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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 3772. Отображено 100.
16-02-2012 дата публикации

Method for compensating for combustion efficiency in fuel control system

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

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

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Номер записи: 1
16-02-2012 дата публикации

Methods and systems for adaptively cooling combustion chambers in engines

Номер: US20120037100A1
Автор: Melvin J. Larsen, Roy E. McAlister, Roy Edward McAlister
Принадлежит: McAlister Technologies LLC

The present disclosure is directed to various embodiments of systems and methods for cooling a combustion chamber of an engine. One method includes introducing fuel into the combustion chamber of an engine having an energy transfer device that moves through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The method further includes monitoring a temperature of the combustion chamber. When the temperature reaches a predetermined value, the method also includes introducing coolant into the combustion chamber only during at least one of the power stroke and the exhaust stroke of the energy transfer device.

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Номер записи: 2
23-02-2012 дата публикации

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

Номер: US20120042658A1
Автор: Ken Ugai, Ryo Higashi, Takeo Hirasaki, Yoshikiyo Okamoto, Yosuke Eto
Принадлежит: Mitsubishi Heavy Industries Ltd

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

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Номер записи: 3
05-04-2012 дата публикации

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

Номер: US20120079831A1
Автор: Denis Michel Martin, Joseph Kirzhner, Matthieu Paul Frederic Vierling, Nicolas Pourron
Принадлежит: General Electric Co

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

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Номер записи: 4
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: 5
03-05-2012 дата публикации

Systems, methods, and apparatus for compensating fuel composition variations in a gas turbine

Номер: US20120102914A1
Автор: Denis Michel Martin, Joseph Kirzhner, Matthieu Paul Frederic Vierling, Nicolas Pourron, Predrag Popovic
Принадлежит: General Electric Co

Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

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Номер записи: 6
03-05-2012 дата публикации

Method and system for preventing combustion instabilities during transient operations

Номер: US20120102967A1
Автор: Joseph Kirzhner, Predrag Popovic
Принадлежит: General Electric Co

A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.

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Номер записи: 7
21-03-2013 дата публикации

METHOD FOR OPERATING A COMBUSTION DEVICE

Номер: US20130067925A1
Автор: BOTHIEN Mirko Ruben, PENNELL Douglas Anthony, ZAJADATZ Martin
Принадлежит: ALSTOM Technology Ltd

A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations. 151525. Method for operating a combustion device ( , , ) comprising:{'b': 35', '36', '5', '15', '25, 'supplying a fuel () and an oxidizer () into the combustion device (, , ) and burning them,'}{'b': 37', '35, 'supplying, during at least a part of a transient operation, an additional fluid () together with the fuel (), and'}{'b': '37', 'regulating the amount of the additional fluid () to counteract combustion pulsations.'}2. The method according to claim 1 , further comprising choosing a first parameter indicative of the fuel feed and supplying the additional fluid only when the fuel reaches a critical value of the first parameter.3. The method according to claim 2 , wherein the first parameter is the fuel mass flow (M).451525. The method according to claim 2 , wherein the first parameter is the differential pressure (AP) between a fuel supply and the inside of the combustion device ( claim 2 , claim 2 , ).5. The method according to claim 1 , further comprising choosing a second parameter indicative of the fuel and additional fluid feed claim 1 , the regulation including maintaining the second parameter above or below a given value or maintaining the second parameter within a prefixed range (R).6. The method according to claim 5 , wherein the given value is a critical value of the second parameter.7. The method according to claim 5 , wherein the second parameter range (R) corresponds to the critical value of the second parameter ±10% or to the critical value of the second parameter ±1% or to the critical value of the second parameter.8. The method according to claim 5 , wherein the bottom or the top of the range (R) correspond to the critical ...

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Номер записи: 8
28-03-2013 дата публикации

TURBINE BURNER

Номер: US20130074506A1
Автор: Kock Boris Ferdinand, Kostlin Berthold, Prade Bernd
Принадлежит:

A turbine burner is provided. The turbine burner has a secondary feed unit and a primary feed unit. The primary feed unit has a primary mixing tube and a fuel nozzle that are arranged concentrically around the secondary feed unit. The primary mixing tube and the fuel nozzle have a fluid flow connection. The fuel nozzle has an annular wall that is radially spaced in the axial direction from the secondary feed unit such that a gap height is fainted by the annular wall and the secondary feed unit. The annular wall has an inside wall directed toward the secondary feed unit and having blades with a leading edge on the upstream side. The fuel nozzle has an inlet and the blades have an axial distance from the inlet. The ratio of the distance to the gap height is greater than 1 and less than the gap height. 113.-. (canceled)14. A turbine burner , comprising:a secondary feed unit for supplying a secondary fuel or air and for discharging the secondary fuel or air from an orifice into a combustion zone; anda primary feed unit comprising a primary mixing tube and a fuel nozzle having a fuel nozzle outlet pointing into the combustion zone for supplying a primary fuel,wherein the fuel nozzle and the primary mixing tube are arranged concentrically around the secondary feed unit,wherein the primary mixing tube and the fuel nozzle have a fluid flow connection,wherein the fuel nozzle has an annular wall spaced radially apart from the secondary feed unit in an axial direction to form a gap height by the annular wall and the secondary feed unit,wherein the annular wall has an internal wall directed toward the secondary feed unit,wherein a fluid channel is between the secondary feed unit and the annular wall,wherein the fluid channel comprises blades each having a blade leading edge on an upstream side,wherein the fuel nozzle has a fuel nozzle inlet,wherein the each blade has an axial distance to the fuel nozzle inlet and a ratio of the axial distance to the gap height is greater than 1 ...

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Номер записи: 9
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: 10
18-04-2013 дата публикации

GAS TURBINE AND GAS-TURBINE PLANT HAVING THE SAME

Номер: US20130091824A1
Автор: Fujii Satoko, Higashi Kazuya, Matsumoto Keigo, Murakami Masayuki, Nakamoto Yukimasa, Shimizu Takeyuki
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

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

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Номер записи: 11
18-04-2013 дата публикации

Fuel System

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

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

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Номер записи: 12
25-04-2013 дата публикации

System for turbine combustor fuel assembly

Номер: US20130098040A1
Автор: Douglas Frank Beadie, Fabien Thibault Codron, Geoffrey David Myers, Gregory Allen Boardman, Hua Zhang
Принадлежит: General Electric Co

A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel.

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Номер записи: 13
25-04-2013 дата публикации

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

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

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

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Номер записи: 14
20-06-2013 дата публикации

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

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

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

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Номер записи: 15
04-07-2013 дата публикации

Automated tuning of multiple fuel gas turbine combustion systems

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

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

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Номер записи: 16
11-07-2013 дата публикации

METHOD FOR OPERATING A GAS TURBINE

Номер: US20130174565A1
Автор: Meeuwissen Thiemo, Schell Susanne Renate
Принадлежит: ALSTOM TECHNOLOGY LTD.

A method for operating a gas turbine, which is optionally operated with a gaseous fuel (A) having a gaseous mass flow ({dot over (m)})and/or with an oil fuel (B) having an oil mass flow ({dot over (m)}), wherein a change between an operating mode with gaseous fuel (A) and an operating mode with oil fuel (B) is undertaken during load operation of the gas turbine, and wherein a water addition of a water mass flow ({dot over (m)}) is provided at least in the operating mode with oil fuel (B). The ratio (Ω) of the added water mass flow ({dot over (m)}) to the fuel mass flow during the change between operating modes is determined according to 2. The method of claim 1 , wherein a water mass flow ratio (Ω) is provided during a change from the first operating mode with gaseous fuel (A) to the second operating mode with oil fuel (B).3. The method of claim 1 , wherein a water mass flow ratio (Ω) is provided during a change from the second operating mode with oil fuel (B) to the first operating mode with gaseous fuel (A).4. The method of claim 2 , wherein the change from the first operating mode to the second operating mode comprises activating the water mass flow ({dot over (m)}) before feeding the oil mass flow ({dot over (m)}).5. The method of claim 3 , wherein the change from the second operating mode to the first operating mode comprises activating the water mass flow ({dot over (m)}) feeding the gaseous mass flow ({dot over (m)}).6. The method of claim 1 , wherein the gas turbine includes a guide vane arrangement claim 1 ,wherein a position of a guide vane of the guide vane arrangement remains unchanged during a change between first the operating mode and the second operating mode.7. The method of claim 1 , wherein the gas turbine in the second operating mode is configured to be operated without addition of the water mass flow ({dot over (m)}) claim 1 , and{'sub': 'H2O', 'wherein the adding of the water mass flow ({dot over (m)}) is activated for changing between the ...

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Номер записи: 17
18-07-2013 дата публикации

BURNER ARRANGEMENT

Номер: US20130180251A1
Автор: Hase Matthias, Meisl Jürgen
Принадлежит:

A burner arrangement includes a carrier and at least two burners which are mounted on the carrier in a flow direction Each burner includes a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades. An attachment is arranged on the side leading to a combustion chamber At least one fuel nozzle is disposed in the attachment and is connected to the fuel duct. The at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form, and the at least two fuel nozzles of the at least two burners with a different functional characteristic and/or spray form include at least one full jet nozzle and at least one pressure swirl nozzle. 110-. (canceled)11. A burner arrangement , comprising:a carrier,at least two burners which are mounted on the carrier in a flow direction, a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades,', 'wherein an attachment is arranged on the side leading to a combustion chamber,', 'wherein at least one fuel nozzle is disposed in the attachment and is connected to the fuel duct,, 'wherein each burner compriseswherein the at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form.12. The burner arrangement as claimed in claim 11 , wherein for each of the burners claim 11 , the at least one fuel nozzle is arranged downstream of the swirl blades.13. The burner arrangement as claimed in claim 11 ,wherein the fuel nozzles with a different functional characteristic differ from one another at least in a nozzle size or a jet angle or liquid distribution or an atomization characteristic.14. The burner arrangement as claimed in claim 13 ,wherein, in the case of a different atomization characteristic of the fuel nozzles, at least the drop size distributions differ from one ...

