motion defined by a minimum pitch and a maximum pitch, and the pitch of the plurality of blower vanes is adjusted based at least on the angle of the plurality of inlet guide vanes. 1. An exhaust gas recirculation (EGR) gas turbine system , comprising:an exhaust gas compressor positioned along an EGR path and configured to compress a recirculated exhaust gas to produce an exhaust gas diluent, wherein the exhaust gas compressor comprises an inlet section comprising a flow control element configured to modulate a flow of the recirculated exhaust gas into the exhaust gas compressor based on a position of the flow control element, wherein the position of the flow control element is capable of ranging from a maximum open position to a minimum open position;a recycle blower positioned along the EGR path and upstream of the exhaust gas compressor, wherein the recycle blower is configured to provide the flow of recirculated exhaust gas to the inlet section, wherein the flow of recirculated exhaust gas ranges from a minimum blower output to a maximum blower output; anda controller coupled to the flow control element and to the recycle blower, wherein the controller is configured to control the position of the flow control element based on a measured or modeled parameter of the EGR gas turbine system, wherein the controller is configured to ...

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Номер записи: 33
01-01-2015 дата публикации

SYSTEMS AND METHODS FOR MONITORING GAS TURBINE SYSTEMS HAVING EXHAUST GAS RECIRCULATION

Номер: US20150000294A1
Автор: Beadie Douglas Frank, Minto Karl Dean
Принадлежит:

A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of extraction passages, wherein the plurality of sensors is configured to measure one or more parameters of the portion of the gas flow traversing the plurality of extraction passages. The system also includes a manifold coupled to the plurality of extraction passages, wherein the manifold is configured to receive the portion of the gas flow from the plurality of extraction passages. The system further includes a return passage coupled to the manifold, wherein the return passage is configured to passively provide the portion of the gas flow to an upstream region of the gas flow path. 1. A system , comprising: a combustor section having one or more combustors configured to combust a fuel and produce an exhaust gas;', 'a turbine section comprising one or more turbine stages disposed downstream from the combustor and configured to be driven by the exhaust gas;', 'an exhaust section disposed downstream from the one or more turbine stages, wherein the exhaust section comprises an exhaust passage configured to receive the exhaust gas from the turbine section; and', 'a gas flow extraction system coupled to the exhaust section and comprising a plurality of extraction passages disposed about the exhaust section, wherein each extraction path is configured to receive a portion of the exhaust gas from a downstream portion of the exhaust passage, wherein the gas flow extraction system is configured to passively route the portion of the exhaust gas to an upstream portion of the exhaust passage via one or more return passages., 'a gas turbine engine, comprising2. The system of claim 1 , wherein each of the plurality of extraction passages comprises one or more sensors.3. The system of claim 2 , wherein the one or more sensors comprise an oxygen ...

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Номер записи: 34
05-01-2017 дата публикации

GAS TURBINE COOL-DOWN PHASE OPERATION METHODS

Номер: US20170002740A1
Автор: CATALDI Giovanni, FILKORN Guenter, PATHAK Gaurav, ROBSON Christopher Michael, RUETER Andreas
Принадлежит: ANSALDO ENERGIA SWITZERLAND AG

The application describes a method of operating a gas turbine during a cool-down phase. The gas turbine provides a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, with the turbine providing a turbine vane carrier. The method includes feeding a flow of cooling air from the compressor to the turbine vane carrier, measuring a temperature of the flow of cooling air and measuring a temperature of the turbine vane carrier. In the method, the flow of cooling air is fed at a first flow rate when the temperature of the turbine vane carrier is lower than the temperature of the cooling air, and the flow of cooling air is fed at a second flow rate when the temperature of the turbine vane carrier is higher than the temperature of the cooling air, wherein the first flow rate is higher than the second flow rate. 1. A method of operating a gas turbine during a cool-down phase , the gas turbine providing a compressor , a combustor downstream of the compressor , and a turbine downstream of the combustor , the turbine providing a turbine vane carrier , the method comprising:feeding a flow of cooling air from the compressor to the turbine vane carrier;measuring a temperature of the flow of cooling air; andmeasuring a temperature of the turbine vane carrier;wherein the flow of cooling air is fed at a first flow rate when the temperature of the turbine vane carrier is lower than the temperature of the cooling air; andwherein the flow of cooling air is fed at a second flow rate when the temperature of the turbine vane carrier is higher than the temperature of the cooling air,wherein the first flow rate is higher than the second flow rate.2. The method of claim 1 , wherein the flow of cooling air is fed from the compressor to the turbine vane carrier through a cooling unit.3. The method of claim 2 , wherein the flow of cooling air is fed from the compressor to the turbine vane carrier through a once-through cooler.4. The method of claim 2 , ...

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Номер записи: 35
04-01-2018 дата публикации

ROTOR BLADE DAMAGE

Номер: US20180003073A1
Автор: BINNINGTON Mark N, ROWE Arthur L, THORNTON Paul R, WOODWARD Colin J
Принадлежит: ROLLS-ROYCE PLC

A rotor assembly () comprising a rotor () having an annular array of rotor blades (), the rotor mounted to a shaft (). A phonic wheel () coupled to the shaft. A speed sensor () axially aligned with the phonic wheel and configured to measure voltage (V), amplitude of the voltage being proportional to clearance () between the sensor and phonic wheel. A processor () configured to: receive the voltage measurement; derive shaft speed (ω) from the voltage measurement; identify modulation of the voltage amplitude at a frequency which is an integer multiple of the shaft speed; compare voltage amplitude to a threshold; and output a rotor damage signal based on the comparison. 1301030. A rotor assembly () in a gas turbine engine () , the rotor assembly () comprising:{'b': 32', '34', '38, 'a rotor () having an annular array of rotor blades (), the rotor mounted to a shaft ();'}{'b': 40', '38, 'a phonic wheel () coupled to the shaft ();'}{'b': 44', '40', '46', '44', '40, 'a speed sensor () axially aligned with the phonic wheel () and configured to measure voltage (V), amplitude of the voltage (V) being proportional to clearance () between the sensor () and phonic wheel (); and'}{'b': '48', 'claim-text': i. receive the voltage (V) measurement;', 'ii. derive shaft speed (ω) from the voltage (V) measurement;', 'iii. identify modulation of the voltage (V) amplitude at a frequency which is an integer multiple of the shaft speed (ω);', {'b': '56', 'iv. compare voltage (V) amplitude to a threshold (); and'}, 'v. output a rotor damage signal based on the comparison., 'a processor () configured to23056. A rotor assembly () as claimed in wherein the threshold () comprises a ratio of maximum to average voltage (V) amplitude.33056. A rotor assembly () as claimed in wherein the threshold () comprises a predetermined proportion of maximum voltage (V) amplitude.43056. A rotor assembly () as claimed in wherein the threshold () comprises 80% of the maximum voltage (V) amplitude.53056. A rotor ...

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Номер записи: 36
02-01-2020 дата публикации

PHONIC WHEEL WITH OUTPUT VOLTAGE TUNING

Номер: US20200003074A1
Автор: YAKOBOV Ella
Принадлежит:

Herein provided is a phonic wheel for use in a gas turbine engine and associated systems and methods. The phonic wheel comprises a circular disk having first and second opposing faces. The circular disk defines a root surface that extends between and circumscribes the first and second faces. A first plurality of projections extend from the root surface and are oriented substantially parallel to an axis of rotation of the disk. The first plurality of projections are circumferentially spaced substantially equally from one another and each have a first physical configuration. At least one second projection extends from the root surface and is positioned between two adjacent first projections, the at least one second projection having a second physical configuration different from the first physical configuration. 1. A phonic wheel for use in a gas turbine engine , the phonic wheel comprising:a circular disk having first and second opposing faces, the circular disk defining a root surface that extends between and circumscribes the first and second faces;a first plurality of projections extending from the root surface and oriented substantially parallel to an axis of rotation of the disk, the first plurality of projections circumferentially spaced substantially equally from one another and each having a first physical configuration; andat least one second projection extending from the root surface and positioned between two adjacent first projections, the at least one second projection having a second physical configuration different from the first physical configuration.2. The phonic wheel of claim 1 , wherein the at least one second projection having a second physical configuration different from the first physical configuration comprises the at least one second projection having a height greater than that the first plurality of projections.3. The phonic wheel of claim 1 , wherein the at least one second projection having a second physical configuration different from ...

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Номер записи: 37
03-01-2019 дата публикации

MICRO GAS TURBINE SYSTEMS AND USES THEREOF

Номер: US20190003385A1
Автор: Ethier Jason How-Ring, Hatch Alyssa, Herold Erik, Wang Ivan
Принадлежит: Dynamo Micropower Corporation

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications. 117.-. (canceled)18. A method of operating a gas turbine heater , wherein the gas turbine heater comprises a gas turbine comprising i) an air starter; ii) a compressor; iii) a turbine; and iv) a combustion unit configured to receive compressed air for combustion from the compressor , to receive a fuel from a source , to burn the fuel to produce a combustion gas , and to supply the combustion gas to the turbine , wherein the gas turbine is configured to heat an external environment directly or indirectly using combustion gas exhausted from the turbine , the method comprising:operating a fan to pump air through an enclosure of the gas turbine heater such that the air passes from an ambient air inlet of the enclosure to an outlet of the ...

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Номер записи: 38
01-01-2015 дата публикации

SYSTEM AND METHOD FOR CONDITIONING NOISY SIGNALS

Номер: US20150006058A1
Автор: GEORGE Kim, TANG Poi Loon
Принадлежит: PRATT & WHITNEY CANADA CORP.

There is provided a system and method for conditioning a noisy signal. A sensing signal is received during each one of a plurality of successive control cycles, the sensing signal comprising a measurement component indicative of a measurement of at least one engine parameter and a noise component. A curve-fitting technique is applied to the received sensing signal for filtering thereof to attenuate the noise component, the filtering comprising, during a first one of the plurality of the control cycles, asymmetrically filtering the sensing signal received during the first control cycle, thereby generating filtered data, and, during a second control cycle subsequent to the first control cycle, symmetrically filtering the sensing signal received during the first control cycle, thereby generating corrected data. 1. A system for conditioning a noisy signal , the system comprising:a receiving unit adapted to receive a sensing signal during each one of a plurality of successive control cycles, the sensing signal comprising a measurement component indicative of a measurement of at least one parameter of an engine and a noise component; anda processing unit adapted to apply a curve-fitting technique to the received sensing signal for filtering thereof to attenuate the noise component, the filtering comprising, during a first one of the plurality of control cycles, asymmetrically filtering the sensing signal received during the first control cycle, thereby generating filtered data, and, during a second control cycle subsequent to the first control cycle, symmetrically filtering the sensing signal received during the first control cycle, thereby generating corrected data.2. The system of claim 1 , wherein the processing unit is adapted to form a data buffer comprising a first number of buffer elements claim 1 , the first number equal to a second number of the plurality of control cycles claim 1 , and to store claim 1 , during the first control cycle being a present one of the ...

