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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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Применить Всего найдено 6874. Отображено 100.
16-07-1999 дата публикации

ПОРШНЕВОЙ ПНЕВМОДВИГАТЕЛЬ

Номер: RU0000010423U1
Автор: Бычковский Е.Г., Ваняшов А.Д., Кабаков А.Н., Калекин В.С.
Принадлежит: Омский государственный технический университет

1. Поршневой пневмодвигатель, содержащий цилиндр, в стенках которого выполнены выпускные окна, поршень, впускной штуцер, а также механизм газораспределения, выполненный в виде нормально открытого клапана, который снабжен закрепленным на пружине запорным элементом, отличающийся тем, что нормально открытый клапан содержит дополнительно пружину сжатия, расположенную внутри пружины растяжения и установленную в выточках, выполненных в запорном элементе и регулировочном винте, причем пружина сжатия выполнена с жесткостью, меньшей жесткости пружины растяжения. 2. Пневмодвигатель по п.1, отличающийся тем, что жесткость пружин сжатия и растяжения удовлетворяет соотношению С = 0,1 - 0,6 С. (19) RU (11) 10 423 (13) U1 (51) МПК F01L 9/02 (1995.01) F01L 25/00 (1995.01) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К СВИДЕТЕЛЬСТВУ (21), (22) Заявка: 98121944/20, 04.12.1998 (24) Дата начала отсчета срока действия патента: 04.12.1998 (46) Опубликовано: 16.07.1999 (72) Автор(ы): Бычковский Е.Г., Кабаков А.Н., Калекин В.С., Ваняшов А.Д. 1 0 4 2 3 R U (57) Формула полезной модели 1. Поршневой пневмодвигатель, содержащий цилиндр, в стенках которого выполнены выпускные окна, поршень, впускной штуцер, а также механизм газораспределения, выполненный в виде нормально открытого клапана, который снабжен закрепленным на пружине запорным элементом, отличающийся тем, что нормально открытый клапан содержит дополнительно пружину сжатия, расположенную внутри пружины растяжения и установленную в выточках, выполненных в запорном элементе и регулировочном винте, причем пружина сжатия выполнена с жесткостью, меньшей жесткости пружины растяжения. 2. Пневмодвигатель по п.1, отличающийся тем, что жесткость пружин сжатия и растяжения удовлетворяет соотношению Сс ж = 0,1 - 0,6 Ср а с т. Ñòðàíèöà: 1 ru CL U 1 U 1 (54) ПОРШНЕВОЙ ПНЕВМОДВИГАТЕЛЬ 1 0 4 2 3 (73) Патентообладатель(и): Омский государственный технический университет R U Адрес для переписки: 644050, Омск, пр.Мира ...

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Номер записи: 1
09-02-2012 дата публикации

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

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

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

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Номер записи: 2
22-03-2012 дата публикации

Wireless sensor for an aircraft propulsion system

Номер: US20120068003A1
Автор: Nicholas Charles Soldner, Peter G. Smith, Sanjay Bajekal, Vijaya Ramaraju Lakamraju
Принадлежит: United Technologies Corp

A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

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Номер записи: 3
19-04-2012 дата публикации

System and Method for Turbine Bucket Tip Shroud Deflection Measurement

Номер: US20120092179A1
Автор: Daniel Howard Tragesser, Joseph Vincent Pawlowski, KrishnaKumar PG, Saurav Dugar
Принадлежит: General Electric Co

A measurement system measures a gap between a plurality of rotating bucket tips and a stationary shroud surface. The system includes a sensor secured to the shroud surface, where the sensor senses a distance between each of the rotating bucket tips and the shroud surface, and a key phasor indexing each of the plurality of rotating bucket tips. A processor receives data from the sensor and the key phasor and calculates a shift against each of the plurality of buckets. The processor determines a time to bucket replacement based on current service hours of the plurality of rotating buckets tips.

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Номер записи: 4
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: 5
10-05-2012 дата публикации

Inter-cylinder air-fuel ratio imbalance judgment device for multi-cylinder internal combustion engine

Номер: US20120116651A1
Автор: Hiroshi Miyamoto, Hiroshi Sawada, Tatsuya Tsuji, Toru Kidokoro, Yasushi Iwazaki
Принадлежит: Toyota Motor Corp

When the intake air amount is smaller than the specific intake air amount, the unit air-fuel ratio change amount calculated during the engine operation is corrected such that the unit air-fuel ratio change amount increases in the condition that the base unit air-fuel ratio change amount is an upper limit and when the intake air amount is greater than the specific intake air amount, the unit air-fuel ratio change amount calculated during the engine operation is corrected such that the unit air-fuel ratio change amount decreases in the condition that the base unit air-fuel ratio change amount is a lower limit. When the corrected unit air-fuel ratio change amount is greater than the judgment value, it is judged that the inter-cylinder air-fuel ratio imbalance condition occurs.