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Номер записи: 18
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: 19
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: 20
01-08-2013 дата публикации

DUAL FUEL AIRCRAFT ENGINE CONTROL SYSTEM AND METHOD FOR OPERATING SAME

Номер: US20130192246A1
Автор: Kamath Deepak Manohar, Leighton David Mark, Morton Scott Chandler
Принадлежит: GENERAL ELECTRIC COMPANY

A dual fuel engine control system comprising a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine, and a second fuel control system configured to control the flow of a second fuel to the aircraft gas turbine engine. 1. A dual fuel aircraft engine control system comprising:a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine; anda second fuel control system configured to control the flow of a second fuel to said aircraft gas turbine engine.2. The control system according to claim 1 , wherein the first fuel and the second fuel are different compositions.3. The control system according to claim 1 , wherein the first fuel is a liquid kerosene-based fuel.4. The control system according to claim 2 , wherein the second fuel is a cryogenic liquid fuel.5. The control system according to claim 2 , wherein the second fuel is Liquefied Natural Gas (LNG).6. The control system according to claim 1 , wherein the first fuel control system is a hydromechanical control system.7. The control system according to claim 1 , wherein the first fuel control system is an electronic control system.8. The control system according to claim 1 , wherein the first fuel control system is a Full Authority Digital Electronic Control (FADEC).9. The control system according to claim 1 , wherein the second fuel control system is an electronic control system.10. The control system according to claim 1 , wherein the first fuel control system and second fuel control system are integrated.11. A method of operating a dual fuel aircraft engine control system claim 1 , the method comprising:activating a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine; andactivating a second fuel control system configured to control the flow of a second fuel to said aircraft gas turbine engine.12. The method according to claim 11 , wherein the first fuel and ...

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Номер записи: 21
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: 22
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: 23
08-08-2013 дата публикации

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

Номер: US20130199198A1
Автор: Alban Corpron
Принадлежит: Eurocopter SA

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

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Номер записи: 24
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: 25
22-08-2013 дата публикации

COMBUSTION DEVICE WITH PULSED FUEL SPLIT

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

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

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Номер записи: 26
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: 27
19-09-2013 дата публикации

Hybrid gas turbine engine-electric motor/generator drive system

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

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

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Номер записи: 28
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: 29
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: 30
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: 31
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: 32
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: 33
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: 34
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: 35
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: 36
23-01-2014 дата публикации

METHOD AND DEVICE FOR GENERATING ELECTRICITY AND GYPSUM FROM WASTE GASES CONTAINING HYDROGEN SULFIDE

Номер: US20140020399A1
Автор: HUELLER Rolf
Принадлежит: KNAUF GIPS KG

The invention relates to a method and an apparatus for generating current from hydrogen sulphide-containing exhaust gases, particularly from the natural gas industry. 1. Method for generating current from hydrogen sulphide-containing exhaust gases , particularly from the natural gas and petroleum industry ,the hydrogen sulphide-containing exhaust gases being delivered to a current generation device and being burnt there, preferably with air being supplied, the energy released during combustion being employed at least partially for current generation,characterized in thatthe composition of the hydrogen sulphide-containing exhaust gases is measured before combustion and is compared with a stipulated composition or stipulated composition bandwidth, and, in the event of a deviation from the stipulated composition or composition bandwidth, an additional fraction of natural gas and/or other substances, which is required for correction, is determined and is admixed to the hydrogen sulphide-containing exhaust gases before combustion.2. Method according to claim 1 ,characterized in thatthe combustion temperature of hydrogen sulphide-containing exhaust gases is at least about 1,300° C.3. Method according to claim 1 ,characterized in thatthe current generation device comprises a steam generator which is part of the thermodynamic circuit of a steam power process, which, in turn, comprises a steam turbine following the steam generator and a condenser following the steam turbine, the combustion of the hydrogen sulphide-containing exhaust gases taking place in the steam generator, and the energy released being employed at least partially for steam generation, and current generation taking place by means of a generator driven by the steam turbine.4. Method according to claim 3 ,characterized in thatthe current generation device comprises a gas turbine and/or a gas engine, current generation taking place by means of a generator driven by the gas turbine and/or by the gas engine.5. ...

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Номер записи: 37
30-01-2014 дата публикации

Combustor nozzle assembly, combustor equipped with the same, and gas turbine

Номер: US20140026578A1
Автор: Shin Kato, Takashi Onozuka, Yoshitaka Terada
Принадлежит: Mitsubishi Heavy Industries Ltd

A combustor nozzle assembly includes: a nozzle mounting base which blocks a combustor insertion opening formed in a turbine casing; a nozzle rod which passes through the nozzle mounting base and has a rod tip portion and a rod base end portion; an oil fuel pipe which is as a whole inserted into the nozzle rod, which has a pipe tip portion and a pipe base end portion, in which fuel is supplied to the inside through the rod base end portion, and which injects the fuel from the pipe tip portion through the rod tip portion; and an O-ring which is disposed in the rod base end portion and suppresses leakage of fuel to the pipe tip portion side between the inner periphery side of the nozzle rod and the outer periphery side of the oil fuel pipe.

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Номер записи: 38
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: 39
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: 40
13-03-2014 дата публикации

GAS TURBINE COMBUSTOR

Номер: US20140069079A1
Автор: HAYASHI Akinori, Koizumi Hiromi, Sekiguchi Tatsuya, Yoshida Shohei
Принадлежит: Hitachi, Ltd.

A gas turbine combustor includes a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction. A first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole. A swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole. 1. A gas turbine combustor having a combustion chamber for mixing a gas and air together to burn the gas , and a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame , wherein:the burner is provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction thereof;a first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole; anda swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole.2. The gas turbine combustor according to claim 1 , wherein:the first gas is a low BTU gas and the second gas is a high BTU gas.3. The gas turbine combustor according to claim 1 , wherein:the burner is provided with a plurality of gas holes in an end surface on an inner circumferential side of the first swirler in a radial direction, and the second gas is supplied to the interior of the combustion chamber through ...

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Номер записи: 41
27-03-2014 дата публикации

STROKE TRANSMITTER FOR GAS TURBINE

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

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

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Номер записи: 42
01-01-2015 дата публикации

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

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

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

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Номер записи: 43
07-01-2021 дата публикации

METHODS AND SYSTEMS FOR DIESEL FUELED CLC FOR EFFICIENT POWER GENERATION AND CO2 CAPTURE

Номер: US20210003041A1
Автор: Adnan Muflih Arisa, HOSSAIN Mohammad Mozahar, Pradiptya Iswan
Принадлежит: KING FAHD UNIVERSITY OF PETROLEUM AND MINERALS

An integrated chemical looping combustion (CLC) electrical power generation system and method for diesel fuel combining four primary units including: gasification of diesel to ensure complete conversion of fuel, chemical looping combustion with supported nickel-based oxygen carrier on alumina, gas turbine-based power generation and steam turbine-based power generation is described. An external combustion and a heat recovery steam generator (HRSG) are employed to maximize the efficiency of a gas turbine generator and steam turbine generator. The integrated CLC system provides a clean and efficient diesel fueled power generation plant with high COrecovery. 1. A diesel fueled chemical-looping combustion (CLC) electrical power generation system , comprising:a feed source of diesel fuel;a gasification chamber fluidly connected to the feed source, the gasification chamber including a first heat exchanger, a gasification reactor and a gasification splitter;a chemical looping combustion chamber fluidly connected to the gasification chamber, the chemical looping combustion chamber including a first reduction reactor, a first splitter, a second reduction reactor and a second splitter;a gas combustion chamber fluidly connected at a first input to a first output of the first splitter and at a second input to the gasification splitter,a gas turbine power generator connected to the combustor;at least one steam turbine electrical power generator;a heat recovery unit fluidly connected to the at least one steam turbine electrical power generator and to the gasification chamber, the heat recovery unit including a second heat exchanger and a plurality of steam generators; and{'sub': 2', '2, 'a COgas purification stage connected to the heat recovery unit, the COgas purification stage including a plurality of condensers and a plurality of compressors.'}2. The system of claim 1 , wherein the first heat exchanger is connected at a first input to the diesel fuel source claim 1 , and at a ...

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Номер записи: 44
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: 45
08-01-2015 дата публикации

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

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

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

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Номер записи: 46
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: 47
12-01-2017 дата публикации

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

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

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

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Номер записи: 48
12-01-2017 дата публикации

FUEL SUPPLY PIPELINE SYSTEM FOR GAS TURBINE

Номер: US20170009666A1
Автор: CANO WOLFF Mariano, CHOI Du-Fhan, Hausmann Kai, LV Song Jun, SCHNEIDER Peter-Andreas, SCHWAGER Julius
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A fuel supply line system used for a gas turbine, including: fuel gas control valves used for controlling delivery to the gas turbine; a first line used for connecting the fuel gas source to the control valves; a second line used for connecting the control valves to the gas turbine; a monitoring device, configured to be used for determining the pressure inside the pipe at the outlet of the second line near said control valve; and a controller, configured to reduce the effective flow area of the pressure control valves or close the control valves when the determined pressure inside the pipe of the second line is greater than a predetermined pressure. 1. A fuel supply pipeline system for a gas turbine , comprising:a control valve to control a gas conveyed to the gas turbine;a first pipeline to connect a gas source to the control valve;a second pipeline to connect the control valve to the gas turbine;a monitoring device, configured to determine an in-pipe pressure of the second pipeline at a position adjacent to an outlet of the control valve; anda controller, configured to reduce an effective through-flow area of the control valve or close the control valve when the in-pipe pressure determined in the second pipeline is relatively greater than a threshold in-pipe pressure.2. The fuel supply pipeline system of claim 1 , further comprising:a blocking valve, disposed upstream of the control valve, the controller being configured to close the blocking valve when the determined in-pipe pressure is relatively greater than the threshold in-pipe pressure.3. The fuel supply pipeline system of claim 1 , wherein the control valve is one of multiple control valves connected in parallel claim 1 , the controller being configured to close all the multiple control valves when the in-pipe pressure determined in the second pipeline adjacent to an outlet of any one of the multiple control valves is relatively greater than the threshold in-pipe pressure.4. The fuel supply pipeline system ...

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Номер записи: 49
09-01-2020 дата публикации

AIRCRAFT ELECTRICALLY-ASSISTED PROPULSION CONTROL SYSTEM

Номер: US20200010205A1
Автор: FLETCHER Paul, Kulathasan Ashog, Pellegrini Alvise, SWANN Peter
Принадлежит: ROLLS-ROYCE PLC

This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor. 1. An aircraft propulsion system comprising:an engine having a propulsive fan and an engine core, the engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor, the propulsive fan configured to generate a mass flow of air that bypasses the engine core and propels an aircraft on which the engine is located;an electrical energy store on board the aircraft;at least one electric motor arranged to drive the propulsive fan and the engine core compressor; anda controller arranged for control of the at least one electric motor by altering a ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor,wherein control of the at least one electric motor comprises selectively and concurrently driving both the propulsive fan and engine core compressor.2. The aircraft propulsion system according to claim 1 , wherein the at least one electric motor is configured to selectively assist the engine core compressor by supplementing torque applied to the compressor via the turbine due to the engine core combustion process.3. The aircraft propulsion system according to claim 1 ...