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Номер записи: 39
08-01-2015 дата публикации

SYSTEMS AND METHODS FOR CONTROL OF A GAS TURBINE

Номер: US20150007574A1
Автор: Baker Scott Richard, Davis, Jordan Harold Lamar, JR. Lewis Berkley, Morgan Rex Allen
Принадлежит:

A system includes a gas turbine system including a compressor, a combustor, and a turbine. The system also includes a controller communicatively coupled to the gas turbine system and configured to control operations of the gas turbine system. The system further includes a life consumption model configured to determine an operating life of the gas turbine system based on both a health status of one or more components of the gas turbine system and operating conditions of the gas turbine system. The controller is configured to utilize at least the life consumption model to derive a control action for the gas turbine system. 1. A system , comprising:a gas turbine system comprising a compressor, combustor, and a turbine;a controller communicatively coupled to the gas turbine system and configured to control operations of the gas turbine system; anda life consumption model configured to determine an operating life of the gas turbine system based on both a health status of one or more components of the gas turbine system and operating conditions of the gas turbine system, wherein the controller is configured to utilize at least the life consumption model to derive a control action for the gas turbine system.2. The system of claim 1 , wherein the life consumption model is configured to calculate an actual life consumption rate for the gas turbine system based on both the health status of the one or more components of the gas turbine system and the operating conditions of the gas turbine system.3. The system of claim 2 , wherein the life consumption model is configured to utilize both a life consumption target rate for the gas turbine system and the actual life consumption rate to determine the operating life of the gas turbine system.4. The system of claim 3 , wherein the life consumption model is configured to adjust the life consumption target rate based on the actual life consumption rate.5. The system of claim 1 , wherein the controller is configured to utilize the life ...

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Номер записи: 40
12-01-2017 дата публикации

Device for Automatically Regulating Aircraft Power Plant Gas Generator and Free Turbine Speeds as a Function of Heating, Electricity Generation, Noise Emission, and Fuel Consumption

Номер: US20170009662A1
Автор: Corpron Alban
Принадлежит: AIRBUS HELICOPTERS

A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine. 1. A regulator device for automatically regulating a power plant of an aircraft having a rotary wing and a turbine engine , the turbine engine being operable in an idling mode of operation and having a gas generator and a free turbine , the regulator device comprising: a first mode of regulation by regulating a speed of rotation (Ng) of the gas generator; or', 'a second mode of regulation by regulating a speed of rotation (NTL) of the free turbine., 'a computer system configured to control the turbine engine, the computer system further configured to, while implementation of the idling mode of operation is requested and the aircraft is standing on ground, implement the idling mode of operation and operate the turbine engine in compliance with the idling mode of operation as a function of a plurality of operational and hierarchically ordered conditions either through2. The regulator device of wherein:the computer system includes at least one of an avionics computer and an engine computer.3. The regulator device of further comprising:a selector for requesting implementation of the idling mode of operation; andwherein the computer system is connected to the selector.4. The regulator device of wherein:the computer system includes an avionics computer and an engine ...

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Номер записи: 41
27-01-2022 дата публикации

SYSTEM FOR COOLING AN AIRCRAFT TURBOJET ENGINE

Номер: US20220025816A1
Автор: BOUCHOUT Jean-Nicolas, CHOUQUET Nicolas, CORBIN Julien, DANG Caroline, Pereira David, PEYRON Vincent
Принадлежит: Safran Nacelles

A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases. 1. A cooling system for a turbojet engine assembly for an aircraft , the turbojet engine assembly including a turbojet engine and a nacelle , the nacelle having an outer structure including an outer fairing defining an outer aerodynamic surface , and an inner fairing defining an inner aerodynamic surface , the cooling system comprising:a first heat-exchanger configured to transfer heat between a heat-transfer fluid and a lubricant of the turbojet engine;a second heat-exchanger configured to transfer heat between the heat-transfer fluid and air; anda first circulation pipe configured to circulate the heat-transfer fluid in closed circuit, the circulation pipe including a portion forming the second heat-exchanger and configured to be disposed in the nacelle in contact with the inner fairing of the nacelle, the outer fairing of the nacelle, or both the inner and outer fairings of the nacelle,wherein the cooling system comprises at least one regulation device for regulating heat extracted from the lubricant of the turbojet engine, the at least one regulation device being controlled by a control module configured to receive information according to different flight phases via a controller member of the turbojet engine,wherein the at least one regulation device for regulating heat extracted from the lubricant of the turbojet engine comprises a plurality of electrical devices for ...

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Номер записи: 42
27-01-2022 дата публикации

Hybrid electric fan with stall free low pressure compressor

Номер: US20220025823A1
Автор: Christopher J. Hanlon, Daniel Bernard Kupratis, William G. Sheridan
Принадлежит: Raytheon Technologies Corp

A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.

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Номер записи: 43
14-01-2021 дата публикации

SINGLE-SHAFT COMBINED CYCLE PLANT, TESTING METHOD FOR SINGLE-SHAFT COMBINED CYCLE PLANT, AND CONTROL DEVICE FOR SINGLE-SHAFT COMBINED CYCLE PLANT

Номер: US20210010393A1
Автор: Aoki Katsuhiro, ENDO Yoji, ESAKI Daisuke, IDEGUCHI Junya, KANAKUCHI Naoya, SHIRAIWA Takashi
Принадлежит:

This single-shaft combined cycle plant comprises: a power generator; a gas turbine; a steam turbine that is driven by using waste heat from the gas turbine, and is connected to the power generator by a clutch when the rotational speed syncs with the rotational speed of the gas turbine; a steam turbine over-rotation prevention device; a gas turbine over-rotation prevention device; and a control device. The control device sets the power generator to an unloaded state and, whilst maintaining the rotational speed Ng of the gas turbine so as to be higher than the rotational speed Ns of the steam turbine and lower than the maximum rotational speed Nglim of the gas turbine, increases the rotational speed Ns of the steam turbine to the maximum rotational speed Nslim of the steam turbine (time t-t) and tests whether or not the steam turbine over-rotation prevention device operates normally. 1. A single-shaft combined cycle plant comprising:a generator;a gas turbine connected to the generator;a steam turbine driven by using waste heat of the gas turbine, and connected to the generator by a clutch when a rotation speed of the steam turbine is synchronized with a rotation speed of the gas turbine;a steam turbine over-rotation prevention device that stops an operation of the steam turbine, when the rotation speed of the steam turbine reaches a predetermined steam turbine upper limit rotation speed;a gas turbine over-rotation prevention device that stops an operation of the gas turbine, when the rotation speed of the gas turbine reaches a predetermined gas turbine upper limit rotation speed; anda control device that brings the generator into an unloaded state, that increases the rotation speed of the steam turbine until the rotation speed of the steam turbine reaches the steam turbine upper limit rotation speed while maintaining the rotation speed of the gas turbine to be lower than the gas turbine upper limit rotation speed, in a state where connection between the generator and ...

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Номер записи: 44
09-01-2020 дата публикации

Aircraft component qualification system and process for target based inventory qualification

Номер: US20200012750A1
Автор: Daniel A. Snyder, Kurt R. Heinemann
Принадлежит: United Technologies Corp

The system then identifies as-manufactured parameters of a second engine component, and applies the as-manufactured parameters of the second engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models. An optimum predicted response from each of the generated predicted response models is identified and the engine type or engine assembly that corresponds with the optimum predicted response is associated with a unique part identifier of the second engine component.

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Номер записи: 45
19-01-2017 дата публикации

Operation plan preparation and evaluation device and operation plan preparation and evaluation method

Номер: US20170016400A1
Автор: Aki NAKAYAMA, Akihiko Yamada, Manabu Kasano, Tomoaki Kitagawa
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

An operation plan preparation and evaluation device including a storage unit for storing master data related to equipment and a component, transaction data related to the equipment and the component generated when an operation plan is prepared, and an initial parameter used when the operation plan is prepared, and a control unit for preparing the operation plan based on the master data, the transaction data, and the initial parameter, in which the control unit performs a factor setting process of assigning a predetermined set value as the initial parameter, an operation plan preparation process of preparing the operation plan based on the initial parameter serving as the set value, the master data, and the transaction data, and an operation plan evaluation process of evaluating a plurality of respective operation plans prepared by repeatedly performing the operation plan preparation process while varying the initial parameter, and deriving an optimum operation plan.

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Номер записи: 46
15-01-2015 дата публикации

GAS TURBINE ENGINE CONTROLLER WITH EVENT TRIGGER

Номер: US20150019104A1
Автор: TANRIVERDI Olgu
Принадлежит:

A feedback control system is provided and includes a controller to control an operation of a motive element in accordance with current and previous measured states. The controller includes a servo, a processor and an event trigger controller. The event trigger controller is configured to cause the processor to command the servo to perform model based control (MBC) executions in an event a difference between the current and previous measured states exceeds a threshold based on the previous measured state or the current measured state exceeds a limit, and skip the MBC executions in an event the difference does not exceed the threshold and the current measured state does not exceed the limit. 1. A feedback control system , comprising:a controller to control an operation of a motive element in accordance with current and previous measured states,the controller including a servo, a processor and an event trigger controller,the event trigger controller being configured to cause the processor to command the servo to:perform model based control (MBC) executions in an event a difference between the current and previous measured states exceeds a threshold based on the previous measured state or the current measured state exceeds a limit, andskip the MBC executions in an event the difference does not exceed the threshold and the current measured state does not exceed the limit.2. The feedback control system according to claim 1 , wherein the current and previous measured states respectively correspond to consecutive time steps.3. The feedback control system according to claim 1 , further comprising:a measurement unit to measure the state of the gas turbine engine; anda feedback unit to provide feedback control information to the controller.4. The feedback control system according to claim 3 , wherein the measurement unit periodically measures the state of the gas turbine engine.5. The feedback control system according to claim 1 , wherein the event trigger controller is ...

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Номер записи: 47
17-01-2019 дата публикации

CLUTCHED COMPRESSOR SECTION FOR GAS TURBINE ENGINE

Номер: US20190017436A1
Автор: DiBenedetto Enzo, Ditomasso John C.
Принадлежит:

A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft. 1. A clutched compressor section of a gas turbine engine coupled to a rotor shaft , comprising:at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.2. The clutched compressor section of claim 1 , further comprising:a plurality of compressor rotor stages axially spaced from each other and operatively coupled to each other, the at least one decoupleable rotor stage being one of the plurality of compressor rotor stages; anda group of stages of the plurality of compressor rotor stages coupled to each other and to the rotor shaft, the at least one decoupleable rotor stage coupled to the group of stages in the coupled condition and decoupled from the group of stages in the decoupled condition, the decoupled condition allowing the decoupleable rotor stage to freely rotate independently of the group of stages.3. The clutched compressor section of claim 2 , wherein the decoupleable stage is located downstream of the group of stages.4. The clutched compressor section of claim 1 , wherein the decoupleable stage is coupled to a shaft that is coaxially oriented with the rotor shaft.5. The clutched compressor section of claim 2 , wherein the clutch mechanism comprises:a first engagement member extending from a disk of one of the stages of the group of stages; anda second ...