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Номер записи: 6
28-06-2012 дата публикации

System and method for rotary machine online monitoring

Номер: US20120162192A1
Автор: Guanghua Wang, James Peter Delancey, Jeremy Clyde Bailey, Lucy Joelle Summerville, Nirm Velumylum Nirmalan
Принадлежит: General Electric Co

In one embodiment, a system includes an optical monitoring system configured to optically communicate with an interior of a rotary machine. The optical monitoring system is configured to redirect a field of view toward different regions of a component within the interior of the rotary machine while the rotary machine is in operation, and to capture an image of each region.

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Номер записи: 7
30-08-2012 дата публикации

System for measuring parameters of fluid flow in turbomachinery

Номер: US20120216608A1
Автор: Dan M. Hudson, Kurt K. Schleif
Принадлежит: General Electric Co

A system, including, a boundary layer rake, including a rake body, a coolant path extending through the rake body, and a first probe coupled to the rake body, wherein the first probe is configured to measure a first parameter of a first boundary layer flow along a first wall.

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Номер записи: 8
13-12-2012 дата публикации

Inspection device and method for positioning an inspection device

Номер: US20120312103A1
Автор: Harm Speicher, Kai WÖSTMANN, Kerstin Hannott, Margarete Neuhaus
Принадлежит: SIEMENS AG

An inspection device includes a distal area, a proximal area, and a flexible area disposed between the distal area and the proximal area. The flexible area includes a plurality of segments disposed displaceably to each other. At least one external guide element is disposed outside of the flexible area, between the distal area and the proximal area so that the distal area can be displaced with respect to the proximal area via the external guide element.

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Номер записи: 9
21-03-2013 дата публикации

System and method for simulating a gas turbine compressor

Номер: US20130073170A1
Автор: John Benjamin Drohan, Randy Scott Rosson
Принадлежит: General Electric Co

A method for simulating a compressor of a gas turbine is disclosed. The method may generally include determining a predicted pressure ratio and a predicted mass flow of the compressor based on a model of the gas turbine, monitoring an actual pressure ratio and an actual mass flow of the compressor, determining difference values between at least one of the predicted pressure ratio and the actual pressure ratio and the predicted mass flow and the actual mass flow, modifying the difference values using an error correction system to generate a compressor flow modifier and using the compressor flow modifier to adjust the predicted pressure ratio and the predicted mass flow.

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Номер записи: 10
25-04-2013 дата публикации

VALVE MECHANISM FOR AN INTERNAL COMBUSTION ENGINE

Номер: US20130098319A1
Автор: Lawrence Nicholas James, Methley Ian
Принадлежит: MECHADYNE PLC

A valve mechanism is disclosed for a cylinder of an internal combustion engine which comprises two gas exchange poppet valves mounted in a cylinder head, a bridge acting on the two valves, a cam for actuating the two valves, a slider movable by the cam and slidable relative to the bridge and a hydraulically controlled locking system having a latched position in which the slider transmits the force of the cam to the bridge to actuate the two valves and a released position in which the valves are deactivated and the slider slides freely relative to the bridge. In the invention, the slider is urged towards the cam by a spring acting between the slider and the cylinder head. 110121221241221241221012124122124134. A valve mechanism for a cylinder of an internal combustion engine , comprising two gas exchange poppet valves ( ,) mounted in a cylinder head , a bridge () acting on the two valves , a cam for actuating the two valves , a slider () movable by the cam and slidable relative to the bridge () , and a hydraulically controlled locking system having a latched position in which the slider () transmits the force of the cam to the bridge () to actuate the two valves ( ,) and a released position in which the valves are deactivated and the slider () slides freely relative to the bridge () , characterised in that the slider () is urged towards the cam by a spring () acting between the slider and the cylinder head.2. A valve mechanism as claimed in claim 1 , wherein the slider is supported by the cylinder head for movement towards and away from the cam.3. A valve mechanism as claimed in claim 2 , wherein the support in the cylinder head for the slider includes an oil passageway for pressurising the locking mechanism.4. A valve mechanism as claimed in claim 3 , wherein the oil passageway is only open when the slider is aligned with the base circle of the cam.5. A valve mechanism as claimed in claim 1 , wherein clips are provided for securing the bridge to the ends of the ...