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Номер записи: 50
11-01-2018 дата публикации

SHAFT SHEAR DETECTION THROUGH SHAFT OSCILLATION

Номер: US20180010980A1
Автор: SHENOUDA Antwan
Принадлежит:

There is described a shaft shear event detection method. The method comprises obtaining a demodulated waveform of a shaft oscillation wave superimposed on a shaft rotational speed signal, comparing the amplitude to an amplitude threshold, detecting oscillation when the amplitude threshold is exceeded for a plurality of samples, and detecting a shaft shear when oscillation continues for a predetermined time limit. 1. A method for detecting a shear of a rotating shaft positioned between a source and a load , the method comprising:obtaining a demodulated waveform of a shaft oscillation wave superimposed on a shaft rotational speed signal, the waveform having an amplitude and a frequency;comparing the amplitude of the waveform to an amplitude threshold;detecting an oscillation of the shaft when the amplitude threshold is exceeded for a plurality of samples; anddetecting a shear of the rotating shaft when oscillation continues for a predetermined time limit.2. The method of claim 1 , wherein the amplitude threshold comprises a lower amplitude threshold and an upper amplitude threshold.3. The method of claim 1 , wherein the demodulated waveform is obtained through amplitude demodulation.4. The method of claim 1 , wherein the demodulated waveform is obtained through frequency demodulation.5. The method of claim 1 , wherein obtaining the demodulated waveform comprises receiving a speed sensor signal and determining the amplitude and frequency of the oscillation wave from the speed sensor signal.6. The method of claim 5 , wherein the speed sensor signal comes from a phonic wheel sensing assembly.7. The method of claim 1 , wherein the predetermined time limit is measured as a function of a period of the waveform.8. A system for detecting a shear of a rotating shaft positioned between a source and a load claim 1 , the system comprising:a processing unit; and obtaining a demodulated waveform of a shaft oscillation wave superimposed on a shaft rotational speed signal, the ...

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Номер записи: 51
14-01-2021 дата публикации

Modulating fuel for a turbine engine

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

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

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Номер записи: 52
14-01-2016 дата публикации

Integrated Power Generation Using Molten Carbonate Fuel Cells

Номер: US20160013502A1
Автор: Barckholtz Timothy Andrew, Berlowitz Paul J., Hershkowitz Frank, Lee Anita S.
Принадлежит: EXXONMOBIL RESEARCH AND ENGINEERING COMPANY

In various aspects, systems and methods are provided for integrated operation of molten carbonate fuel cells with turbines for power generation. Instead of selecting the operating conditions of a fuel cell to improve or maximize the electrical efficiency of the fuel cell, an excess of reformable fuel can be passed into the anode of the fuel cell to increase the chemical energy output of the fuel cell. The increased chemical energy output can be used for additional power generation, such as by providing fuel for a hydrogen turbine. 1. A method for producing electricity , the method comprising:introducing a fuel stream comprising a reformable fuel into an anode of a molten carbonate fuel cell, an internal reforming element associated with the anode, or a combination thereof;{'sub': 2', '2, 'introducing a cathode inlet stream comprising COand Ointo a cathode of the molten carbonate fuel cell;'}generating electricity within the molten carbonate fuel cell, the molten carbonate fuel cell being operated such that a fuel utilization in the anode is about 50% or less at steady state conditions;{'sub': 2', '2, 'generating an anode exhaust comprising H, CO, and CO;'}{'sub': '2', 'separating, from at least a portion of the anode exhaust, a first H-rich gas stream; and'}{'sub': '2', 'combusting at least a portion of the first H-rich gas stream to produce electricity.'}2. The method of claim 1 , further comprising performing a water gas shift process on the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.3. The method of claim 1 , further comprising separating COand/or HO from the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.4. The method of claim 1 , wherein the separating step comprises:performing a water gas shift process on the anode exhaust or at least a portion of the anode exhaust to form a shifted anode exhaust portion; and{'sub': 2', '2', '2, 'separating HO ...

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Номер записи: 53
10-01-2019 дата публикации

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

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

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

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Номер записи: 54
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: 55
17-01-2019 дата публикации

PERFORMANCE AND LIFE OPTIMIZING CONTROL SYSTEM FOR A TURBINE ENGINE

Номер: US20190017409A1
Автор: Paul Jacques, Yardibi Tarik
Принадлежит:

Systems and methods for controlling powerplants that include and/or leverage one or more health models to proactively optimize component life or minimize damage of one or more components of the powerplant are provided. In one exemplary aspect, a control system for a powerplant feeds engine data into one or more health models. The health models output health data indicative of a condition of one or more components of the powerplant. The control system utilizes the health data outputs to proactively control the components of the powerplant in such a way so as to optimize component life/damage.

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Номер записи: 56
21-01-2021 дата публикации

REDUCING IDLE THRUST IN A PROPULSIVE GAS TURBINE

Номер: US20210017914A1
Автор: TURNER Caroline L.
Принадлежит:

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; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; and an engine controller configured to identify a condition to the effect that the engine is in an approach idle condition, and operate the first electric machine in a motor mode and operate the second electric machine in a generator mode to transfer power electrically from the LP spool to the HP spool to thereby reduce the LP spool rotational speed and increase the HP spool rotational speed. 1. A gas turbine engine for an aircraft , comprising:a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine;a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; andan engine controller configured to identify a condition to the effect that the engine is in an approach idle condition, and operate the first electric machine in a motor mode and operate the second electric machine in a generator mode to transfer power electrically from the LP spool to the HP spool to thereby reduce the LP spool rotational speed and increase the HP spool rotational speed.2. The gas turbine engine of claim 1 , further comprising a fan forming part of the LP spool claim 1 , whereby reduction of the LP spool rotational speed substantially reduces the thrust produced by the engine.3. The gas turbine engine of claim 2 , in which the engine is a geared turbofan engine claim 2 , in which a fan thereof is drivingly connected with the LP spool via a reduction gearbox.4. The gas turbine engine of claim 1 , in which the engine controller is further configured to:identify a condition to the effect that, to maintain a target HP spool rotational speed, an operating point of the LP compressor will erode one of a surge margin or a choke margin; ...

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Номер записи: 57
16-01-2020 дата публикации

INDEPENDENTLY CONTROLLED THREE STAGE WATER INJECTION IN A DIFFUSION BURNER

Номер: US20200018232A1
Автор: Dandwani Heena H., Rodd Shervin, Singh Gurdev
Принадлежит:

A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the first stage water mixes and travels with the gaseous fuel to be injected into a combustor. A second stage includes water injected into the combustor via a secondary liquid nozzle which is used for fuel oil during liquid fuel operation, but which may be used for the secondary water during gaseous fuel operation. A third stage includes water injected into the combustor via a plurality of nozzle holes known as an atomizing air cap. An algorithm and criteria are also defined for controlling the three stages of water injection to achieve the optimum balance of turbine operational criteria including NOx emissions, combustion dynamics and water impingement downstream of the nozzle. 1. A method for determining water flow rates for three stage water injection in a turbine engine combustion system , said method comprising:providing a turbine engine with injection of primary water, secondary water and tertiary water in the combustion system;setting the turbine engine to operate at a load point and measuring turbine operational data;determining if a plurality of turbine operational criteria are satisfied at the load point using single stage water injection or two stage water injection in the combustion system using the operational data;starting three stage water injection if the turbine operational criteria are not satisfied at the load point using single stage water injection or two stage water injection;setting primary/secondary/tertiary water fractions to preliminary values for the load point;setting water/fuel ratio to a preliminary value for the load point;operating the turbine engine using the water/fuel ratio and the primary/secondary/tertiary water fractions and measuring the turbine operational data;determining if the plurality of ...

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Номер записи: 58
26-01-2017 дата публикации

METHOD AND INSTALLATION FOR STORING AND RECOVERING ENERGY

Номер: US20170022897A1
Автор: Alekseev Alexander, Bergins Christian, Stiller Christoph, Stöver Brian
Принадлежит:

A method and installation for storing and recovering energy, according to which a condensed air product is formed in an energy storage period, and in an energy recovery period, a pressure flow is formed and is expanded to produce energy using at least part of the condensed air product. For the formation of the condensed air product: the compression of air in an air conditioning unit, at least by means of at least one isothermally operated compressor device and the adsorptive cleaning of the air by means of at least one adsorptive cleaning device at a hyperbaric pressure level. 1. A method for storing and recovering energy in which , in an energy storage period , an air liquefaction product is formed and , in an energy recovery period , a pressurized stream is formed and expanded to perform work by using at least part of the air liquefaction product , the method comprising , compressing air in an air conditioning unit, at least by means of at least one isothermally operated compressor device, and adsorptively purifying the air by means of at least one adsorptive purification device at a superatmospheric pressure level,', 'liquefying the compressed and adsorptively purified air, starting from a temperature level in a range of 0 to 50° C., in a first fraction in a fixed-bed cold storage unit and in a second fraction in a counterflow heat exchanger unit at a liquefaction pressure level in a range of 40 to 100 bara, and', 'subsequently expanding the liquefied air in at least one cold production unit,, 'for the formation of the air liquefaction product,'} producing a vaporization product from at least part of the liquefaction product at a vaporization pressure level, which deviates by no more than 5 bar from the liquefaction pressure level, in the fixed-bed cold storage unit, and', 'forming a fluid stream from at least part of the vaporization product and conducting it through at least one combustion device, in which a fuel is burned., 'and, for the formation of the ...

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Номер записи: 59
26-01-2017 дата публикации

System and Method for Providing Highly Reactive Fuels to a Combustor

Номер: US20170022898A1
Автор: Douglas Frank Beadie, Ilya Alexandrovich Slobodyanskiy, Jeffrey Scott Goldmeer
Принадлежит: General Electric Co

A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system includes multiple fuel circuits. Each fuel circuit individually feeds fuel to a corresponding fuel distribution manifold. The system further includes a steam injection system. The steam injection system includes at least one flow control valve that is in fluid communication with at least one of the fuel circuits. The flow control valve provides for fluid communication between a superheated steam source and the fuel circuit during both fueled operation and during non-fueled operation of the corresponding fuel circuit.