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Номер записи: 48
26-01-2017 дата публикации

Adaptive PID Control System for Industrial Turbines

Номер: US20170023965A1
Автор: Britt Tena K.
Принадлежит:

The subject matter of this specification can be embodied in, among other things, a method that includes providing a process controller configured to perform a control algorithm based on at least one first control parameter, providing a parameter controller configured to perform a parameter adjustment algorithm, providing a turbine having an output sensor, providing to the process controller at least one first control parameter and a first input value, controlling the turbine based on the at least one first control parameter and the first input value, receiving a turbine response value provided by the turbine output sensor, determining at least one second control parameter based on the turbine response value and the parameter adjustment algorithm, providing, to the process controller from the parameter controller, the at least one second control parameter, and controlling the turbine based on the at the least one second control parameter and a second input value. 145-. (canceled)46. A method for controlling a process , comprising:providing a process controller configured to perform a control algorithm based on at least one first control parameter representing a first value selected from a group comprising a proportional gain (P) value, an integral gain (I) value, and a derivative gain (D) value based on a speed derivative ratio (SDR);providing a parameter controller configured to perform a parameter adjustment algorithm;providing a controllable process configured to provide a process response value to the process controller and the parameter controller;providing, to the process controller, at least one first control parameter and a first input value;controlling, by the process controller, the controllable process based on the at least one first control parameter and the first input value;receiving, by the parameter controller, the process response value;determining, by the parameter controller, at least one second control parameter based on the process response value ...

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Номер записи: 49
10-02-2022 дата публикации

AIRCRAFT HYBRID PROPULSION SYSTEM

Номер: US20220042465A1
Автор: SWANN Peter
Принадлежит:

A control system for an aircraft hybrid propulsion system comprising a gas turbine engine coupled to an electric generator, a propulsor coupled to an electric motor, and an electrical storage device coupled to the motor and the generator. The control system configured to operate the propulsion system in a first descent mode and a second descent mode. In the first descent mode, the gas turbine engine is operated at a first engine power level and the generator is operated at a first generator power level. In the second descent mode, the gas turbine engine is operated at a second engine power level, higher than the first engine power level, and the generator is operated at a second generator power level, higher than the first generator power level. Electric power generated by the electric generator during operation in the second descent mode is stored in the electrical storage device. 1. A control system for an aircraft hybrid propulsion system , the hybrid propulsion system comprising;a gas turbine engine coupled to an electric generator;a propulsor coupled to an electric motor; andan electrical energy storage device coupled to the motor and the generator;whereinthe control system comprising a controller configured to operate the propulsion system in one of a first descent mode and a second descent mode, wherein in the first descent mode, for a given thrust, the gas turbine engine is operated at a first engine power level and the generator is operated at a first generator power level, and in the second descent mode, for a given thrust, the gas turbine engine is operated at a second engine power level which is higher than the first engine power level, and the generator is operated at a second generator power level which is higher than the first generator power level, wherein electric power generated by the electric generator during operation in the second descent mode is stored in the electrical energy storage device.2. A control system according to claim 1 , wherein ...

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Номер записи: 50
24-01-2019 дата публикации

PLANT CONTROL APPARATUS, PLANT CONTROL METHOD AND POWER PLANT

Номер: US20190024529A1
Автор: KAJIHARA Mizu, Mori Takahiro, TOBOU Masayuki
Принадлежит:

In one embodiment, a plant control apparatus controls a power plant that includes a combustor to burn fuel with oxygen introduced from an inlet guide vane to generate gas, a gas turbine driven by the gas from the combustor, a heat recovery steam generator to generate steam using heat of an exhaust gas from the gas turbine, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus controls an angle of the inlet guide vane before a start of the steam turbine to a first angle, controls the angle of the inlet guide vane after the start of the steam turbine to a second angle larger than the first angle, and reduce the angle of the inlet guide vane from the second angle to the first angle or more during the predetermined period. 2. The apparatus of claim 1 , wherein the second output controller continuously reduces the angle of the inlet guide vane from the second angle to the first angle or to the third angle during the predetermined period such that the angle of the inlet guide vane is the second angle at a start time of the predetermined period and the angle of the inlet guide vane is the first angle or the third angle at a completion time of the predetermined period.3. The apparatus of claim 1 , wherein the angle controller calculates a setting value of temperature rising speed of a temperature of the exhaust gas during the predetermined period claim 1 , and controls the angle of the inlet guide vane based on the setting value of the temperature rising speed.4. The apparatus of claim 3 , wherein the angle controller calculates the setting value of the temperature rising speed by dividing a difference between a setting value of the temperature of the exhaust gas at the start time of the predetermined period and a setting value of the temperature of the exhaust gas at the completion time of the predetermined period by the predetermined period.5. The apparatus of claim 4 , whereinthe setting value of the temperature of the exhaust gas ...

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Номер записи: 51
23-01-2020 дата публикации

Optimal thrust control of an aircraft engine

Номер: US20200025130A1
Автор: Chaohong Cai, David Lei Ma, Mark E. Lacour, Timothy J. Crowley
Принадлежит: United Technologies Corp

A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system may further include a control module for determining a control command for the gas turbine engine. The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal and an estimated thrust value. The control system may further include an actuator for controlling the gas turbine engine based on the control command.

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Номер записи: 52
29-01-2015 дата публикации

Method for securing the operation of a turbomachine

Номер: US20150030464A1
Автор: Alban Lemaitre, Serge LE GONIDEC
Принадлежит: SNECMA SAS

A method of making safe operation of a rotary assembly of a turbomachine including a turbine and a rotary machine, the method anticipating an event of exceeding a predetermined threshold speed by repetitively performing a prediction cycle including: measuring magnitudes relating to operation of the turbomachine, including real speed of rotation of its rotary assembly; based on the magnitudes, estimating driving and resisting torques applied to the rotary assembly; preparing a representative value representative of the difference between these two torques; and calculating a predicted speed of rotation for the rotary assembly at a given time horizon based on the representative value and the real speed of rotation. An action is taken on the operation of the turbomachine to limit an extent to which its rotary assembly exceeds the threshold speed in the event of the predicted speed of rotation exceeding the threshold speed.

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Номер записи: 53
31-01-2019 дата публикации

SYSTEM FOR CONTROLLING A CONTROLLED PARAMETER

Номер: US20190031359A1
Автор: DJELASSI Cedrik
Принадлежит: SAFRAN AIRCRAFT ENGINES

A control system for controlling a controlled parameter of an aeronautical equipment device, the controlled parameter being governed by an operating law linking the controlled parameter to a command and to a plurality of input parameters, the control system including a control loop controlling the controlled parameter to a setpoint with the control of the device by the command, the system including an operating law compensation module and a determination module determining a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of the controlled parameter in response to a variation in the command in a stabilised operating regime of the operating law, the operating law compensation module using the inverse of the local gain. 1. A system for controlling a regulated parameter of an aeronautical equipment device , said regulated parameter being governed by an operating law of said aeronautical equipment device linking said regulated parameter to a command and to a plurality of input parameters , said operating law being modellable by a transfer function constituting a mathematical model of a relationship between the command , the input parameters , and the regulated parameter , said regulation control system comprising a regulation loop servo-controlling said regulated parameter at a setpoint through the command controlling the aeronautical equipment device ,wherein the regulation loop comprises a regulator comprising in series a corrector and a compensation module of the operating law whereof a transfer function is intended to compensate the transfer function of the operating law, the command being delivered to the aeronautical equipment device corresponding to an output of the regulator, wherein the system further comprises a determination module of a local gain receiving the command and the input parameters, and configured to determine a local gain of a static part of a model of the operating law ...

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Номер записи: 54
31-01-2019 дата публикации

METHOD AND APPARATUS FOR PREDICTING TURBINE OUTLET TEMPERATURE IN GAS TURBINE

Номер: US20190032512A1
Автор: KANIWA Masato, KAWANO Yukihiro, SCHMIT Nicolas, SODEKODA Shiho
Принадлежит: IHI CORPORATION

In a method for predicting a turbine outlet temperature at a future use of a gas turbine based on a past use thereof, the turbine outlet temperature (objective variable) at the future use is predicted by a turbine outlet temperature model by using a parameter (explanatory variable) in environmental and operational conditions planned for the future use and a rotating speed of a fan (explanatory variable) planned for the future use, and coefficients with respect to the explanatory variables are identified through a learning. In the learning, the coefficients are identified based on a regression learning of the explanatory variables and the objective variable of the turbine outlet temperature model made by using the parameter, the rotating speed of the fan and the turbine outlet temperature at the past use of the gas turbine. 1. A method for predicting a turbine outlet temperature at a future use of a gas turbine based on a past use of the gas turbine , the gas turbine getting an output power by compressing air introduced by a fan and then combusting the air together with fuel , the method comprising:an outlet temperature prediction step for predicting, by a turbine outlet temperature model, the turbine outlet temperature at the future use that is an objective variable by using at least one parameter in environmental and operational conditions planned for the future use of the gas turbine and a rotating speed of the fan planned for the future use as explanatory variables; anda learning step for identifying coefficients with respect to the explanatory variables, the learning step being done every time when a given learning trigger is satisfied,wherein, in the learning step, based on a result of a regression learning of the explanatory variables and the objective variable of the turbine outlet temperature model that is made by using the parameter, the rotating speed of the fan and the turbine outlet temperature at the past use of the gas turbine.2. The method for ...

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Номер записи: 55
31-01-2019 дата публикации

PARTIALLY REDUNDANT ELECTRONIC CONTROL SYSTEM

Номер: US20190032573A1
Автор: GUILLAUMIN Vincent, PRIAT Jerome
Принадлежит: Safran Power Units

An asymmetrical electronic control system for a gas turbine, which is designed to control a set of functions associated with logic input data or data from sensors and associated with output data, in particular for an actuator, the system including a primary electronic control unit configured to process the entire set of functions; a secondary electronic control unit, partially redundant with the primary unit, configured to process only a strict subset of sufficient functions to operate or start the gas turbine in an acceptable degraded mode when the primary unit is faulty; a redundant or main chain selection and switching module for selecting one or other of the primary and secondary units in order to control the gas turbine according to the operating state of the primary unit. 1. An asymmetric electronic control system of a gas turbine configured to control a set of functions associated with logic input data or coming from sensors and associated with output data especially for actuator(s) , said system comprising:a primary electronic control unit, configured to process the entire set of functions,wherein the control system electronic also comprises:a secondary electronic control unit, partially redundant with the primary unit, configured to process only a strict subset of functions sufficient to maintain in operation or start the gas turbine according to a degraded mode acceptable when the primary unit is in default,a selection and switching module for the selection and switching of one or the other of the primary and secondary units for regulating the gas turbine as a function of an operating state of said primary unit.2. The control system according to claim 1 , wherein the strict subset of sufficient functions corresponds to the vital functions of the gas turbine.3. The control system according to claim 1 , wherein the primary unit and the secondary unit are dissimilar in terms of architecture.4. The control system electronic according to claim 1 , wherein the ...