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Номер записи: 11
27-06-2013 дата публикации

Airflow Testing Method and System for Multiple Cavity Blades and Vanes

Номер: US20130160535A1
Автор: Edward Pietraszkiewicz, Richard Varsell, Sergey Mironets, Thomas R. DAVIS
Принадлежит: United Technologies Corp

A system for airflow testing a turbine engine component having multiple cavities has a test fixture with a module for supporting a turbine engine component to be tested and a sliding element for sequentially allowing a pressurized fluid to flow through each of the multiple cavities in the turbine engine component. A method for performing the airflow testing is also described.

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Номер записи: 12
25-07-2013 дата публикации

Method of sealing cooling holes

Номер: US20130187307A1
Автор: Michiel Kopmels, Simon CROWTHER
Принадлежит: Rolls Royce PLC

A method of sealing a gap between an aerofoil component ( 30 ) and a further component ( 32 ). The method comprises placing the aerofoil component ( 30 ) in close proximity with the further component ( 32 ) to define a gap ( 38 ) therebetween, applying a thermoplastic material ( 20 ) to the gap ( 38 ) in a molten phase and cooling the thermoplastic material ( 20 ) to set the thermoplastic material ( 20 ).

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Номер записи: 13
01-08-2013 дата публикации

System for detecting an impact on an aircraft engine impeller wheel

Номер: US20130197747A1
Автор: David Tourin, Geoffroy Nicq, Valerio Gerez
Принадлежит: SNECMA SAS

The invention relates to a method and a system for detecting an impact on an impeller wheel ( 7 ) of an aircraft engine, characterised in that it comprises: acquisition means ( 13 ) for acquiring a revolutions per minute of said engine and a series of deflection signals representative of the deflections on the blades of said impeller wheel at said revolutions per minute, and correlation means ( 15 ) for constructing signals for detecting impact on said impeller wheel by correlating each of the deflection signals with a predetermined signature of a shock on a blade at said revolutions per minute.

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Номер записи: 14
12-12-2013 дата публикации

ARRANGEMENT OF A VALVE IN A BORE OF A DUCT HOUSING

Номер: US20130327972A1
Автор: Bornemann Dirk, Quirll Michael
Принадлежит: PIERBURG GMBH

An arrangement of a valve in a bore of a duct housing includes the duct housing comprising the bore with a stepped design. A valve housing with a stepped outer diameter comprises an inlet and at least one outlet, and is plugged into the bore of the duct housing. A translational valve rod is arranged in the valve housing. At least one valve-closure member is arranged on the translational valve rod. The at least one valve-closure member corresponds with at least one valve seat. A bore diameter of the bore decreases when viewed from a plug-in direction of the valve housing. The stepped outer diameter forms an interference fit with the bore diameter in regions radially surrounding the at least one valve seat. Other regions of the stepped outer diameter have an outer diameter which is smaller than the respective radially surrounding bore diameter. 18-. (canceled)9. An arrangement of a valve in a bore of a duct housing , the arrangement comprising:the duct housing comprising the bore with a stepped design;a valve housing with a stepped outer diameter, the valve housing comprising an inlet and at least one outlet, the valve housing being configured to be plugged into the bore of the duct housing;a translational valve rod arranged in the valve housing; andat least one valve-closure member arranged on the translational valve rod, the at least one valve-closure member being configured to correspond with at least one valve seat;wherein,a bore diameter of the bore decreases when viewed from a plug-in direction of the valve housing,the stepped outer diameter of the valve housing is configured to form an interference fit with the bore diameter in regions radially surrounding the at least one valve seat, andother regions of the stepped outer diameter of the valve housing have an outer diameter which is smaller than the respective radially surrounding bore diameter.10. The arrangement as recited in claim 9 , wherein two valve-closure members are arranged on the translational valve ...