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Номер записи: 60
26-01-2017 дата публикации

SYSTEM AND METHOD FOR OPERATING A POWER PLANT

Номер: US20170022902A1
Автор: Hao Yongjiang, Wu Wenjie, Zhang Hua
Принадлежит:

A system including a fuel-supply system including, an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system, an expander configured to generate power by expanding an oxidant from the gas-turbine system, and a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator 1. A system , comprising:an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system;an expander configured to generate power by expanding an oxidant from the gas-turbine system; anda motor-generator configured to function in a motor mode and in a generator mode, wherein the motor-generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor-generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor-generator.2. The system of claim 1 , comprising a fuel-gas compressor-expander having both the auxiliary-fuel gas compressor and the expander as a single dual-purpose unit.3. The system of claim 1 , comprising a controller configured to change the motor-generator between the motor mode and the generator mode.4. The system of claim 3 , comprising a compressor clutch configured to engage and disengage the auxiliary-fuel-gas compressor from the motor-generator claim 3 , wherein the controller controls operation of the auxiliary-fuel-gas compressor by engaging and disengaging the compressor clutch.5. The system of claim 4 , comprising an expander clutch configured to engage and disengage the expander from the motor-generator claim 4 , wherein the controller controls operation of the expander by engaging and disengaging the expander clutch.6. The system of ...

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Номер записи: 61
28-01-2016 дата публикации

ENERGY-EFFICIENT AND CONTROLLED VAPORIZATION OF CRYOFUELS FOR AIRCRAFT ENGINES

Номер: US20160025339A1
Автор: Delgado, EPSTEIN Michael Jay, JR. Adon, Kamath Deepak Manohar
Принадлежит:

A method and apparatus of using cryogenic fuel in an engine for an aircraft wherein the cryogenic fuel is supplied to the engine for combustion. 1. A method of using cryogenic fuel in an engine for aircraft generating waste heat , the method comprising:supplying liquid cryogenic fuel for combustion in the engine; andvaporizing the liquid cryogenic fuel with the waste heat from the aircraft to form vaporized fuel from the liquid cryogenic fuel prior to combustion in the engine.2. The method of further comprising combusting the vaporized cryogenic fuel in the engine.3. The method of wherein vaporizing the liquid cryogenic fuel with waste heat from the aircraft comprises passing the waste heat and the liquid cryogenic fuel through a heat exchanger to heat the liquid cryogenic fuel with the waste heat.4. The method of wherein passing the waste heat through the heat exchanger comprises passing multiple sources of waste heat through the heat exchanger.5. The method of wherein passing the waste heat and liquid cryogenic fuel through the heat exchanger comprises passing the waste heat and liquid cryogenic fuel through multiple heat exchangers.6. The method of wherein passing the waste heat through the multiple heat exchangers comprises passing different sources of waste heat to different heat exchangers of the multiple heat exchangers.7. The method of wherein passing the waste heat through multiple heat exchangers further comprises passing the liquid cryogenic fuel through a first heat exchanger such that the first heat exchanger heats the fuel to a temperature below the fuel vaporization temperature claim 6 , and passing the liquid cryogenic fuel from the first heat exchanger to a second heat exchanger such that the second heat exchanger vaporizes the fuel claim 6 , and wherein the passing the liquid cryogenic fuel through both heat exchangers occurs if a single heat exchanger is unable to vaporize the fuel.8. The method of wherein vaporizing the liquid cryogenic fuel with ...

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Номер записи: 62
10-02-2022 дата публикации

COMBUSTION SYSTEM AND METHOD FOR ATTENUATION OF COMBUSTION DYNAMICS IN A GAS TURBINE ENGINE

Номер: US20220042684A1
Автор: Bush Scott Matthew, Danis Allen Michael, Johnson Arthur Wesley, Lyle Kent Hamilton, Overman Nicholas Ryan, Stevens Eric John
Принадлежит:

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system. 117-. (canceled)18. A combustion system for a gas turbine engine , the combustion system comprising:a liner and dome assembly together defining a combustion chamber;a first fuel nozzle and a second fuel nozzle together in alternating circumferential arrangement around a longitudinal centerline; and{'b': '50', 'a fuel supply system providing a first supply of fuel to the first fuel nozzle and a second supply of fuel to the second fuel nozzle, wherein at least % of an overall supply of fuel is the first supply of fuel.'}19. The combustion system of claim 18 , wherein the fuel supply system comprises a first fuel manifold coupled to the first fuel nozzle and a second fuel manifold coupled to the second fuel nozzle claim 18 , wherein the fuel supply system provides at least 50% of the overall supply of fuel to the first fuel nozzle and a remainder of the overall supply of fuel to the second fuel nozzle.20. The combustion system of claim 18 , wherein the fuel supply system comprises a main fuel manifold coupled to the first fuel nozzle and the second fuel nozzle claim 18 , and wherein each of the first fuel nozzle and the second fuel nozzle define a proportion of the overall supply of fuel.21. The ...

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Номер записи: 63
29-01-2015 дата публикации

SYSTEM FOR PERFORMING STAGING CONTROL OF A MULTI-STAGE COMBUSTOR

Номер: US20150027100A1
Автор: Qin Yong, STEVENSON Andrew
Принадлежит:

A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split. 1. A fuel supply system for feeding fuel to a multi-stage combustor of a gas turbine engine , the fuel supply system comprising: a plurality of fuel manifolds which distribute fuel to respective stages of the combustor , a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds , an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds , and a control system for performing staging control of the combustor;wherein the control system includes:a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds; anda controller which commands the fuel metering valve to supply fuel to the combustor at a given flow rate, and which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split.2. A fuel supply system according to claim 1 , wherein ...

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Номер записи: 64
28-01-2021 дата публикации

HYBRID GAS TURBINE ENGINE STARTING CONTROL

Номер: US20210025339A1
Автор: Collopy Gary, Terwilliger Neil
Принадлежит:

A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor. 1. A system comprising:a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor;a low spool motor configured to augment rotational power of the low speed spool; and 'control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.', 'a controller configured to cause fuel flow, the controller operable to2. The system of claim 1 , wherein the controller is further operable to control the low spool motor responsive to the thrust command during a starting operation of the gas turbine engine.3. The system of claim 2 , further comprising a high spool motor configured to augment rotational power of the high speed spool claim 2 , wherein the controller is configured to control the high spool motor to accelerate the high speed spool during the starting operation of the gas turbine engine while the low spool motor controls thrust of the gas turbine engine on the low speed spool.4. The system of claim 3 , wherein the starting operation comprises a ground-based start or an in-flight restart.5. The system of claim 3 , further comprising:a low spool generator configured to extract power from the low speed spool; anda high spool generator configured to extract power from the high speed spool.6. The system of claim 5 , wherein the controller is configured to selectively provide electrical power from the low spool generator to the high spool motor and selectively provide electrical power ...

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Номер записи: 65
04-02-2016 дата публикации

FUEL PLENUM FOR A FUEL NOZZLE AND METHOD OF MAKING SAME

Номер: US20160033138A1
Автор: Berry Jonathan Dwight, Graham Kaitlin Marie
Принадлежит:

A fuel plenum for a fuel nozzle assembly includes a gaseous fuel conduit, a conduit passage, and a liquid fuel conduit. Said gaseous fuel conduit received at a first end of said fuel plenum. Said fuel plenum is configured to distribute gaseous fuel received from said gaseous fuel conduit. Said conduit passage extends from the first end to a second end of said fuel plenum. Said conduit passage is at least partially defined by at least one interior wall of said fuel plenum. Said liquid fuel conduit defined by an outer wall and a portion of said liquid fuel conduit extending through said conduit passage. Said liquid fuel conduit outer wall is offset from said at least one interior wall. 1. A fuel plenum for a fuel nozzle assembly , said fuel plenum comprising:a gaseous fuel conduit received at a first end of said fuel plenum, said fuel plenum is configured to distribute gaseous fuel received from said gaseous fuel conduit;a conduit passage that extends from the first end to a second end of said fuel plenum, said conduit passage is at least partially defined by at least one interior wall of said fuel plenum; anda liquid fuel conduit defined by an outer wall, a portion of said liquid fuel conduit extends through said conduit passage, said liquid fuel conduit outer wall is offset from said at least one interior wall.2. The fuel plenum of claim 1 , wherein said liquid fuel conduit is received at said first end of said fuel plenum claim 1 , said liquid fuel conduit outer wall is offset by a first distance from an outer wall of said gaseous fuel conduit at said fuel plenum first end.3. The fuel plenum of claim 1 , wherein said liquid fuel conduit outer wall is offset by a second distance from said at least one interior wall.4. The fuel plenum of claim 1 , wherein said portion of said liquid fuel conduit is structurally coupled to the fuel nozzle assembly at a single location proximate said fuel plenum claim 1 , such that an end of said portion opposite the single location is ...

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Номер записи: 66
01-02-2018 дата публикации

Gas turbine energy supplementing systems and heating systems, and methods of making and using the same

Номер: US20180030902A1
Автор: Joshua KRAFT, Robert J. Kraft
Принадлежит: Powerphase Llc

Electrical power systems, including generating capacity of a gas turbine are provided, where additional electrical power is generated utilizing a separate engine and auxiliary air injection system. The gas turbine and separate engine can operate on different fuel types.

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Номер записи: 67
05-02-2015 дата публикации

GAS TURBINE SYSTEM CONTROL ADJUSTMENT FOR GAS TURBINE SHAFT SPEED CHANGE

Номер: US20150033750A1
Автор: Ho Chi Ming, Huey John Rogers, Jordan Harold Lamar
Принадлежит: GENERAL ELECTRIC COMPANY

A power system includes a gas turbine configured to rotate a shaft to supply power to an electricity grid and a controller configured to detect a change in a speed of the shaft and to adjust a formula for controlling a fuel supplied to a combustor of the gas turbine based on detecting a changing shaft speed. 1. A power system , comprising:a gas turbine configured to rotate a shaft to supply power to an electricity grid; anda controller configured to detect a change in a speed of the shaft and to adjust a formula for controlling a fuel supplied to a combustor of the gas turbine based on detecting a changing shaft speed.2. The power system of claim 1 , wherein the controller is configured to adjust the formula by omitting from the formula a variable corresponding to shaft acceleration based on detecting the changing shaft speed.3. The power system of claim 2 , wherein the controller is configured to omit from the formula the variable corresponding to the shaft acceleration based on detecting a decreasing shaft speed.4. The power system of claim 3 , wherein the controller is configured to include in the formula the variable corresponding to the shaft acceleration based on detecting an increasing shaft speed.5. The power system of claim 3 , wherein the formula for controlling the fuel supplied to the combustor is based on a change in power output equation:{'br': None, 'Change in gas turbine power output=−Iωα,'}wherein ω is a speed of the shaft, I is an moment of inertia of the shaft, and α is the variable corresponding to the shaft acceleration.6. The power system of claim 2 , wherein the controller is configured to maintain steady a supply of fuel to the gas turbine based on detecting an increasing shaft speed.7. A method of controlling a gas turbine connected to an electrical grid claim 2 , comprising:detecting a change in speed of a shaft of the gas turbine;adjusting a formula for controlling fuel supplied to a combustor of the gas turbine based on detecting a ...