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Номер записи: 56
04-02-2021 дата публикации

Reducing low flight mach number fuel consumption

Номер: US20210033031A1
Автор: Caroline L. Turner
Принадлежит: Rolls Royce PLC

A gas turbine engine for an aircraft, comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine, the first electric machine having a first maximum output power; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine, the second electric machine having a second maximum output power; and an engine controller configured to identify a condition to the effect that the LP turbine is operating in an unchoked regime, and, in response to an electrical power demand being between zero and the first maximum output power, only extracting electrical power from the first electric machine to meet the electrical power demand.

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Номер записи: 57
11-02-2016 дата публикации

METHOD FOR THE COMPUTERIZED CONTROL AND/OR REGULATION OF A TECHNICAL SYSTEM

Номер: US20160040602A1
Автор: Brummel Hans-Gerd, Düll Siegmund, Singh Jatinder P., Sterzing Volkmar, Udluft Steffen
Принадлежит:

The invention concerns a method for the computerized control and/or regulation of a technical system (T). Within the context of the method according to the invention, there is implemented in a preset regulating process (CO CO) an exploration rule (EP) by means of which new, as yet unknown, states (x) of the technical system (T) are started, a simulation model (SM) of the technical system (T) checking whether the actions (a) of the exploration rule (EP) lead to sequential states (x′) lying within predetermined thresholds. Only in that case is the corresponding action (a) performed according to the exploration rule (EP) on the technical system. The method according to the invention enables new states to be explored within the framework of the operation of a technical system, it being ensured through checking of appropriate thresholds that the exploration is carried out imperceptibly and does not lead to incorrect operation of the technical system. The method according to the invention is suitable in particular for controlling or regulating gas turbines or wind turbines. 1. A method for computer-assisted open-loop control , closed-loop control , or open-loop and closed-loop control of a technical system , wherein the open-loop control , the closed-loop control , or the open-loop and closed-loop control carries out , at respective times , actions comprising one or more action variables at the technical system as a function of one or more states of the technical system , comprising in each case one or more state variables , the method comprising:determining, by a predefined regulating method, at respective times, first actions that are to be carried out on the technical system as a function of at least the state of the technical system at the respective time;determining, by at least one exploration rule, one or more second actions to be carried out on the technical system as a function of at least the state of the technical system at the respective time;predicting a set ...

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Номер записи: 58
11-02-2016 дата публикации

METHOD FOR THE COMPUTERIZED CONTROL AND/OR REGULATION OF A TECHNICAL SYSTEM

Номер: US20160040603A1
Автор: Düll Siegmund, Hentschel Alexander, Udluft Steffen
Принадлежит:

The invention concerns a method for the computerized control and/or regulation of a technical system. Within the context of the method according to the invention, an action-selection rule (PO′) is determined which has a low level of complexity and yet is well suited to the regulating and/or control of the technical system, there being used for determination of the action-selection rule (PO′) an evaluation measure (EM) which is determined on the basis of a distance measure and/or a reward measure and/or an action-selection rule evaluation method. The action-selection rule is then used to control and/or regulate the technical system. The method according to the invention has the advantage of the action-selection rule being comprehensible to a human expert. Preferably, the method according to the invention is used for regulating and/or controlling a gas turbine and/or a wind turbine. 1. A method for computerized control , regulation , or control and regulation of a technical system , the method comprising:characterizing a dynamic behavior of the technical system for multiple points in time in each case by a state of the technical system and an action executed on the technical system, wherein a respective action at a respective point in time results in a new state of the technical system at the next point in time;providing, generating, or providing and generating action selection policies, wherein a respective action selection policy specifies an action to be executed at a corresponding point in time on the technical system, in dependence on at least the state of the technical system at the corresponding point in time, and wherein each action selection policy is associated with a complexity measure that describes a complexity of the respective action selection policy that is less than or equal to a predetermined complexity threshold; a distance measure between the respective action selection policy and a predefined optimum action selection policy, wherein decreasing ...

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Номер записи: 59
08-02-2018 дата публикации

APPARATUS AND METHOD FOR DETECTING A THRESHOLD VIBRATION CONDITION IN A GAS TURBINE ENGINE

Номер: US20180038284A1
Автор: BOSSE Alexandre, PATRY Benoit
Принадлежит:

Apparatus and methods for detecting a threshold condition associated with the operation of a gas turbine engine are disclosed. In one embodiment, the method comprises: generating one or more sensor signals associated with an operating parameter of the gas turbine engine and providing the one or more sensor signals to a controller of the gas turbine engine; disturbing the one or more sensor signals provided to the controller in response to the threshold condition being met; and detecting the disturbance in the one or more sensor signals provided to the controller and generating one or more output signals indicative of the detected disturbance. 1. A gas turbine engine comprising:a compressor for pressurizing air;a combustor in which the compressed air is mixed with fuel and ignited for generating a stream of combustion gases;a turbine for extracting energy from the combustion gases;a controller of the gas turbine engine;a sensor operatively coupled to the controller to provide to the controller a sensor signal associated with a parameter of the gas turbine engine; anda vibration-sensitive trigger mounted to the engine for monitoring engine vibration and configured to disturb the sensor signal when a threshold vibration condition is met;the controller configured to detect the disturbance in the sensor signal and generate one or more output signals indicative of the detected disturbance.2. The gas turbine engine as defined in claim 1 , wherein the disturbance comprises a detectible anomaly introduced into a speed sensor signal provided to the controller.3. The gas turbine engine as defined in claim 1 , wherein the disturbance comprises an interruption of a speed sensor signal provided to the controller.4. The gas turbine engine as defined in claim 1 , wherein the vibration-sensitive trigger is configured to cause a temporary disturbance of the sensor signal when a threshold vibration condition is met.5. The gas turbine engine as defined in claim 1 , wherein the ...

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Номер записи: 60
03-03-2022 дата публикации

AIRCRAFT ENGINE

Номер: US20220063792A1
Автор: Freely Brendan Michael, McMahon Michael James, Murrow Kurt David
Принадлежит:

A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch. 1. A method of operating an aircraft engine coupled to a wing of an aircraft comprising:setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.2. The method of claim 1 , wherein the plurality of rotor blades extend at least partially over a top of the wing when in the first position claim 1 , and wherein the plurality of rotor blades extend at least partially below a bottom of the wing when in the second position.3. The method of claim 1 , wherein the top of the wing is a suction side of the wing claim 1 , and wherein the bottom of the wing is a pressure side of the wing.4. The method of claim 1 , further comprising:receiving data indicative of an operating condition of the aircraft engine, of the aircraft, or both, and wherein setting the pitch of the plurality of rotor blades comprises setting the pitch of the plurality of rotor blades in response to the received data indicative of the operating condition of the aircraft engine, of the aircraft, or both.5. The method of claim 4 , wherein the operating condition is a high lift operating condition.6. The method of claim 4 , wherein ...

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Номер записи: 61
03-03-2022 дата публикации

Propulsion system for an aircraft

Номер: US20220063819A1
Автор: Alexis Raquel Nunes, Kurt David Murrow
Принадлежит: General Electric Co

A hybrid propulsion system for an aircraft can include a propulsor assembly having at least one propulsor and a power generation system. The power generation system can include a first power assembly, a second power assembly, a first electric machine, and a second electric machine. The first power assembly can be drivingly coupled to the first electric machine to produce a first amount of electric power. The second power assembly can be drivingly coupled to the second electric machine to produce a second amount of electric power. A controller can be operably coupled to the first power assembly, the first electric machine, or both and to the second power assembly, the second power assembly, or both. The controller can be configured to combine at least a portion of the first and second amount of power for electric transfer to the propulsor assembly.

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Номер записи: 62
03-03-2022 дата публикации

HYBRID ELECTRIC AIRCRAFT ENGINE

Номер: US20220063825A1
Автор: Higgins Craig William, Zatorski Darek Tomasz
Принадлежит:

A method for operating a hybrid electric propulsion system of an aircraft, the hybrid electric propulsion system comprising a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine, the method comprising: operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.

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Номер записи: 63
03-03-2022 дата публикации

IN-FLIGHT HYBRID ELECTRIC ENGINE SHUTDOWN

Номер: US20220063826A1
Автор: Cafaro Stefan Joseph, Gemin Paul Robert, Hiett David Alexander, McQuiston Robert Jon, Ostdiek David Marion, Rambo Jeffrey Douglas
Принадлежит:

A method for operating a hybrid-electric propulsion system of an aircraft is provided. The hybrid-electric propulsion system includes a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or low pressure system. The method includes receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine. 1. A method for operating a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a gas turbine engine having a high pressure system , a low pressure system , and an electric machine coupled to one of the high pressure system or low pressure system , the method comprising:receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; andadding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.2. The method of claim 1 , wherein receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine comprises receiving data indicative of an actual in-flight shutdown of the gas turbine engine.3. The method of claim 2 , wherein adding power to the gas turbine engine includes adding power to the gas turbine engine immediately after receiving data indicative of the actual in-flight shutdown of the gas turbine engine.4. The method of claim 2 , further includinginitiating a re-start of the engine after an amount of time after receiving data indicative of the actual in-flight shutdown of a gas turbine engine, wherein adding power to the gas turbine engine includes adding power to the gas turbine engine substantially continuously at least until ...

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Номер записи: 64
03-03-2022 дата публикации

SYSTEMS AND METHODS FOR DETERMINING AND/OR CONTROLLING MOTOR THRUST AND ENGINE THRUST IN A PARALLEL HYBRID AIRCRAFT

Номер: US20220065174A1
Автор: Chapman Alex J., Savagian Peter J.
Принадлежит: Ampaire, Inc.

A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft. One or more sensors may be configured to monitor one or more flight parameters to generate sensor information. User input including one or more pilot estimates may be received. The sensor information may be obtained. A performance thrust ratio may be calculated based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model. The performance thrust ratio may be used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight. A first thrust setting for the motor and/or a second thrust setting for the engine may be determined based on the performance thrust ratio. 1. A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft , the system comprising:one or more sensors configured to monitor one or more flight parameters to generate sensor information; receive user input, the user input including one or more pilot estimates;', 'obtain the sensor information;', 'calculate a performance thrust ratio based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model, wherein the performance thrust ratio is used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight;', 'determine a first thrust setting for the motor and a second thrust setting for the engine based on the performance thrust ratio., 'one or more hardware processors configured by machine-readable instructions to23. The system of claim 1 , wherein the one or more hardware processors are further configured by machine-readable instructions to:actuate the motor according to the first thrust setting; andactuate the engine according to the second thrust setting.3. The system of claim 1 , wherein the one or more sensors are configured to monitor the one or more flight parameters on ...