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Номер записи: 15
12-12-2013 дата публикации

Cmc blade with pressurized internal cavity for erosion control

Номер: US20130330189A1
Автор: Andres Jose Garcia-Crespo, Jerome Walter Goike
Принадлежит: Individual

A ceramic matrix composite blade for use in a gas turbine engine having an airfoil with leading and trailing edges and pressure and suction side surfaces, a blade shank secured to the lower end of each airfoil, one or more interior fluid cavities within the airfoil having inlet flow passages at the lower end which are in fluid communication with the blade shank, one or more passageways in the blade shank corresponding to each one of the interior fluid cavities and a fluid pump (or compressor) that provides pressurized fluid (nominally cool, dry air) to each one of the interior fluid cavities in each airfoil. The fluid (e.g., air) is sufficient in pressure and volume to maintain a minimum fluid flow to each of the interior fluid cavities in the event of a breach due to foreign object damage.

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Номер записи: 16
09-01-2014 дата публикации

SYSTEM AND METHOD FOR FAULT DIAGNOSIS IN FUEL INJECTION SYSTEM

Номер: US20140012484A1
Автор: Lombardi Frank, Love William J., Prakash Kiran S., Puckett Daniel R., Thomas Aaron L.
Принадлежит: CATERPILLAR INC.

A method for fault diagnosis in a fuel injection system having first and second fuel injectors. The method includes initiating a current flow in the first and second fuel injectors. Further, a rise duration of the current flow to reach a threshold level is measured. The method further includes comparing the rise duration and a preset duration. The fuel injection system is controlled based on the comparison. 1. A method for fault diagnosis in a fuel injection system having first and second fuel injectors , the method comprising:initiating a current flow in the first and second fuel injectors;measuring a rise duration of the current flow from the first and second fuel injectors, to reach a threshold level;comparing the rise duration and a preset duration; andcontrolling the fuel injection system based at least on the comparison.2. The method of claim 1 , wherein the current flow is initiated in the first and second fuel injectors claim 1 , for a preselected time.3. The method of further includes generating a fault signal indicative of a short-circuited fuel injector from the first and second fuel injectors claim 1 , based on the comparison.4. The method of claim 3 , wherein the fault signal is generated when the rise duration is greater than the preset duration.5. The method of claim 3 , wherein the fault signal is generated when the rise duration is greater than the preset duration by more than a tolerance limit.6. The method of claim 1 , wherein controlling the fuel injection system includes opening the first and second fuel injectors claim 1 , in response to the fault signal.7. A control system for fault diagnosis in a fuel injection system having first and second fuel injectors claim 1 , the control system comprising:a first module configured to initiate current flow in the first and second fuel injectors;a second module configured to measure a rise duration of the current flow, from the first and second fuel injectors, to reach a threshold level;a third module ...

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Номер записи: 17
23-01-2014 дата публикации

DYNAMIC MECHANISM TO LIFT THE FLUID TO HIGHEST

Номер: US20140023522A1
Автор: AL-ANEZI Neda
Принадлежит:

A dynamic fluid pump for illustrating fluid dynamics includes a basin of the fluid have a base and a mass of fluid from the basin surface to the base. The dynamic fluid pump is supported at the bottom of the basin. The dynamic fluid pump includes four inner pipes. Two from the inner pipes are upwardly to the fluid tank, one upwardly to the surface of the basin and one act as a vent. The Smallest inner pipe are inside the main inner pipe and the secondary inner pipe smaller diameter than the main inner pipe. Two upwardly inner pipes (main and secondary) each one includes a piston in the bottom of the basin connected together to a pivot assembly in the base of the basin. So that, one of the pistons is at or near the top of one of the inner pipes when the other of the pistons is at or near the bottom of the other inner pipe. 1. A dynamic fluid pump mechanism , the mechanism comprising:a basin of liquid, the basin of liquid having a base and a mass of liquid within the basin and having a liquid surface;a liquid tank located above the basin; a main inner pipe extending upwardly from the base of the basin to the upper end of the basin;', 'secondary and smallest inner pipes extending upwardly from the basin to the liquid tank, the secondary and smallest inner pipes having a smaller diameter than the main inner pipe, the smallest inner pipe having a diameter smaller than the secondary inner pipe and at least a portion of the smallest inner pipe being located within the main inner pipe;', 'a vent inner pipe extending upwardly from the basin and open to atmosphere at an upper end thereof;', 'a first piston located in the main inner pipe;', 'a second piston located in the secondary inner pipe; and', 'a pivot assembly located at the base of the basin and connecting the first and second pistons such that the first and second pistons reciprocate in opposite directions within the respective main or second pipe so that one of the pistons will go down within one of the inner pipes ...