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Номер записи: 68
17-02-2022 дата публикации

System and Methods for Recycling Hydrocarbon Waste Gas That is Generated During Cleaning of a Hydrocarbon Storage Tank

Номер: US20220049649A1
Автор: McElduff Kelan Samuel, McGuire Adam Mark
Принадлежит:

A hydrocarbon waste-gas recycling method having the steps of: transporting a hydrocarbon waste-gas composition, which is generated during a hydrocarbon storage-tank cleaning process, from a storage tank that is being cleaned to a fuel-gas blend controller; blending the hydrocarbon waste-gas composition with a second hydrocarbon gas-phase composition to thereby create a third gas-phase composition; and using the third gas-phase composition to fuel a combustion engine. 1. A hydrocarbon waste-gas recycling method comprising the steps:transporting a hydrocarbon waste-gas composition, which is generated during a hydrocarbon storage-tank cleaning process, from a storage tank that is being cleaned to a fuel-gas blend controller;blending the hydrocarbon waste-gas composition with a second hydrocarbon gas-phase composition to thereby create a third gas-phase composition; andusing the third gas-phase composition to fuel a combustion engine.2. The hydrocarbon waste-gas recycling method of claim 1 , wherein the hydrocarbon storage-tank cleaning process is a crude-oil storage-tank cleaning process.3. The hydrocarbon waste-gas recycling method of claim 1 , wherein the combustion engine powers an electric generator.4. The hydrocarbon waste-gas recycling method of claim 1 , wherein the second hydrocarbon gas-phase composition is propane gas.5. The hydrocarbon waste-gas recycling method of claim 3 , further comprising the step of using electricity generated by the electric generator to power at least one electric motor.6. The hydrocarbon waste-gas recycling method of claim 1 , further comprising the step of using a heat recovery unit to recover heat from exhaust emitted by the combustion engine.7. The hydrocarbon waste-gas recycling method of claim 1 , wherein a pipeline is used to transport the hydrocarbon waste-gas composition from the storage tank that is being cleaned to the fuel-gas blend controller.8. The hydrocarbon waste-gas recycling method of claim 1 , wherein a pipeline ...

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Номер записи: 69
31-01-2019 дата публикации

SYSTEMS AND METHODS FOR PREDICTING AN ANOMALY IN A COMBUSTOR

Номер: US20190032510A1
Автор: Abrol Sidharth, Balram Sangeeta, Kalya Prabhanjana, Patchaikani Prem Kumar
Принадлежит:

A method for predicting an anomaly in a combustor () is presented. The method includes receiving signals representative of parameters in one or more combustion cans () of the combustor, generating a plurality of patterns based on a permutation entropy window and the signals, identifying a plurality of pattern categories in the plurality of patterns, determining a permutation entropy based on the plurality of patterns and the plurality of pattern categories, and predicting an anomaly in the combustor based on the permutation entropy. The method further includes comparing the plurality of pattern categories to determined permutations of pattern categories if the anomaly is present in the combustor, and predicting a category of the anomaly based on the comparison of the plurality of pattern categories to the determined permutations of pattern categories. 1. A method for predicting an anomaly in a combustor , comprising:receiving, by a processing subsystem, signals representative of parameters in one or more combustion cans of the combustor;generating, by the processing subsystem, a plurality of patterns based on a permutation entropy window and the signals;identifying, by the processing subsystem, a plurality of pattern categories in the plurality of patterns;determining, by the processing subsystem, a permutation entropy based on the plurality of patterns and the plurality of pattern categories;predicting, by the processing subsystem, an anomaly in the combustor based on the permutation entropy;if the anomaly is present in the combustor then comparing, by the processing subsystem, the plurality of pattern categories to determined permutations of pattern categories; andpredicting a category of the anomaly, by the processing subsystem, based on the comparison of the plurality of pattern categories to the determined permutations of pattern categories.2. The method of claim 1 , wherein identifying the plurality of pattern categories comprises grouping the plurality of ...

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Номер записи: 70
31-01-2019 дата публикации

METHOD OF CONTROLLING GAS GENERATOR POWER AND TORQUE OUTPUT

Номер: US20190032577A1
Автор: Castellani Simone, CIPOLLA Lorenzo, DELLAVALLE Federico, FELIPPONE Felice, GABBI Giampaolo
Принадлежит:

The present disclosure is directed to a system for controlling an output of a gas generator via an operator manipulated input device. The system includes one or more sensors measuring one or more environmental conditions, a gas generator shaft speed, and a power turbine torque. The system further includes an operator manipulated input device and one or more controllers including one or more processors and one or more memory devices. The one or more memory devices stores instructions that when executed by the one or more processors cause the one or more processors to perform operations. The operations include receiving, via an operator manipulated input device, a throttle lever position defining at least an idle position, a takeoff position, and one or more intermediate positions therebetween; receiving, via one or more sensors, one or more environmental conditions, wherein the environmental condition includes one or more of an ambient air temperature, an ambient air pressure, and an ambient airflow rate; determining, via the controller, a first commanded fuel flow of the gas generator based on a gas generator speed output curve based at least on the throttle lever position, the one or more environmental conditions, and a coefficient reference table; determining, via the controller, a second commanded fuel flow of the gas generator based on a power turbine torque output curve based at least on the one or more environmental conditions; and generating, via the gas generator, a gas generator output based on the first commanded fuel flow or the second commanded fuel flow. 1. A system for controlling an output of a gas generator via an operator manipulated input device , the system comprising one or more sensors measuring one or more environmental conditions , a gas generator shaft speed , and a power turbine torque , the system further comprising an operator manipulated input device and one or more controllers comprising one or more processors and one or more memory ...

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Номер записи: 71
09-02-2017 дата публикации

METHOD FOR SYNCHRONISING THE ENGINES OF AN AIRPLANE WITH DUAL INTERMEDIATE STATE

Номер: US20170036774A1
Автор: Nobelen Florent
Принадлежит: SAFRAN AIRCRAFT ENGINES

A method for synchronizing the engines of an airplane according to one activation logic having a deactivated state (), an armed state (), and one activated state (), in which: 1. A method for synchronising there between engines of an airplane , using at least one activation logic per engine , the activation being intended to check the safety and/or activation conditions in order to apply the synchronisation , with each activation logic defining and switching between at least a deactivated state , an armed state , and an activated state , with the method comprising , per engine:the switching of the activation logic from the deactivated state to the armed state when an activation order is given by the pilot of the airplane;the periodical checking of the safety and/or activation conditions relative to said states, in order to define whether said conditions are met or not met,the switching of the activation logic from the armed state to the activated state when some of the safety and/or activation conditions are met; andthe switching of the activation logic from the activated state or the armed state to the deactivated state when a deactivation order is given by the pilot or when some of said safety conditions are not met,wherein:the switching of the activation logic from the armed state to the activated state is carried out via a first and then a second successive intermediate state of the activation logic,every instance of the activation logic switching from the second intermediate state to the activated state involves exchanging such data between the engines carried out by an exchange digital link, so that:the switching of the activation logic of one of the engines to the activated state requires that the safety and activation conditions applied to the other engine(s) are all met,and if the activation logic of one of the engines switches to the deactivated state, the activation logic of the other engine(s) automatically does so as well; andfor each engine, the ...

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Номер записи: 72
12-02-2015 дата публикации

METHOD FOR FUEL SPLIT CONTROL TO A GAS TURBINE USING A MODIFIED TURBINE FIRING TEMPERATURE

Номер: US20150040571A1
Автор: Coomar Nilanjan Prosad
Принадлежит: GENERAL ELECTRIC COMPANY

A method for controlling fuel splits to a controller is provided that includes comparing a combustor operating parameter to a predefined combustor operating parameter range. If the combustor operating parameter is outside its respective range, then a modified turbine firing temperature is calculated. The modified turbine firing temperature may then be used to determine the fuel splits to the combustor using a nominal fuel splits lookup table. 1. A method for controlling fuel splits to a combustor of a gas turbine , comprising performing the following with a controller:determining a reference turbine firing temperature of the gas turbine;monitoring a combustor operating parameter;comparing the combustor operating parameter to a predefined combustor operating parameter range;computing a modified turbine firing temperature as a function of the combustor operating parameter if the combustor operating parameter is outside of the predefined combustor operating parameter range; anddetermining the fuel splits to the combustor based on the modified turbine firing temperature and a nominal fuel splits lookup table.2. A method as in claim 1 , wherein the combustor operating parameter is any one of claim 1 , or combination of fuel composition claim 1 , compressor inlet temperature claim 1 , ambient humidity claim 1 , inlet guide vane angle claim 1 , nitrogen oxides emissions claim 1 , or combustion dynamics in the combustor.3. A method as in claim 1 , wherein the step of comparing further comprises determining a shift value based on the value of the combustor operating parameter if the combustor operating parameter is outside the predefined combustor operating parameter range claim 1 , and wherein the step of computing further comprises summing the shift value and the reference turbine firing temperature to determine the modified turbine firing temperature.4. A method as in claim 1 , wherein the combustor operating parameter is fuel composition as measured by a Modified Wobbe ...

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Номер записи: 73
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: 74
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: 75
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: 76
24-02-2022 дата публикации

SYSTEM AND METHOD FOR MONITORING FUEL ADDITIVES

Номер: US20220056841A1
Автор: Cordatos Haralambos, Dardas Zissis A., She Ying
Принадлежит: Raytheon Technologies Corporation

A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser. 110-. (canceled)11. A method for monitoring fuel additives on board a vehicle , comprising:flowing fuel from a fuel tank along a fuel line to an engine;sensing concentration of additives in the fuel at a point along the fuel line;determining whether the concentration of the additive in the fuel is less than a fuel additive specification;when the concentration is less than the specification, operating a flow control device to divert a portion of the fuel from the fuel line along a parallel line to a fuel additive dispenser.12. The method of claim 11 , wherein the fuel additive dispenser is positioned along a fuel additive bypass line connected at an upstream end to the flow control device and connected at a downstream end back to the fuel line.13. The method of claim 12 , wherein the fuel additive sensor is positioned upstream of or at the flow control device.14. The method of claim 12 , wherein the fuel additive sensor is positioned downstream of the downstream end of the fuel additive bypass line.15. The method of claim 11 , wherein the controller is configured to compare the concentration with a pre-set additive requirement specification claim 11 , and to control the flow control device to increase flow through to fuel additive dispenser when the concentration is less than the specification.16. The method of claim 15 , wherein the controller is ...