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Номер записи: 65
03-03-2022 дата публикации

Compressor stall mitigation

Номер: US20220065175A1
Автор: Paul Robert Gemin, Robert Jon Mcquiston, Stefan Joseph CAFARO
Принадлежит: General Electric Co

A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising a gas turbine engine having a compressor and an electric machine coupled to the compressor, the method comprising: sensing data indicative of a pressure within the compressor of the gas turbine engine; determining conditions within the compressor are within a threshold of a stall limit for the compressor based at least in part on the sensed data indicative of the pressure within the compressor of the gas turbine engine; and modifying a torque of the compressor using the electric machine in response to determining the conditions within the compressor are within the threshold of the stall limit for the compressor to reduce a risk of compressor stall.

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Номер записи: 66
13-02-2020 дата публикации

DISTRIBUTED CONTROL AND MONITORING SYSTEM FOR MULTIPLE PLATFORMS

Номер: US20200047902A1
Автор: Bingham Nathan, Elliott Michael T., McPherson James, Ruff Chris, Terbrock Andrew, Wiegand Kerry
Принадлежит: Rolls-Royce Corporation

Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor. 1. A distributed control system for a gas turbine engine wherein an operating environment of the gas turbine engine is harsh and an operating environment outside of the gas turbine engine is benign , the control system comprising: a first processor; and', 'a first network interface device operably coupled to the first processor;, 'an input/output (I/O) module attached to the gas turbine engine comprisingat least one sensor operably coupled to the I/O module providing a signal to the first processor based on sensed conditions of the gas turbine engine;at least one actuator operably coupled to the I/O module and controlled by the first processor; and a second processor with higher processing power than the first processor; and', 'a second network interface device operably coupled to the second processor, wherein the second network interface device and the first network interface device provide a communication network between the first processor and the second processor, wherein the second processor executes gas turbine engine safety ...

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Номер записи: 67
13-02-2020 дата публикации

DISTRIBUTED CONTROL AND MONITORING SYSTEM FOR MULTIPLE PLATFORMS

Номер: US20200047903A1
Автор: Bingham Nathan, Elliott Michael T., McPherson James, Ruff Chris, Terbrock Andrew, Wiegand Kerry
Принадлежит: Rolls-Royce Corporation

Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor. 1. A distributed control system for a gas turbine engine wherein an operating environment of the gas turbine engine is harsh and an operating environment outside of the gas turbine engine is benign , the gas turbine engine comprising: a first processor; and', 'a first network interface device operably coupled to the first processor;, 'an input/output (I/O) module attached to the gas turbine engine comprisingat least one sensor operably coupled to the I/O module providing a signal to the first processor based on sensed conditions of the gas turbine engine;at least one actuator operably coupled to the I/O module and controlled by the first processor; and a second processor with higher processing power than the first processor; and', 'a second network interface device operably coupled to the second processor, wherein the second network interface device and the first network interface device provide a communication network between the first processor and the second processor, wherein the first processor executes gas turbine engine ...

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Номер записи: 68
13-02-2020 дата публикации

DISTRIBUTED CONTROL AND MONITORING SYSTEM FOR MULTIPLE PLATFORMS

Номер: US20200047904A1
Автор: Bingham Nathan, Elliott Michael T., McPherson James, Ruff Chris, Terbrock Andrew, Wiegand Kerry
Принадлежит: Rolls-Royce Corporation

Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor. 1. A distributed control system for a gas turbine engine , the gas turbine engine defining during operation a benign environment associated with at least one location and a harsh environment associated with at least another location , the control system comprising: a first processor; and', 'a first network interface device operably coupled to the first processor;, 'an input/output (I/O) module attached to the gas turbine engine comprisingat least one sensor operably coupled to the I/O module providing a signal to the first processor, the signal based on sensed conditions of the gas turbine engine;at least one actuator operably coupled to the I/O module and controlled by the first processor; and a second processor with higher processing power than the first processor; and', 'a second network interface device operably coupled to the second processor, wherein the second network interface device and the first network interface device provide a communication network between the first processor and the second processor, wherein the second ...

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Номер записи: 69
25-02-2021 дата публикации

POWER SYSTEM FOR ROTARY WING AIRCRAFT

Номер: US20210054782A1
Автор: Hanrahan Paul R., Kupratis Daniel Bernard
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a low speed spool; a first compressor, a turbine and a generator rotationally coupled via the low speed spool; a high speed spool; and a second compressor and a motor rotationally coupled via the high speed spool. 1. A gas turbine engine , comprising:a low speed spool;a first compressor, a turbine and a generator rotationally coupled via the low speed spool;a high speed spool; anda second compressor and a motor rotationally coupled via the high speed spool.2. The gas turbine engine of claim 1 , wherein the motor is configured to receive power from the generator to drive the second compressor.3. The gas turbine engine of claim 2 , further comprising a storage device configured to drive the second compressor.4. The gas turbine engine of claim 2 , wherein the first compressor is a low pressure compressor and the second compressor is a high pressure compressor claim 2 , the high pressure compressor configured to compress air received from the low pressure compressor when driven by the motor.5. The gas turbine engine of claim 1 , further comprising an intra-engine power control configured to direct power from the generator to the motor.6. The gas turbine engine of claim 5 , further comprising an intra-engine connection configured to electrically couple the generator and the motor.7. A power system for a rotary wing aircraft claim 5 , comprising: a first low speed spool,', 'a first low pressure compressor, a first turbine and a first generator rotationally coupled via the first low speed spool,', 'a first high speed spool, and', 'a first high pressure compressor and a first motor rotationally coupled via the first high speed spool; and, 'a first engine having'} a second low speed spool,', 'a second low pressure compressor, a second turbine and a second generator rotationally coupled via the second low speed spool,', 'a second high speed spool, and', 'a second high pressure ...

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Номер записи: 70
25-02-2021 дата публикации

AUGMENTED DRIVE OF COMPRESSORS VIA DIFFERENTIAL AND MULTISTAGE TURBINE

Номер: US20210054788A1
Автор: Hanrahan Paul R., JR. Arthur M., Kupratis Daniel Bernard, Salve
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine. 1. A method of distributing power within a gas turbine engine , comprising:driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool;driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; andselectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.2. The method of claim 1 , wherein the selectively applying the auxiliary input power includes applying a first input power to a first motor-generator connected to the high pressure compressor spool.3. The method of claim 1 , wherein the ...

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Номер записи: 71
23-02-2017 дата публикации

Method for operating a power plant

Номер: US20170051681A1
Автор: Darrel Shayne Lilley, Manuel Arias Chao, Wilhelm Reiter
Принадлежит: General Electric Technology GmbH

Disclosed is a method for operating a power plant. The method includes providing a power target setpoint to a power plant controller; dependent on said power target setpoint, determining a setpoint of at least one first power plant operation parameter; operating the power plant at a set power output; and and with the at least one first operation parameter adjusted to the setpoint of the operation parameter, applying a measurement to determine an actual value of at least one second operation parameter. The method further includes applying a theoretical power plant model to determine an expected value of the at least one second operation parameter; comparing the expected value of the at least one second operation parameter and the measured value of the at least one second operation parameter; and applying a calibration loop for the theoretical power plant model.

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Номер записи: 72
15-05-2014 дата публикации

HEAT EXCHANGE ARRANGEMENT

Номер: US20140131027A1
Автор: Chir Adam Philip
Принадлежит:

A heat exchange arrangement () for a gas turbine engine (). The arrangement () comprises a first conduit () for an engine component cooling fluid and a second conduit () for a second fluid. The arrangement further comprises a heat exchange portion () in which fluids flowing through the first and second conduits () are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion (). The arrangement comprises a temperature sensor () configured to sense a temperature of one of the fluids after said fluid has passed through the heat exchange portion () and a controller (). The controller () is configured to control the valve () in response to a rate of change of the temperature with respect to time of the fluid sensed by the temperature sensor (). 1. A heat exchange arrangement for a gas turbine engine , the heat exchange arrangement comprising:a first conduit for an engine component cooling fluid and a second conduit for a second fluid,a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship;a valve configured to moderate the mass flow rate of one of the fluids through the heat exchange portion;a temperature sensor configured to sense a temperature of one of the fluids after said fluid has passed through the heat exchange portion; anda controller, wherein the controller is configured to control the valve in response to a rate of change of the temperature with respect to time of the fluid sensed by the temperature sensor.2. A heat exchange arrangement according to claim 1 , wherein the controller is configured to actuate the valve when the rate of change of the temperature with respect to time of the fluid sensed by the temperature sensor is above a predetermined value.3. A heat exchange arrangement according to claim 1 , wherein the second fluid comprises any of air claim 1 , fuel or engine oil.4. A heat ...

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Номер записи: 73
14-02-2019 дата публикации

GAS TURBINE GENERATOR TORQUE DC TO DC CONVERTER CONTROL SYSTEM

Номер: US20190052208A1
Автор: Noderer Keith D.
Принадлежит: Rolls-Royce North American Technologies Inc.

A system includes a first controller configured to control a gas turbine to operate at a constant speed set point and a variable torque output to drive a generator. A DC to DC converter may operate as a load on a power source bus supplied by the generator. A second controller may limit a rate of change of the DC output power of the DC to DC converter during intermittent supply of a transient step change load subsequent to receipt of a transient load control signal. The transient load control signal is anticipatory of application of the transient step change load to the load bus. The rate of change is limited by the second controller to maintain the variable torque of the gas turbine below a predetermined threshold as a load ramp rate of the DC to DC converter changes on the power source bus. 1. A method comprising:controlling a gas turbine to rotate at a constant rated speed and a variable torque to drive a generator in accordance with a load being supplied by the generator;outputting electric power with the generator to a power source bus;energizing a DC to DC converter coupled to the power source bus as at least part of the load being supplied by the generator;controlling a level of a DC output power output by the DC to DC converter on a load bus;supplying the load bus with DC power supplied from an energy storage device;receiving a transient load control signal indicative of an anticipated future occurrence of a step change load event on the load bus;receiving the step change load event on the load bus after receipt of the transient load control signal;adjusting the level of the DC output power of the DC to DC converter in response to the step change load event; andapplying a constraint on a rate of change of the level of the DC output power of the DC to DC converter, the constraint applied based on the transient load signal to maintain the variable torque of the generator below a predetermined threshold as a load ramp rate of the DC to DC converter changes on ...

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Номер записи: 74
10-03-2022 дата публикации

Flow measurement for a gas turbine engine

Номер: US20220074770A1
Автор: Kevin Todd LOWE, Maurice BRISTOW, Peter Loftus, Vasileios KYRITSIS
Принадлежит: Virginia Polytechnic Institute and State University

A flow machine having a flow passage and an air flow measurement system comprising a plurality of acoustic sensors. The acoustic sensors comprise at least one acoustic transmitter configured to transmit an acoustic waveform through the airflow passing through the flow passage to an acoustic receiver. At least one of the acoustic sensors is rotatable relative to one or more other acoustic sensor.