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Номер записи: 18
30-01-2014 дата публикации

METHOD AND SYSTEM FOR MONITORING ROTATING BLADE HEALTH

Номер: US20140030092A1
Автор: Feiner Drew M., Griffin Jerry H., Heinig Roger W.
Принадлежит:

A method and system for establishing sets of blade frequency values for each rotating blade of a rotor assembly at two or more different points in time and determining an indication of blade health from the change in the blade frequency values is provided. Blade frequency values are determined by receiving measurements of vibratory responses from blade monitoring equipment () and processing via a processing device () vibration data as a system of rotating blades to extract a frequency of each blade. Sets of blade frequency values are compared to determine a change in the blade frequency values for each rotating blade to provide the indication of blade health. 1. A method for monitoring a health of rotating blades of a rotor assembly , comprising:establishing sets of blade frequency values for each rotating blade at two or more different points in time, wherein the blade frequency values are determined by processing vibration data as a system of rotating blades to extract a frequency of each blade and applying a function in which the extracted frequency is an independent variable;comparing the sets of blade frequency values to determine a change in the blade frequency values for each rotating blade; anddetermining an indication of blade health from the change in the blade frequency values.2. The method of wherein the system of rotating blades comprises at least one entire row of rotating blades.3. The method of wherein the function comprises a blade frequency ratio.4. The method of wherein the blade frequency ratio comprises a ratio between the extracted frequency of each rotating blade and an average of the extracted frequencies.5. The method of wherein the blade frequency ratio comprises a ratio comprising a difference of the extracted frequency of each rotating blade and an average of the extracted frequencies over the average of the extracted frequencies.6. The method of wherein the blade frequency ratios are calculated from the equation{'br': None, 'sub': k', 'k ...

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Номер записи: 19
20-02-2014 дата публикации

HYDRODYNAMIC COMPONENT

Номер: US20140050565A1
Автор: Ebert Christian, Foehl Bruno, Kibler Jürgen, Laukmann Dieter, Luhrs Thursten, Menne Achim, Schade Ravi, Schlosser Markus
Принадлежит: VOITH PATENT GMBH

The invention relates to a hydrodynamic component comprising at least two elements which form a working chamber therebetween and which comprises a primary wheel and a secondary wheel. A working medium which can be introduced into the working chamber allows torque to be transmitted between said elements. At least one of the elements is arranged in a rotationally fixed manner on a shaft. The hydrodynamic component comprises a device for detecting a variable characterising at least directly the transmitted torque and/or the rotation of the shaft. According to the invention, the shaft is at least designed to have at least two sections which are at an axial distance from each other and which are made of a ferromagnetic material and is provided with a magnetic field which is rotationally stable with the respective section. Magnetic field sensors are arranged in areas corresponding to the at least two sections. 118-. (canceled)19. A hydrodynamic componentcomprising at least two elements which form a working chamber therebetween, which comprises a primary wheel and a secondary wheel, and which via a working medium which can be introduced into the working chamber transmit a torque between said elements,at least one of the elements is arranged in a rotationally fixed manner on a shaft,comprising a device for detecting a variable characterizing at least indirectly the transmitted torque and/or the rotational speed of the shaft,characterized in thatthe shaft at least consists of at least two sections which are at an axial distance from each other and which are made of a ferromagnetic material and are provided with a magnetic field configured to be rotationally fixed with the respective section and thatmagnetic field sensors are arranged in areas corresponding to the at least two sections.201. The hydrodynamic component according to claim , characterized in that at least one of the sections is provided with a permanent magnetic field.211. The hydrodynamic component according to ...

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Номер записи: 20
06-03-2014 дата публикации

Tip clearance probe including anti-rotation feature

Номер: US20140064925A1
Автор: Eli Cole Warren
Принадлежит: Individual

A tip clearance probe includes at least one anti-rotation feature within the probe housing that prevents a sensor component from rotating when the tip clearance probe fails due to extraordinary wear and tear.