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Номер записи: 77
07-02-2019 дата публикации

SYSTEMS AND METHODS FOR VANADIUM CORROSION INHIBITORS

Номер: US20190040800A1
Автор: Aboujaib Maher, AMANCHERLA Sundar, Anand Krishnamurthy, JR. David Terry, Khalidi Abdurrahman Abdallah, Montagne Pierre Olivier, Trayhan, Vierling Matthieu Paul Frederic
Принадлежит:

A system includes a turbine combustor and one or more supply circuits configured to supply one or more fluids to the turbine combustor. The one or more supply circuits include at least a liquid fuel supply circuit fluidly coupled to a liquid fuel source and configured to supply a liquid fuel from the liquid fuel source to the turbine combustor. The system also includes a corrosion inhibitor injection system including a magnesium source storing a magnesium-based inhibitor that includes magnesium oxide (MgO) and an yttrium source storing an yttrium-based inhibitor that includes yttrium oxide (YO). The corrosion inhibitor injection system is fluidly coupled to the turbine combustor and the one or more supply circuits, and is configured to inject the magnesium-based inhibitor and the yttrium-based inhibitor as vanadium corrosion inhibitors into the turbine combustor or the one or more supply circuits. 1. A system , comprising:a turbine combustor;one or more supply circuits configured to supply one or more fluids to the turbine combustor, wherein the one or more supply circuits comprise at least a liquid fuel supply circuit fluidly coupled to a liquid fuel source and configured to supply a liquid fuel from the liquid fuel source to the turbine combustor; and{'sub': 2', '3, 'a corrosion inhibitor injection system comprising a magnesium source storing a magnesium-based inhibitor comprising magnesium oxide (MgO) and an yttrium source storing an yttrium-based inhibitor comprising yttrium oxide (YO), the corrosion inhibitor injection system being fluidly coupled to the turbine combustor and the one or more supply circuits, and wherein the corrosion inhibitor injection system is configured to inject the magnesium-based inhibitor and the yttrium-based inhibitor as vanadium corrosion inhibitors into the turbine combustor or the one or more supply circuits.'}2. The system of claim 1 , wherein the liquid fuel contains vanadium claim 1 , sodium claim 1 , potassium claim 1 , or any ...

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Номер записи: 78
12-02-2015 дата публикации

SHAFT DISPLACEMENT CONTROL

Номер: US20150046061A1
Автор: Cookerly Alan B., Copeland Andrew D.
Принадлежит:

An aircraft powerplant having a shaft is disclosed in one embodiment in which a squeeze-film damper is used. The squeeze-film damper includes a plurality of sectors having a working fluid. A pressure can be controlled in the working fluid to the sectors to discourage changes in the sectors as a result of vehicle maneuvering. A controller is used to operate upon sensed aircraft motion and regulate pressure in the sectors. 1. An apparatus comprising:a vehicle powerplant structured to provide power and having a shaft structured to rotate with a bladed air moving device disposed within an enclosure that forms a flow path;a bearing assembly supportingly coupled with the shaft;a squeeze-film damper positioned between the bearing assembly and a housing structured to contain the bearing assembly, the squeeze-film damper having a plurality of sectors that are each in fluid communication with a fluid pressure source; anda controller structured to operate upon a sensed vehicle motion and provide a fluid pressure for the plurality of sectors to influence a clearance between the bladed air moving device and the enclosure.2. The apparatus of claim 1 , wherein the plurality of sectors are circumferentially distributed around the squeeze-film damper claim 1 , and which further includes a pressure regulating device capable of changing the fluid pressure in at least one of the plurality of sectors.3. The apparatus of claim 2 , wherein the plurality of sectors are each in communication with a single fluid pressure source.4. The apparatus of claim 1 , wherein at least one of the plurality of sectors is bounded by an o-ring.5. The apparatus of claim 1 , wherein a maneuvering of a vehicle is sensed by one of an accelerometer and a rate gyro claim 1 , and wherein the controller is structured to produce a signal to change a pressure in a sector and counteract a change in angular momentum of the vehicle powerplant.6. The apparatus of claim 5 , which further includes a communications bus ...

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Номер записи: 79
01-05-2014 дата публикации

SYSTEM FOR DETECTING SHAFT SHEAR EVENT

Номер: US20140121934A1
Автор: Dooley Kevin Allan
Принадлежит:

Systems and methods for detecting a shaft shear event in a turbine engine. An accelerometer coupled to the engine detects an axial acceleration indicative of a shaft shear event in the engine. A control system is configured to, in response to the detected axial acceleration, transmit a signal to initiate a shut down of a fuel system of the engine. 1. A system for detecting a shaft shear event in a turbine engine , the system comprising:an accelerometer coupled to the engine for detecting an axial acceleration indicative of a shaft shear event in the engine; anda control system configured to, in response to the detected axial acceleration, transmit a signal to initiate a shut down of a fuel system of the engine.2. The system of wherein the control system is an engine control unit configured to execute machine-readable instructions to cause the engine control unit to:receive a signal from the accelerometer representing a detection of axial acceleration of the engine that is indicative of the shaft shear event; andtransmit the signal to initiate the shut down of the fuel system of the engine.3. The system of wherein the system further comprises a plurality of accelerometers claim 2 , and the instructions further cause the engine control unit to receive signals from the plurality of accelerometers claim 2 , to determine whether at least a minimum number of the received signals indicate that a shaft shear event has occurred claim 2 , and to transmit the signal to initiate the shut down only if at least the minimum number of signals indicate that the shaft shear event has occurred.4. The system of wherein the instructions further cause the engine control unit to compare acceleration information received from the received signal with an expected acceleration profile to verify that a shaft shear event has occurred claim 2 , and to transmit the signal to initiate the shut down only after occurrence has been verified.5. The system of wherein the control system is a solid ...

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Номер записи: 80
16-02-2017 дата публикации

FUEL CONTROL METHOD FOR GAS TURBINE, CONTROL DEVICE FOR EXECUTING SAID METHOD, AND GAS TURBINE INSTALLATION PROVIDED WITH SAID CONTROL DEVICE

Номер: US20170044994A1
Автор: Murakami Masayuki, NAKANISHI Yoshiaki, Suzuki Hiroki, Takata Yasutsugu
Принадлежит: Mitsubishi Hitachi Power Systems, Ltd.

A control device includes a fuel equivalent value calculation unit for determining the flow rate of fuel supplied to a gas turbine in accordance with a target value deviation between an actual rotation speed and a target rotation speed, an upper limit deviation calculation unit for obtaining an upper limit deviation which is a deviation between a set upper limit output and an actual output, a lower limit deviation calculation unit for obtaining a lower limit deviation which is a deviation between a set lower limit output and the actual output, and a parameter-changing unit for changing any one parameter among the target rotation speed, the actual rotation speed, and the target value deviation so that the target value deviation decreases when the actual rotation speed decreases and the upper limit deviation is small, and so that the target value deviation increases when the actual rotation speed increases and the lower limit deviation is small. 1. A control device for a gas turbine comprising:a target value output unit outputting a target value equivalent to a target rotation speed of the gas turbine;a target value deviation calculation unit obtaining a target value deviation, the target value deviation being a deviation of the target value with respect to an actual rotation speed equivalent value equivalent to an actual rotation speed of the gas turbine;a fuel equivalent value calculation unit determining a fuel equivalent value equivalent to a flow rate of fuel supplied to the gas turbine in accordance with the target value deviation;a rotation speed variation detecting unit detecting a variation of the actual rotation speed of the gas turbine;an upper limit deviation calculation unit obtaining an upper limit deviation, the upper limit deviation being a deviation of a set upper limit output of the gas turbine with respect to an actual output of the gas turbine;a lower limit deviation calculation unit obtaining a lower limit deviation, the lower limit deviation ...

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Номер записи: 81
16-02-2017 дата публикации

METHOD FOR SELECTING OPERATING POINTS OF A GAS TURBINE

Номер: US20170044995A1
Автор: Amann Christian, Beckmann Björn, Deuker Eberhard, Kadau Kai, Kock Boris Ferdinand, Rollmann Georg, Schmitz Sebastian, Zwingenberg Marcel
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A method for selecting operating points of a gas turbine while taking into consideration at least one controlled variable, the operating points being defined at least by parameter combinations of manipulated variables, wherein the operating points are automatically selected on the basis of already known parameter combinations by using an interpolation method, the Kriging interpolation method being used as the interpolation method. 1. A method for selecting operating points of a gas turbine while taking into consideration at least one controlled variable , the operating points being defined at least by parameter combinations of manipulated variables , the method comprising:selecting the operating points automatically using an interpolation method based on already known parameter combinations,wherein the Kriging interpolation method is used as the interpolation method.2. The method as claimed in claim 1 ,wherein the manipulated variables comprise a total fuel volume flow supplied to the gas turbine, and/or a distribution of the total fuel volume flow supplied to the gas turbine over individual burner stages of the gas turbine, and/or a gas turbine outlet temperature and/or a position of guide vanes of the gas turbine.3. The method as claimed in claim 1 ,wherein the controlled variables describe the emission behavior of the gas turbine and/or the combustion stability of the gas turbine.4. The method as claimed in claim 1 ,wherein in the selection of operating points the influence of interfering variables is taken into consideration.5. The method as claimed in claim 4 ,wherein the interfering variables comprise the ambient temperature and/or the air humidity of the environment and/or the ambient pressure.6. The method as claimed in claim 1 ,wherein the already known parameter combinations are such as have been determined by manual variation of the parameters.7. The method as claimed in claim 6 ,wherein in the manual variation of the parameters, known parameter ...

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Номер записи: 82
16-02-2017 дата публикации

METHOD FOR OPERATING A BURNER ASSEMBLY

Номер: US20170044996A1
Автор: Deuker Eberhard, Kock Boris Ferdinand, Simon Dieter
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A method for operating a burner assembly, in particular a burner assembly of a gas turbine, wherein an evaluation variable representing the combustion stability is determined and at least one control variable is altered, at least based on the determined evaluation variable, when the determined evaluation variable does not fall within a previously defined desired range, the desired range of the evaluation variable being constant over the entire output range of the machine, and wherein the evaluation variable is determined based on measured maximum actual amplitudes in previously defined frequency bands and measured actual outputs of the burner assembly. 1. A method for operating a burner assembly , the method comprising:determining an evaluation variable representing the combustion stability, andaltering at least one control variable at least on the basis of the determined evaluation variable when the determined evaluation variable does not lie within a previously defined desired range,wherein the desired range of the evaluation variable is constant over the entire output range of the machine, andwherein the evaluation variable is determined on the basis of measured maximum actual amplitudes in previously defined frequency bands and measured actual outputs of the burner assembly.2. The method as claimed in claim 1 ,wherein the actual amplitudes are alternating pressure actual amplitudes or component acceleration actual amplitudes.3. The method as claimed in claim 1 ,wherein the evaluation variable is determined using output-dependent weighting factors and/or frequency-dependent weighting factors.4. The method as claimed in claim 1 , wherein the evaluation variable is defined as the sum{'br': None, 'sub': f1', '1', '1', 'f2', '2', '2', 'fn', 'n', 'n, 'i': ·k', '·A', '+g', '·k', '·A', '+ . . . +g', '·k', '·A, 'sup': 2', '2', '2, 'g'}{'sub': 1', 'n', '1', 'n', 'f1', 'fn', '1', 'n', '1', 'n, 'wherein Ato Arepresent the maximum amplitudes in the frequency bands fto f, gto ...