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Номер записи: 75
01-03-2018 дата публикации

PLANT CONTROL APPARATUS, PLANT CONTROL METHOD AND POWER PLANT

Номер: US20180058321A1
Автор: SAWATA Kazuna, TOBO Masayuki, YOKOYAMA Kumiko
Принадлежит: KABUSHIKI KAISHA TOSHIBA

In one embodiment, a plant control apparatus controls a power plant including a combustor configured to burn fuel to generate a combustion gas, a gas turbine driven by the combustion gas from the combustor, a heat recovery steam generator configured to use heat of an exhaust gas from the gas turbine to generate steam, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus includes a gas turbine controller configured to control an output value of the gas turbine to a second output value that is larger than a first output value and depends on atmospheric temperature and then control the output value of the gas turbine to the first output value. The apparatus further includes a steam turbine controller configured to start up the steam turbine while the output value of the gas turbine is controlled to the first output value. 1. A plant control apparatus configured to control a power plant comprising:a combustor configured to burn fuel with air to generate a combustion gas;a gas turbine configured to be driven by the combustion gas from the combustor;a heat recovery steam generator configured to use heat of an exhaust gas from the gas turbine to generate steam; anda steam turbine configured to be driven by the steam from the heat recovery steam generator,the plant control apparatus comprising:a gas turbine controller configured to control an output value of the gas turbine to a second output value that is larger than a first output value and depends on an atmospheric temperature and then control the output value of the gas turbine to the first output value; anda steam turbine controller configured to start up the steam turbine while the output value of the gas turbine is controlled to the first output value.2. The apparatus of claim 1 , wherein the gas turbine controller controls the output value of the gas turbine based on a temperature of the exhaust gas so as to control the output value of the gas turbine to the second output ...

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Номер записи: 76
01-03-2018 дата публикации

Systems and methods to improve shut-down purge flow in a gas turbine system

Номер: US20180058337A1
Автор: David August Snider, Lewis Berkley Davis, Jr., Michael Joseph Alexander
Принадлежит: General Electric Co

A system includes a controller including a memory storing instructions to perform operations of a power generation system and a processor that executes the instructions. The instructions cause the controller to control purging fluid flow to an inlet of a gas turbine, an exhaust of the gas turbine, or a combustion section of the gas turbine. The instructions cause the controller to receive a first temperature at the inlet, a rotational speed of the gas turbine, and a purging fluid flow rate. The instructions cause the controller to calculate an exhaust flow rate of the system based on at least the first temperature, the rotational speed, and the purging fluid flow rate. The instructions cause the controller to control the system to isolate a fuel source from the gas turbine at a portion of normal operating speed sufficient to achieve a purging volume during coast down.

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Номер записи: 77
01-03-2018 дата публикации

Hazgas system with acoustic wave sensors

Номер: US20180058972A1
Автор: David TRAYHAN, Hua Zhang, Manuel Cardenas, JR.
Принадлежит: General Electric Co

A gas monitoring system for monitoring gas leaks from a gas turbine engine disposed within a gas turbine enclosure includes a controller including a processor and a memory communicatively coupled to the processor. The memory stores instructions which when executed by the processor perform operations including obtaining one or more operational parameters associated with a gas turbine system having the gas turbine engine from one or more sensors during operation of the gas turbine engine. The operations also include utilizing a gas leakage monitoring model to monitor for gas leaks within the gas turbine enclosure and to generate a gas index indicative of a severity of a gas leak within the gas turbine enclosure based on the one or more operational parameters. The operations further include outputting the index.

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Номер записи: 78
04-03-2021 дата публикации

SYSTEM AND METHOD FOR SYNCHROPHASING AIRCRAFT ENGINES

Номер: US20210062726A1
Автор: "CARON-LECUYER Alexis", COLAVINCENZO Stephen, KATHIRCHELVAN Thineshan
Принадлежит:

Systems and method for synchrophasing aircraft engines are disclosed. One method comprises receiving data indicative of a sensed vibration level associated with a first aircraft engine and a second aircraft engine operating at a substantially same operating speed and commanding one or more momentary changes in operating speed of the second aircraft engine until the sensed vibration level substantially reaches a target vibration level. The momentary changes in operating speed of the second aircraft engine is commanded irrespective of phase information associated with imbalances of the first and second aircraft engines. 1. A method for synchrophasing aircraft engines , the method comprising:receiving data indicative of a sensed vibration level associated with a first aircraft engine and a second aircraft engine operating at a substantially same operating speed; andcommanding one or more momentary changes in operating speed of the second aircraft engine until the sensed vibration level substantially reaches a target vibration level, the momentary changes in operating speed of the second aircraft engine being commanded irrespective of phase information associated with imbalances of the first and second aircraft engines.2. The method as defined in claim 1 , wherein each of the one or more momentary changes in operating speed of the second aircraft engine is a respective momentary increase in rotational speed of the second aircraft engine.3. The method as defined in claim 1 , wherein the sensed vibration level comprises a summation of vibrations from the first aircraft engine and the second aircraft engine.4. The method as defined in claim 1 , wherein the target vibration level is based on a sensed vibration level minimum associated with the first and second aircraft engines.5. The method as defined in claim 1 , to comprising:commanding an operating speed difference between the first and second aircraft engines to induce beats of a predefined period in resultant vibration ...

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Номер записи: 79
03-03-2016 дата публикации

Provision of negative control power by a gas turbine

Номер: US20160064933A1
Автор: Günther Ebner, Uwe Lenk
Принадлежит: SIEMENS AG

A method for providing negative control power for an electrical supply and/or transmission network by means of the operation of a gas turbine, includes the following steps: a dynamo-electric machine of the gas turbine is supplied with electric power for motor operation from the supply and/or transmission network; the electrical input power is regulated or controlled by the motor operation on the basis of a network signal from the supply and/or transmission network to which the gas turbine is connected; and an operating parameter of the gas turbine for motor operation is altered as a result of this regulation or control for the purpose of deliberately increasing the electrical input power from the supply and/or transmission network.

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Номер записи: 80
29-05-2014 дата публикации

Engine Compressor Wash System

Номер: US20140144151A1
Автор: Bifulco Anthony R.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine includes: a compressor; a combustor downstream of the compressor along a gaspath; a turbine downstream of the combustor along the gaspath; a plurality of wash nozzles having outlets along the gaspath; and at least one inlet fitting coupled to the wash nozzles to bound a wash flowpath from an inlet port of the at least one inlet fitting to said outlets of said nozzles. The plurality of stages include: a stage upstream of blades of one compressor section; and another stage between said blades of one compressor section and blades of another compressor section. 1. A gas turbine engine comprising:a compressor;a combustor downstream of the compressor along a gaspath; anda turbine downstream of the combustor along the gaspath, the engine further comprising:a plurality of wash nozzles having outlets along the gaspath; andat least one inlet fitting coupled to the wash nozzles to bound a wash flowpath from an inlet port of the at least one inlet fitting to said outlets of said nozzles, wherein: a stage upstream of blades of one compressor section; and', 'another stage between said blades of one compressor section and blades of another compressor section., 'said plurality of stages include2. The engine of wherein:the nozzles extend within associated airfoils, the airfoils radially extending between inboard and outboard boundaries of the gaspath.3. The engine of wherein:there are no further stages of said nozzles.4. The engine of wherein:said another stage is formed along an intermediate case.5. The engine of wherein:the nozzles comprise a cast-in leg of a strut.6. The engine of wherein:the cast-in leg is along a trailing edge wall of the strut aft of a central cavity.7. The engine of wherein:the fitting is located between an outboard wall of the gaspath and an access panel.8. The engine of wherein:the engine is a turbofan engine; andthe access panel is along an inboard boundary of a bypass flowpath.9. The engine of wherein:the nozzle outlets are positioned ...

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Номер записи: 81
28-02-2019 дата публикации

VIBRATION CONTROL FOR A GAS TURBINE ENGINE

Номер: US20190063747A1
Автор: Mollmann Daniel Edward
Принадлежит:

A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine. 1. A method for operating a gas turbine engine comprising:receiving data indicative of an operational vibration within a section of the gas turbine engine; andproviding electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.2. The method of claim 1 , wherein the section of the gas turbine engine is a combustion section of the gas turbine engine.3. The method of claim 2 , wherein receiving data indicative of the operational vibration within the combustion section of the gas turbine engine comprises receiving data from one or more accelerometers within the combustion section of the gas turbine engine.4. The method of claim 3 , wherein the one or more accelerometers are configured to measure a vibration of one or more of a combustor liner of a combustor within the combustion section of the gas turbine engine claim 3 , a fuel nozzle within the combustion section of the gas turbine engine claim 3 , a fuel manifold within the combustion section of the gas turbine engine claim 3 , or a combustor case within the combustion section of the gas turbine engine.5. The method of claim 1 , wherein receiving data indicative of the operational vibration within the section of the gas turbine engine comprises receiving data indicative of at least one of a frequency claim 1 , an amplitude claim 1 , or a phase of the operational vibration.6. The method of claim 5 , wherein providing electrical power ...

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Номер записи: 82
27-02-2020 дата публикации

COMPRESSED AIR STORAGE POWER GENERATION DEVICE

Номер: US20200063658A1
Автор: KUBO Yohei, MATSUKUMA Masaki, SAKAMOTO Kanami, SARUTA Hiroki, Toshima Masatake
Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

The compressed air energy storage power generation device includes a third heat exchanger and fourth heat exchangers. The third heat exchanger performs heat exchange between the air exhausted from the expander and the second heating medium to cool the second heating medium. The fourth heat exchanger performs heat exchange between the second heating medium cooled by the third heat exchanger and at least one of the lubricating oil to be supplied to the compressor or the first heating medium to be supplied to the first heat exchanger to cool the lubricating oil or the first heating medium. 1. A compressed air energy storage power generation device comprising:an electric motor to be driven by electric power generated by renewable energy;a compressor configured to be driven by the electric motor and to compress air;a pressure accumulator configured to store compressed air compressed by the compressor;an expander to be driven by the compressed air to be supplied from the pressure accumulator;a generator mechanically connected to the expander;a first heat exchanger configured to perform heat exchange between the compressed air to be supplied from the compressor to the pressure accumulator and a first heating medium to cool the compressed air and to heat the first heating medium;a first heat storage configured to store the first heating medium heated by the first heat exchanger;a second heat exchanger configured to perform heat exchange between the compressed air to be supplied from the pressure accumulator to the expander and the first heating medium to be supplied from the first heat storage to heat the compressed air and to cool the first heating medium;a third heat exchanger configured to perform heat exchange between air exhausted from the expander and a second heating medium to heat the air and to cool the second heating medium; anda fourth heat exchanger configured to perform heat exchange between the second heating medium cooled by the third heat exchanger and at ...