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Номер записи: 83
15-02-2018 дата публикации

SHAFT SHEAR DETECTION IN GAS TURBINE ENGINES

Номер: US20180045071A1
Автор: AHMAD Zubair, PERERA Ryan John, ROACH Andrew Elliot
Принадлежит:

There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine. The method comprises determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a shaft of a second spool of the engine different from the first spool, the set of threshold values varying throughout a flight envelope, the detection threshold defining, for each spool speed value, at least one load transfer value beyond which a shaft event is detected. Operation values of the spool speed and the load transfer are obtained during operation of the engine, and the operation values are compared to the detection threshold. The shaft event is detected when the operation values are below the detection threshold. 1. A method for detecting a shaft event in a gas turbine engine , the method comprising:determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a shaft of a second spool of the engine different from the first spool, the set of threshold values varying throughout a flight envelope, the detection threshold defining, for each spool speed value, at least one load transfer value beyond which a shaft event is detected;obtaining operation values of the spool speed and the load transfer during operation of the engine;comparing the operation values to the detection threshold; anddetecting the shaft event when the operation values are beyond the detection threshold.2. The method of claim 1 , wherein the first spool is a high pressure spool and the second spool is a low pressure spool claim 1 , and wherein obtaining the operation values comprises measuring the load transfer through a low pressure shaft.3. The method of claim 2 , wherein measuring the load transfer comprises measuring the load transfer with a torque sensor in a gearbox of the engine.4. ...

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Номер записи: 84
08-05-2014 дата публикации

GAS TURBINE BURNER

Номер: US20140123670A1
Автор: Eroglu Adnan
Принадлежит: ALSTOM Technology Ltd

The burner of a gas turbine includes a swirl generator and, downstream of it, a mixing tube. The swirl generator is defined by at least two walls facing one another to define a conical swirl chamber and is provided with nozzles arranged to inject a fuel and apertures arranged to feed an oxidiser into the swirl chamber. The burner includes a lance which extends along a longitudinal axis of the swirl generator and is provided with side nozzles for ejecting a fuel within the burner. The side nozzles have their axes inclined with respect to the axis of the lance and can be positioned along the axis of the burner. 2. A method for operating a burner having a swirl generator defined by at least two walls facing one another to define a substantially conical swirl chamber , the swirl generator including nozzles arranged to inject a fuel and apertures arranged to feed an oxidizer into said swirl chamber , a mixing tube positioned downstream of the swirl generator , and a lance positioned inside at least the swirl generator , the lance extending along a longitudinal axis of the swirl generator and being provided with side nozzles for ejecting fuel oil within the burner , the lance side nozzles having axes inclined with respect to an axis of the lance , the method comprising:at starting, injecting about 80% of the oil through lance tip nozzle and injecting about 20% through the lance side nozzles;at idle operation, injecting about 75% of the oil through the lance tip nozzle and injecting about 25% through the lance side nozzles;at part load, injecting about 50% of the oil through the lance tip nozzle and injecting about 50% through the lance side nozzles; andat full load, injecting about 10% of the oil through the lance tip nozzle and injecting about 90% through the lance side nozzles.3. A method for operating a burner having a swirl generator defined by at least two walls facing one another to define a substantially conical swirl chamber , the swirl generator including nozzles ...

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Номер записи: 85
03-03-2022 дата публикации

Systems and methods for detecting a fuel leak

Номер: US20220065736A1
Автор: Willy Steve Ziminsky
Принадлежит: General Electric Co

Systems and methods of detecting a fuel leak are provided. A method of detecting a fuel leak within a turbomachine combustor includes a step of monitoring, by a controller, a sensor output from a particulate matter sensor positioned on a component within the combustor. The sensor output includes one of a fault state sensor output or a non-fault state sensor output. The method further includes receiving, with the controller, the fault state sensor output from the particulate matter sensor when a fuel leak is present within the combustor.

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Номер записи: 86
26-02-2015 дата публикации

METHOD FOR CONTROLLING A GAS TURBINE GROUP

Номер: US20150052904A1
Автор: FERREIRA-PROVIDAKIS Theodoros, LIPARI Sebastian, Meeuwissen Thiemo, Singla Ghislain
Принадлежит:

The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group. 1. A method for controlling a gas turbine group comprising , in a flow direction of a working fluid , a first combustion chamber , a first turbine connected downstream of the first combustion chamber , a second combustion chamber connected downstream of the first turbine which operates by autoignition , a second turbine connected downstream of the second combustion chamber , and a load connected to be driven by the first and second turbines , the method comprising:measuring a temperature TAT1 at an outlet of the first turbine;determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio SIR and temperature TAT1;adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel mass flow feeding the first combustion chamber of the gas ...

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Номер записи: 87
26-02-2015 дата публикации

Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity

Номер: US20150052905A1
Автор: Ilya Aleksandrovich Slobodyanskiy, William Francis Carnell, JR.
Принадлежит: General Electric Co

Systems and methods for pulse-width modulation of late lean liquid injection velocity can be provided by certain embodiments of the disclosure. In one embodiment, a gas turbine combustor utilizing a late lean injection scheme can be provided, wherein the combustor can include a combustor liner and a transition piece. Methods described herein can allow for dynamic and intelligent adjustment of the late lean injection scheme based on a duty cycle and, optionally, a measured combustion gases temperature profile. The adjustments can involve a pulse-width modification of the duty cycle, which in turn can affect a fuel introduction velocity. Dynamic control of the fuel introduction velocity can provide for improved fuel droplet penetration and moving the heat release zone away from walls of the transitional piece.

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Номер записи: 88
22-02-2018 дата публикации

SYNCHRONIZATION OF AIRCRAFT ENGINES

Номер: US20180050809A1
Автор: "CARON LECUYER Alexis", BOGDAN Mirel, BRODEUR Andre, COLAVINCENZO Stephen, JOVICIC Dragan
Принадлежит:

Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine. 1. A method for improving synchronization of two engines on an aircraft where each engine comprises a first spool and a second spool , and , where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine , the method comprising:receiving a value of a sensed parameter useful in controlling the first engine, the sensed parameter being indicative of one of altitude and a flow of bleed air from the first engine;adding a bias to the value; andusing the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine and thereby reduce a difference in rotational speed between the second spool of the first engine and the second spool of the second engine.2. The method as defined in claim 1 , comprising determining the bias based on a difference in rotational speed between the second spool of the first engine and the second spool of the second engine.3. The method as defined in claim 1 , comprising determining the bias based on the value of the sensed parameter.4. The method as defined in claim 1 , comprising receiving feedback indicative of the ...

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Номер записи: 89
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: 90
23-02-2017 дата публикации

SYSTEM AND METHOD FOR ABATEMENT OF DYNAMIC PROPERTY CHANGES WITH PROACTIVE DIAGNOSTICS AND CONDITIONING

Номер: US20170051682A1
Автор: Pastecki Patrick Edward, Simmons James Arthur
Принадлежит:

A system includes a fluid transfer system that has instrumentation configured to measure fuel properties; a fluidic buffer volume device located downstream of a fuel sensing point, wherein the fluidic buffer volume device is configured to provide a residence time for the fuel within the fluidic buffer volume device to enable a signal representative of the fuel properties to be communicated to enable adjustment of operating conditions of a fuel consuming system as the fuel is provided; and a controller programmed to receive properties of the fuel consuming system, receive the signal, receive properties of the fluidic buffer volume device, and generate a time-resolved volumetric grid that characterizes fuel transport properties of the fuel for different flow conditions and times based on the properties of the fuel consuming system, the fuel properties, and the properties of the fluidic buffer volume device. 1. A system , comprising: instrumentation configured to measure one or more properties of a fuel;', 'a fluidic buffer volume device located downstream of a fuel sensing point of the instrumentation, wherein the fluidic buffer volume device is configured to provide a residence time for the fuel within the fluidic buffer volume device to enable a signal from the instrumentation representative of an analysis of the one or more properties of the fuel to be communicated to enable adjustment of operating conditions of a fuel consuming system by a time that the fuel is provided to the fuel consuming system; and', 'a controller programmed to receive one or more properties of the fuel consuming system, to receive the signal from the instrumentation representative of the one or more properties of the fuel, and to receive one or more properties of the fluidic buffer volume device, and to generate a time-resolved volumetric grid that characterizes fuel transport properties of the fuel for different flow conditions and flow times based at least on the one or more properties of ...

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Номер записи: 91
23-02-2017 дата публикации

Devices and methods for early prediction of impending instabilities of a system

Номер: US20170051683A1
Автор: Meenatchidevi MURUGESAN, Sujith Raman Pillai Indusekharan Nair, Vineeth Nair Vinod, Vishnu R UNNI
Принадлежит: INDIAN INSTITUTE OF TECHNOLOGY MADRAS

The invention includes a method for predicting the operational state of equipment with turbulent flow characterized by time series data relating to its operation. The invention further includes a system and method for predicting the onset of an impending oscillatory instability. Further, the invention includes a system and method for identifying an impending absorbing transition such as flame blowout in combustion systems. A variable representing the dynamics of operation is measured with the help of a sensor, to obtain time series data. A complex network is then derived from the measured time series data. Network properties are then calculated using the complex network to identify the state of stability relating to operation of the equipment. The stability information may include one of thermoacoustic instability, aero-elastic instability such as flutter, flow-induced vibration, magneto-hydrodynamic, aerodynamic, aeromechanical, aero-acoustic instability or onset of flame blowout of a combustor.

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Номер записи: 92
22-02-2018 дата публикации

INJECTOR DEVICE AND METHOD FOR MANUFACTURING AN INJECTOR DEVICE

Номер: US20180051884A1
Автор: BAIBUZENKO Igor, MAURER Michael, MYLNIKOV Sergey, STYTSENKO Alexey
Принадлежит: ANSALDO ENERGIA SWITZERLAND AG

An injector device is disclosed which includes an elongated body with a leading edge and a trailing edge, gas nozzles and oil nozzles, an oil supply duct housed within the elongated body and connected to the oil nozzles, and a gas supply duct housed within the elongated body and connected to the gas nozzles. The oil supply duct is connected to the gas supply duct only between one or more oil nozzles and one gas nozzles, and the gas supply duct is connected to the elongated body only via bridges. 1. An injector device for a burner of a gas turbine comprising:an elongated body with a leading edge and a trailing edge;gas nozzles and oil nozzles;an oil supply duct housed within the elongated body and connected to the oil nozzles; anda gas supply duct housed within the elongated body and connected to the gas nozzles;wherein:the oil supply duct is connected to the gas supply duct only between at least one oil nozzles and one gas nozzles; andthe gas supply duct is connected to the elongated body only via at least one bridge.2. The injector device of claim 1 , wherein:a connection between the oil supply duct and the gas supply duct is at a the terminal part of the oil nozzle and gas nozzle.3. The injector device of claim 1 , wherein the elongated body comprises:at least a channel at the leading edge, wherein the at least one bridge is provided only between the gas supply duct and the channel.4. The injector device of claim 1 , comprising:only two bridges, each bridge being connected at one side of the gas supply duct.5. The injector device of claim 1 , wherein:the trailing edge has a lobed configuration or a straight configuration or a zig-zag configuration.6. The injector device of claim 1 , comprising:air nozzles.7. The injector device of claim 6 , wherein:the air nozzles and/or gas nozzles and/or oil nozzles are at the trailing edge.8. The injector device of claim 1 , being a selective laser melted (SLM) structure.9. A method for manufacturing an injector device having: ...

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Номер записи: 93
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: 94
05-03-2015 дата публикации

Control Method for Gasification Power Generation System

Номер: US20150059351A1
Автор: FUKUHARA Hirotsugu, KISO Fumihiko, Yoshida Yasuhiro
Принадлежит:

The present invention relates to an operation control method for a gasification power generation system for gasifying carbon-based fuel such as coal in a gasifier using oxygen or oxygen-enriched air as an oxidizing agent, burning the obtained syngas as fuel in a gas turbine, driving the gas turbine by the syngas, driving a steam turbine by steam generated using exhaust heat of the gas turbine, thus executing combined power generation. 1. A control method for a gasification power generation system including a gasifying equipment for gasifying carbon based fuel by an oxidizing agent in a gasifier and generating syngas , a gas clean-up unit for obtaining a syngas purified by removing a sulfur compound in the syngas generated in the gasifier , and a gas turbine equipment for generating power by burning the purified syngas obtained by the gas clean-up unit as fuel , comprising the steps of:inferring a syngas beating value at a gasifier outlet and a syngas quantity from a property and a feed rate of the carbon based fuel fed to the gasifier of the gasifying equipment, a flow rate of nitrogen or water used for transport of the carbon based fuel to the gasifier, and a property and a feed rate of the oxidizing agent fed to the gasifier;analyzing syngas sampled from instruments or pipes between the gasifier of the gasifying equipment and the gas turbine equipment, and correcting the inferred value of the syngas heating value using analytical values of the sampled syngas;inferring a time lag until the syngas heating value is changed at a gas turbine equipment inlet after the feed rate of the carbon based fuel fed to the gasifier is changed from the inferred value of the syngas quantity, volumes of the instruments and the pipes between the gasifier of the gasifying equipment and the gas turbine equipment, and a temperature and a pressure of the syngas in the instruments and the pipes; andsetting the syngas heating value inferred from the feed rate of the carbon based fuel fed ...

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Номер записи: 95
05-03-2015 дата публикации

DUAL FUEL COMBUSTOR FOR A GAS TURBINE ENGINE

Номер: US20150059352A1
Автор: Myers Geoffrey D.
Принадлежит: GENERAL ELECTRIC COMPANY

The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel, injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor. 1. A dual fuel combustor for a gas turbine engine , the combustor comprising;a primary premixer positioned within a head end plenum of the combustor; and a dual fuel injection system positioned within the head end plenum and upstream of the premixer;wherein the injection system is configured to inject a gas feel about an inlet end of the premixer when the combustor operates on the gas fuel; andwherein the injection system is configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel,2. The dual fuel combustor of claim 1 , wherein the premixer comprises a micro-mixer comprising a. plurality of micro-mixer tubes positioned about at least one fuel tube.3. The dual fuel claim 1 , combustor of claim 1 , wherein the injection system comprises at least one toroidal injection manifold extending about a circumference of the premixer.4. The dual fuel combustor of claim 3 , wherein the toroidal injection manifold comprises an internal sleeve and an external sleeve surrounding the internal sleeve claim 3 , wherein the internal sleeve is configured to receive a flow of the liquid fuel therein claim 3 , and wherein the external sleeve is configured to direct a flow of air against the internal ...

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Номер записи: 96
05-03-2015 дата публикации

Gas Turbine Combustion System

Номер: US20150059353A1
Автор: Akinori Hayashi, Tomohiro Asai, Yasuhiro Akiyama
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

The present invention provides a gas turbine combustion system capable of minimizing unburned content of a gas fuel under all load conditions from partial load to rated load. A gas turbine combustion system includes: a plurality of gas fuel burners 32, 33; an IGV 9 that adjusts a flow rate of air to be mixed with a gas fuel; and a control system 500 that temporarily reduces an air flow rate from a reference flow rate to a set flow rate by outputting a signal to the IGV 9 when a combustion mode is switched from a partial combustion mode in which the gas fuel is burned with part of the gas fuel burners 32, 33 to a full combustion mode in which the gas fuel is burned with all of the gas fuel burners 32, 33.

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Номер записи: 97
10-03-2022 дата публикации

SYSTEMS AND METHODS FOR OPERATION OF A FLEXIBLE FUEL COMBUSTOR

Номер: US20220074594A1
Автор: Fetvedt Jeremy Eron, LU XIJIA, McGroddy Peter Michael
Принадлежит:

The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a power production method utilizing different fuel chemistries. Combustion of the different fuel mixtures can be controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel chemistries. 1. A method for normalizing combustion in a power production process , the method comprising:inputting to a combustor with a combustion zone and a dilution zone that is downstream from the combustion zone a fuel, an oxidant, and diluent so that the fuel is combusted to provide a combustor exhaust stream; andpassing the combustor exhaust stream through a turbine to generate power;wherein the fuel is a variable fuel is that subject to compositional changes during the power production process;wherein the diluent comprises carbon dioxide;wherein the diluent is mixed with the fuel, is mixed with the oxidant, and is also separately injected into the dilution zone of the combustor; andwherein the method also comprises implementing at least one control function such that one or more of fuel heating value, flame temperature, combustion pressure, combustor exit temperature, mass flow out of the combustor, turbine inlet flow chemistry, and turbine speed varies from a predetermined value by no greater than 10% and thus accounts for the compositional changes to the fuel during the power production process so that combustion is normalized, said control function including one or more of:varying a ratio of diluent mixed with oxygen in the oxidant;varying a temperature of the oxidant input to the combustor;varying a temperature of the fuel input to the combustor;varying a temperature of the diluent input to the combustor in the dilution zone;varying a flow rate of the oxidant input to the combustor;varying ...

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Номер записи: 98
03-03-2016 дата публикации

Gaseous Fuel Wobbe Index Modification Skid

Номер: US20160060554A1
Автор: Pastrana Ryan Margate, Taylor Robert Warren
Принадлежит:

A method of regulating a Modified Wobbe index number (MWI) of a multi-composition gas fuel supplied to one or more combustors of a gas turbine is disclosed. A rapid temperature swing absorber comprising a skid or platform comprising one or more reactor vessels is also disclosed, the one or more vessels comprising a plurality of hollow fibers each of which is impregnated by one or more sorbents for the separation of one or more deleterious gases from a fuel stream. 1. A method of regulating a Modified Wobbe index number (MWI) of a multi-composition gas fuel comprising:separating particulates and moisture from an initial gas fuel stream, the separating performed with a media that is both hydrophobic and oleophobic; andabsorbing one or more deleterious gases present in the initially treated gas fuel stream using a plurality of fibers impregnated with sorbents to absorb the one or more deleterious gases to afford a secondary gas fuel stream, thereby changing the MWI of the secondary gas fuel stream relative to the initial gas fuel stream.2. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the multi-composition gas fuel is supplied to one or more combustors of a gas turbine.3. A method of regulating a MWI of a multi-composition gas fuel according to claim 2 , further comprising providing a control system for regulating fuel and air flow to one or more combustors.4. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the hydrophobic and oleophobic media is an ePTFE media.5. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the plurality of fibers impregnated with sorbents are hollow fibers.6. A method of regulating a MWI of a multi-composition gas fuel according to claim 4 , wherein the plurality of hollow fibers impregnated with sorbents are present in one or more reactor vessels.7. A method of regulating a MWI of a multi-composition gas fuel ...

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Номер записи: 99
21-02-2019 дата публикации

CONTROL OF FUEL FLOW FOR POWER GENERATION BASED ON DC LINK LEVEL

Номер: US20190055890A1
Автор: Ethier Jason How-Ring, Lakov German, Wang Ivan
Принадлежит: Dynamo Micropower Corporation

A power generating unit, control unit and modular power generating system. A power generating unit includes an engine-generator set including an engine that produces mechanical power and a generator mechanically coupled to the engine. The generator converts the mechanical power to electrical power provided to a DC link. The control unit includes at least one controller configured to control fuel flow to the engine based on a voltage of the DC link. 1. A power generating unit , comprising: an engine that produces mechanical power; and', 'a generator coupled to the engine, wherein the generator receives the mechanical power from the engine and converts the mechanical power to a first form of electrical power;, 'an engine-generator set, comprisinga first power converter that receives the first form of electrical power from the generator and converts the first form of electrical power to a second form of electrical power;a DC link that receives the second form of electrical power from the first power converter;an energy storage unit that receives the second form of electrical power from the DC link; andat least one controller configured to control fuel flow to the engine based on a voltage of the DC link.2. The power generating unit of claim 1 , further comprising a power delivery unit that receives the second form of electrical power from the DC link claim 1 , and converts the second form of electrical power to a third form of electrical power claim 1 , and provides the third form of electrical power as the output of the power generating unit.3. The power generating unit of claim 1 , wherein the engine that produces mechanical power is a gas turbine engine.4. The power generating unit of claim 3 , wherein the gas turbine engine is a two-shaft gas turbine engine comprising:a compressor;a first turbine that is mechanically coupled to the compressor; anda second turbine that is not mechanically coupled to the compressor or first turbine,wherein gas from the first turbine ...

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Номер записи: 100