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Номер записи: 83
17-03-2016 дата публикации

METHOD AND SYSTEM TO PROTECT A SURFACE FROM CORROSIVE POLLUTANTS

Номер: US20160076455A1
Автор: Davis Dale Joel, Ekanayake Sanji, Orenstein Robert Michael, Scipio Alston Ilford, Smith Raub Warfield
Принадлежит:

Disclosed herein are systems and methods for protecting a surface from corrosive pollutants. A method includes detecting airborne corrosive pollutants proximate to a surface using at least one sensor adapted to detect a concentration of the airborne corrosive pollutants and/or one or more types of airborne corrosive pollutants, the concentration of the airborne corrosive pollutants being an instantaneous concentration value or a time-weighted-integrated concentration value; selecting a fluid to deliver to at least a portion of the surface based upon a predetermined type and/or concentration of the airborne corrosive pollutants detected by the at least one sensor; and initiating a fluid treatment to deliver the selected fluid such that the selected fluid contacts the at least a portion of the surface. 1. A method comprising:detecting airborne corrosive pollutants proximate to a surface using at least one sensor adapted to detect a concentration of the airborne corrosive pollutants and/or one or more types of airborne corrosive pollutants, the concentration of the airborne corrosive pollutants being an instantaneous concentration value or a time-weighted-integrated concentration value;selecting a fluid to deliver to at least a portion of the surface based upon a predetermined type and/or concentration of the airborne corrosive pollutants detected by the at least one sensor; andinitiating a fluid treatment to deliver the selected fluid such that the selected fluid contacts the at least a portion of the surface.2. The method of claim 1 , wherein the surface is a turbomachine surface.3. The method of claim 1 , wherein the surface is a gas turbine engine surface or a gas turbine engine compressor surface.4. The method of claim 1 , wherein the airborne corrosive pollutants are within a duct that is fluidly connected with a compressor of a gas turbine engine.5. The method of claim 1 , wherein the airborne corrosive pollutants proximate the surface comprise sulfur dioxide ...

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Номер записи: 84
24-03-2022 дата публикации

System and method for determining high oil consumption in gas turbine engine

Номер: US20220090515A1
Автор: Daniel CUTTING, Dongfeng Shi, James A COOKE, Peter A BEECROFT
Принадлежит: Rolls Royce PLC

A system and a method for determining a high oil consumption in a gas turbine engine of an aircraft are provided. The method includes determining one or more engine and aircraft conditions. The one or more engine and aircraft conditions includes at least one of an oil quantity, an oil temperature, an oil pressure, an engine speed, an aircraft altitude, and an aircraft attitude. The method further includes determining a trend in oil conditions based on at least the one or more engine and aircraft conditions. The trend in oil conditions provides at least one of a rate of consumption of oil or a time duration of remaining oil. The method further includes determining the high oil consumption based on a comparison of the trend in oil conditions with a threshold or a comparison model.

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Номер записи: 85
05-03-2020 дата публикации

Efficiency-based machine control

Номер: US20200072130A1
Автор: Alan Smith
Принадлежит: Rolls Royce Corp

A system can include a gas turbine and a processing system. The gas turbine can include a compressor coupled to a turbine through a shaft. The processing system can be configured to: automatically transition an operating condition of the system through a plurality of operating states; determine an efficiency of the system at each of a plurality of the operating states; for each of the plurality of operating states: select a future operating state of the system based on the determined efficiency of the current operating state.

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Номер записи: 86
19-03-2015 дата публикации

SYSTEM AND METHOD FOR CONTROLLING OPERATION OF A GAS TURBINE BASED POWER PLANT

Номер: US20150081121A1
Автор: Balkcum, III James Tyson, Jordan, JR. Harold Lamar, Morgan Rex Allen, VanTassel Brad Wilson, Watts Stephen R.
Принадлежит:

A system for controlling a gas turbine power plant includes a plurality of sensors configured to transmit signals indicative of one or more operating parameters of the gas turbine, and a control system in electronic communication with each sensor. The control system is configured to compute cumulative wear for one or more hardware components of the gas turbine based at least in part on the signals. Instructions are inputted into the control system which indicates a desired operational mode for the gas turbine. The control system may then compute a hardware consumption rate based at least in part on the cumulative wear. The hardware consumption rate may then be displayed to an operator via a display device. The operator may use the hardware consumption rate to determine potential economic impact of operating the gas turbine at the desired operational mode. 1. A system for controlling a gas turbine power plant , comprising:a plurality of sensors, each sensor being configured to sense and communicate a signal indicative of an operating parameter of the gas turbine; receive the signals from the sensors;', 'compute cumulative wear for one or more hardware components of the gas turbine based at least in part on one or more of the signals via the computing device;', 'receive input instructions selecting a desired operational mode for the gas turbine;', 'compute a hardware consumption rate based at least in part on the cumulative wear and the desired operation mode via the computing device; and', 'display the hardware consumption rate to an operator via a display device that is in electronic communication with the control system., 'a control system including a computing device in electronic communication with each sensor of the plurality sensors, wherein the control system is configured to2. The system as in claim 1 , wherein the plurality of sensors includes at least one of a temperature sensor claim 1 , a pressure sensor and a humidity sensor.3. The system as in claim 1 , ...

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Номер записи: 87
19-03-2015 дата публикации

ADAPTIVE REMAINING USEFUL LIFE BALANCING CONTROL SYSTEM AND METHOD FOR MULTI-ENGINE SYSTEMS

Номер: US20150081193A1
Автор: Gordon Grant, Gorelik Michael, Ling Richard, Peralta-Duran Hector Alonso
Принадлежит: HONEYWELL INTERNATIONAL INC.

A system and method of adaptively managing a plurality of engines in a multi-engine system, where each engine comprises hot gas components and non-hot gas components, and each engine exhibits a performance margin and a remaining useful life, includes continuously, and in real-time, determining a plurality of different degradation mechanisms for each of the plurality of engines, and continuously, and in real-time, determining which of the determined degradation mechanisms is most limiting. The engines are controlled, based on the most limiting degradation mechanism, in a manner that the remaining useful lives of each engine are substantially equal. The plurality of different degradation mechanisms of each engine are determined based on the engine performance margin, modeled failure predictions of the hot gas components, and modeled failure predictions of the non-hot gas components. 1. A method of adaptively managing a plurality of engines in a multi-engine system , each engine comprising hot gas components and non-hot gas components , and each engine exhibiting a performance margin and a remaining useful life , the method comprising the steps of:continuously, and in real-time, determining a plurality of different degradation mechanisms for each of the plurality of engines;continuously, and in real-time, determining which of the determined degradation mechanisms is most limiting; andcontrolling the plurality of engines, based on the most limiting degradation mechanism, in a manner that the remaining useful lives of each engine are substantially equal, (i) the engine performance margin,', '(ii) modeled failure predictions of the hot gas components, and', '(iii) modeled failure predictions of the non-hot gas components., 'wherein the plurality of different degradation mechanisms of each engine are determined based on2. The method of claim 1 , wherein the step of controlling the plurality of engines comprises selectively controlling the engines to create a load imbalance ...

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Номер записи: 88
05-06-2014 дата публикации

SYSTEM AND METHOD FOR GAS TURBINE OPERATION

Номер: US20140156165A1
Автор: Ewens David Spencer, Huey John Rogers, Lindenmuth Marc Gavin
Принадлежит: GENERAL ELECTRIC COMPANY

A system includes a controller configured to control one or more parameters of a gas turbine engine based on a feedback and a predicted lifespan of one or more components of the gas turbine engine to substantially maintain at least one of power output or heat rate above a threshold level in response to degradation or fouling of the gas turbine engine. 1. A system , comprising:a controller configured to control one or more parameters of a gas turbine engine based on a feedback and a predicted lifespan of one or more components of the gas turbine engine, wherein the controller comprises instructions disposed on a non-transitory, machine readable medium, wherein the instructions are configured to:operate the gas turbine engine;determine a base power output, a base heat rate, or a combination thereof based on new and clean operation of the gas turbine engine at base load;obtain a corrective parameter;determine a target power output, a target heat rate, or a combination thereof based at least in part on the base power output, the base heat rate, or a combination thereof and the corrective parameter;monitor a power output, a heat rate, or a combination thereof of the gas turbine engine;compare the power output to the target power output, compare the heat rate to the target heat rate, or a combination thereof; andadjust the one or more parameters of the gas turbine engine such that a difference between the power output and the target power output, the heat rate and the target heat rate, or a combination thereof is less than a threshold value, wherein the difference between the power output and the target power output, the heat rate and the target heat rate, or the combination thereof is caused at least partially by degradation and/or fouling of the gas turbine engine.2. The system of claim 1 , wherein at least one of the power output or heat rate is within approximately 10% of a base output value claim 1 , wherein the base output value is based on a base output value of ...

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Номер записи: 89
31-03-2022 дата публикации

AIRCRAFT PERFORMANCE OPTIMIZATION BASED ON ENGINE PERFORMANCE MONITORING

Номер: US20220097864A1
Автор: Adibhatla Sridhar, Baladi Mehdi M., Collins Kathleen K., ESPOSITO Aniello
Принадлежит:

A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine. The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft. 1. A computer-readable , non-transitory storage medium storing instructions that , when executed by a digital controller of an aircraft comprising a turbine engine causes the aircraft to execute a method comprising:receiving during a flight of the aircraft, at the digital controller, a data from an engine sensor of the turbine engine;determining at the digital controller, based on the data received from the engine sensor, that a load on the engine exceeds an allowed maximum operating power; andupon determining that the load on the engine exceeds the allowed maximum operating power, issuing a control command to an aircraft system other than the engine—ASOTE to reduce a power load on the engine.2. The computer-readable claim 1 , non-transitory storage medium of claim 1 , wherein the method further comprises:issuing a control command to the ASOTE to reduce, to modify, or to limit an operation of the ASOTE, wherein the reduced, modified, or limited ASOTE operation reduces the electrical load on an electrical power generator which is driven by the engine.3. The computer-readable claim 1 , non- ...

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Номер записи: 90
23-03-2017 дата публикации

METHOD AND SYSTEM FOR THERMAL EXPANSION COMPENSATION IN HEATED FLOW CHARACTERIZATION

Номер: US20170082032A1
Автор: Claussen Heiko, DeSilva Upul P.
Принадлежит:

Techniques for a chamber, such as gas turbine engine (), surrounding a heated fluid include a sensor () mounted in a first wall () of the chamber to detect phenomenon inside the chamber and a processor (). The processor is in electrical communication with the sensor and is configured to receive first data, determine a first temperature of the first wall, determine a current path length, determine properties of the fluid flow, and operate a device based on the properties. First data indicates a value of the phenomenon along a path between the first wall and a different wall of the chamber. The current path length () is based on a nominal path length () and thermal expansion of the first wall due to the first temperature. The property of fluid flow in the chamber is based on the first data and the current path length. 1. A system comprising:a chamber configured to surround a heated fluid;a sensor mounted in a first wall of the chamber to detect a phenomenon in the chamber;a device affected by a property of the heated fluid; and receiving from the sensor first data that indicates a value for the phenomenon along a path through the chamber between the first wall and a different wall of the chamber,', 'determining a first temperature of the first wall;', 'determining a current path length of the path based at least in part on a nominal path length for a nominal temperature different from the first temperature and thermal expansion of the first wall due to the first temperature;', 'determining a property of fluid flow in the chamber based on the first data and the current path length of the path; and', 'operating the device based on the property of fluid flow in the chamber., 'a processor in electrical communication with the sensor, the processor configured to perform at least the steps of2. A system as recited in claim 1 , wherein.the chamber is at least one of a combustor in a gas turbine engine or an exhaust diffuser in a gas turbine engine;the sensor is an acoustic ...

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Номер записи: 91
31-03-2022 дата публикации

SYSTEM FOR CONTROLLING A TURBINE

Номер: US20220099032A1
Автор: Crom Elden W., Crowe David Keith
Принадлежит:

A system for controlling a turbine is disclosed. The system includes a turbine control fuel governor that has a plurality of VCPIDs operating in parallel with one another. Each VCPID is associated with a respective turbine parameter and one or more external parameters. Each VCPID incorporates feedback from the parallel operating VCPIDs to feed an integral term of a current VCPID in the following manner: a previous derivative gain and a previous proportional gain are summed and subtracted from a selected output for the turbine to yield a result, and the result is input to an integral gain portion of the current VCPID. 1. A system for controlling a turbine , comprising:a closed loop turbine control fuel governor comprising a plurality of VCPID control loops operating in parallel with one another, each VCPID control loop being associated with a respective turbine parameter and one or more external parameters,wherein each VCPID control loop incorporates feedback from the parallel operating VCPID control loops to feed an integral term of a current VCPID control loop in the following manner: a previous derivative gain and a previous proportional gain are summed and subtracted from a selected output for the turbine to yield a result, and the result is input to an integral gain portion of the current VCPID control loop.2. The system of claim 1 , wherein each VCPID control loop includes a VCPID output that is fed to a minimum select function.3. The system of claim 2 , wherein the minimum select function selects a fuel command based on the VCPID outputs claim 2 , the fuel command being a command that requires the least amount of fuel to not exceed a setpoint to the parallel VCPID control loops.41. The system of claim 1 , wherein one VCPID control loop is connected to the core engine speed N.52. The system of claim 1 , wherein one VCPID control loop is connected to the power turbine speed N.6. The system of claim 1 , wherein one or more VCPID control loops are connected to ...

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Номер записи: 92
19-06-2014 дата публикации

Systems and Methods for Controlling Mode Transfers of a Combustor

Номер: US20140165581A1
Автор: Healy Timothy Andrew, Terry Jason Charles
Принадлежит: GENERAL ELECTRIC COMPANY

Systems and methods for controlling mode transfers of a turbine combustor are provided. According to one embodiment, a system may include a controller to control a combustor, and a processor communicatively coupled to the controller. The processor may be configured to receive current operating conditions, target operating limits, and combustor transfer functions. The combustor transfer functions may be evaluated to estimate operating limits associated with one or more combustion modes under the current operating conditions. The estimated operating limits associated with the one or more combustor modes may be compared to the target operating limits, and, based on the comparison, at least one of the combustion modes may be selected. The combustor may then be selectively transferred to the selected combustion mode. 1. A method for controlling mode transfers of a combustor , the method comprising:receiving, by a processor, one or more current operating conditions;receiving, by the processor, one or more target operating limits;receiving, by the processor, one or more combustor transfer functions;evaluating, by the processor, the one or more combustor transfer functions to estimate operating limits associated with one or more combustion modes under the one or more current operating conditions;comparing, by the processor, the one or more estimated operating limits associated with the one or more combustion modes to the target operating limits; andbased at least in part on the comparison, selecting, by the processor, at least one of the combustion modes.2. The method of claim 1 , further comprising transferring the combustor to the selected combustion mode.3. The method of claim 1 , wherein the selection of the combustion mode comprises comparing the one or more estimated operating limits associated with the one or more combustion modes and a current combustion mode.4. The method of claim 3 , further comprising:determining that one or more differences between the one or ...

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Номер записи: 93
12-03-2020 дата публикации

Hybrid electric propulsion system and method of operation

Номер: US20200083791A1
Автор: Eric Latulipe, Richard Freer
Принадлежит: Pratt and Whitney Canada Corp

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

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Номер записи: 94
05-05-2022 дата публикации

TEMPERATURE SENSING FOR TORCH IGNITION SYSTEMS

Номер: US20220136446A1
Автор: PROCIW Lev Alexander, Ryon Jason, Seei Roger A., Williams Brandon P.
Принадлежит:

An embodiment of a system for measuring fuel ignition within a torch igniter for a combustor in a gas turbine engine includes a housing surrounding and defining a combustion chamber, a first glow plug received through the housing, and control circuitry. An innermost end of the first glow plug extends into the combustion chamber while an outermost end opposite the innermost end extends away from the combustion chamber. The control circuitry is connected to the outermost end of the glow plug and is configured to measure a temperature of the innermost end of the glow plug based on electrical resistance of the glow plug. The control circuitry is further configured to determine an operational parameter of the torch igniter based on the temperature.

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Номер записи: 95
19-03-2020 дата публикации

VEHICLE CONTROL WITH FUNCTIONAL REDUNDANCY

Номер: US20200089228A1
Автор: Adamski Paul A.
Принадлежит:

A control assembly for an aircraft system according to an example of the present disclosure includes a multi-core processor that has a plurality of cores coupled to a communications module and to an arbitration module. The communications module is operable to communicate information between the plurality of cores and one or more aircraft modules. The plurality of cores include first and second cores operable to concurrently execute a first discrete set of software instructions to generate respective instances of an output. The arbitration module is operable to communicate each and every one of the respective instances to control the one or more aircraft modules. A method of operating an aircraft system is also disclosed. 1. A control assembly for an aircraft system comprising:a multi-core processor including a plurality of cores coupled to a communications module and to an arbitration module;wherein the communications module is operable to communicate information between the plurality of cores and one or more aircraft modules;wherein the plurality of cores include first and second cores operable to concurrently execute a first discrete set of software instructions to generate respective instances of an output; andwherein the arbitration module is operable to communicate each and every one of the respective instances to control the one or more aircraft modules.2. The control assembly as recited in claim 1 , wherein the plurality of cores include third and fourth cores operable to concurrently execute a second discrete set of software instructions to control the one or more aircraft modules.3. The control assembly as recited in claim 2 , wherein the third core claim 2 , but not the fourth core claim 2 , is operable to concurrently execute the first discrete set of software instructions with the first and second cores to control the one or more aircraft modules.4. The control assembly as recited in claim 1 , wherein each of the plurality of cores includes a localized ...

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Номер записи: 96
03-07-2014 дата публикации

GAS TURBINE AND METHOD OF CONTROLLING A GAS TURBINE AT PART-LOAD CONDITION

Номер: US20140182297A1
Автор: Healy Timothy Andrew, Jensen Gregory Earl, Pinson Mark William, Terry Jason Charles
Принадлежит: GENERAL ELECTRIC COMPANY

A gas turbine includes a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and a controller. The controller controls the operation of the gas turbine at a reduced load, and is capable of querying a database including multiple sets of operational parameters for the gas turbine correlated with at least one measured output response at each set of operational parameters. One of the sets of operational parameters provides a desired gas turbine load that meets a target level for the output response. Related methods are also disclosed. 1. A method of operating a gas turbine at a reduced load , the method comprising:operating a gas turbine at multiple sets of operational parameters;measuring at least one output response of the gas turbine at each of the sets of operational parameters;creating a database at least partially including correlations of each of the sets of operational parameters with the measured output response;determining a desired reduced gas turbine load;selecting a set of operational parameters from the database that provides the desired reduced gas turbine load and that meets a target level for the output response; andfurther operating the gas turbine at the selected set of operational parameters.2. The method of claim 1 , further including the steps of:measuring the output response during the further operation of the gas turbine;comparing the measured output response to the target level for the output response; andselecting an alternate set of operational parameters if the measured output response does not meet the target level.3. The method of claim 2 , further including claim 2 , after the selecting an alternate set of operational parameters step claim 2 , repeating the further operating step and the steps thereafter.4. The method of claim 1 , wherein the set of operational parameters includes one or more of the level of an inlet guide vane angle claim 1 , an inlet ...

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Номер записи: 97
03-07-2014 дата публикации

Filter for aircraft apu system

Номер: US20140182306A1
Автор: Lamont Larry Castagnera
Принадлежит: United Technologies Corp

An auxiliary power unit (APU) system comprises an auxiliary power unit (APU) mounted in a compartment of an aircraft. A first air inlet conduit directs air to a first component disposed in the compartment. A first dry filter element is disposed within the first air inlet conduit, and has a substantially uniform pore size.

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Номер записи: 98
08-04-2021 дата публикации

Device for temporarily increasing turbomachine power

Номер: US20210102491A1
Автор: Bertrand Moine, Frederic Pousse, Laurent Minel, Lionel Napias
Принадлежит: Safran Helicopter Engines SAS

A device for temporarily increasing power in order to increase the power from at least one first turbine engine and from at least one second turbine engine, the device including a tank of coolant liquid, a first injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the first turbine engine, a second injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the second turbine engine, each of the first and second injection circuits including at least one first valve and at least one second valve arranged upstream from said at least one first valve, and a bridge pipe connecting together the first injection circuit and the second injection circuit upstream from their respective first valves and downstream from their respective second valves.

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Номер записи: 99
04-04-2019 дата публикации

Method for determining a local hot gas temperature in a hot gas duct, and devices for carrying out the method

Номер: US20190101019A1
Автор: Ken Yves Haffner, Wolfgang Franzdietrich MOHR
Принадлежит: General Electric Technology GmbH

A method is disclosed for determining a local hot gas temperature in a hot gas duct downstream a combustion device. The method comprises extracting at least one flue gas sample at least one specific cross-sectional location of the hot gas duct downstream the combustion device, determining at least one flue gas species concentration in the sample, and determining the local flue gas total temperature based upon the at least one flue gas species concentration In an embodiment, the method is conducted at the entry to an expansion turbine of a gas turbine engine. At least one vane member is provided in the guide vane row which comprises an airfoil, wherein at least one sample extraction orifice is provided on an outer surface of the airfoil, and a sample duct is provided in fluid communication with the sample extraction orifice and running inside the airfoil. The flue gas samples are extracted through the sample extraction orifices.

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Номер записи: 100