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Номер записи: 21
05-01-2017 дата публикации

DETECTION METHOD OF SENSOR IN GAS TURBINE

Номер: US20170002682A1
Автор: LAU Ow, Neuenhahn Thomas, REN Chao, Zheng Jie
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A detection method of a sensor in a gas turbine includes adopting a pressure sensor to measure a pushing force of a push rod; measuring a first rotational angle of a guide vane where a first angle sensor is mounted; measuring a second rotational angle of the guide vane where a second angle sensor is mounted; obtaining a maximum measured rotational angle deviation from the absolute value of a difference value between the first and second rotational angles; calculating a maximum calculated deviation from the pushing force of the push rod; calculating the absolute value of a difference value between the maximum measured deviation and the maximum calculated deviation; and determining that the angle sensors and the pressure sensor have appropriate measurement accuracy; or, if the absolute value is greater than the standard value, determining that the angle and/or pressure sensors require calibration. 1. A method for sensors in a gas turbine , the gas turbine including a cylinder , a plurality of guide vanes , a first angle sensor , a second angle sensor , and a guide vane driving mechanism configured to drive the guide vanes to rotate , the guide vane driving mechanism including a driving ring , a push rod configured to push the driving ring to rotate relative to the cylinder , a pressure sensor configured to measure a thrust of the push rod , a plurality of connecting rods and adjusting rods connecting the guide vanes and the driving ring , and a plurality of elastic support bases connecting the cylinder and the driving ring , the method comprising:measuring thrust of the push rod via the pressure sensor;measuring a first rotation angle of the guide vanes in an installation position of the first angle sensor;measuring a second rotation angle of the guide vanes in an installation position of the second angle sensor;obtaining a measured maximum rotation angle offset according to an absolute value of a difference between said measured first rotation angle and said measured ...

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Номер записи: 22
07-01-2016 дата публикации

VISUAL INDICATOR OF COATING THICKNESS

Номер: US20160003092A1
Автор: Chamberlain Adam Lee, Lazur Andrew Joseph, Lee Kang N.
Принадлежит:

In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer. 1. An article comprising:a substrate; anda coating on the substrate, wherein the coating comprises at least one abradable layer, wherein the at least one abradable layer comprises a matrix material and a plurality of microspheres located within the at least one abradable layer at a predetermined depth from an outer surface of the coating, wherein the plurality of microspheres define a visual characteristic distinct from the matrix material, and wherein the plurality of microspheres comprise at least one rare earth oxide, at least one rare earth silicate, or at least one rare earth oxide and at least one rare earth silicate.2. The article of claim 1 , wherein the coating further comprises an environmental barrier coating layer claim 1 , wherein the environmental barrier coating layer comprises at least one rare earth silicate claim 1 , and wherein the environmental barrier coating layer is between the substrate and the at least one abradable layer.3. The article of claim 1 , wherein the coating further comprises a bond layer between the substrate and the at least one abradable layer claim 1 , wherein the bond layer comprises silicon.4 ...

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Номер записи: 23
01-01-2015 дата публикации

TURBOMACHINE FOR GENERATING POWER HAVING A TEMPERATURE MEASUREMENT DEVICE IN A REGION OF THE ROTOR

Номер: US20150003965A1
Автор: Ahaus Guido, Balkowski Ingo, Flohr Patrick Ronald, Heckel Waldemar, Hoell Harald, Lyko Christian, Ricken Oliver, Sieber Uwe, Stock Sebastian, Veitsman Vyacheslav, Woditschka Frank
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A turbomachine having a rotor is provided, wherein the rotor comprises a central holding element and rotor elements which are arranged thereon, is intended to permit faster start-up without reducing the lifetime of the rotor, while permitting better predictions relating to the remaining lifetime of the rotor. To this end, a contact element is arranged in a region of the rotor between the holding element and the rotor element, wherein the contact element comprises a temperature measurement device. 1. A turbomachine for generating power , comprising:a rotor, wherein the rotor comprises a central retaining element in the form of a tie rod and rotor elements in the form of rotor disks arranged thereon, wherein a contact element is arranged in a region of the rotor between the central retaining element and the rotor element, wherein the contact element comprises a temperature measurement device.2. The turbomachine as claimed in claim 1 , wherein said region of the rotor is the region which is subjected to the highest thermal loads in comparison to other regions.3. The turbomachine as claimed in claim 1 , wherein the contact element is mounted rotatably on an axle claim 1 , wherein the axle is attached to the central retaining element.4. The turbomachine as claimed in claim 1 , wherein the contact element comprises a thermally conductive material on its side facing the rotor element.5. The turbomachine as claimed in claim 1 , wherein the contact element comprises an insulating material on its side facing the central retaining element.6. The turbomachine as claimed in claim 1 , wherein in the region of a bearing assigned to the central retaining element claim 1 , the central retaining element comprises a transmitter connected to the temperature measurement device on a data side of the device claim 1 , wherein said transmitter transmits temperature data.7. The turbomachine as claimed in claim 1 , wherein a plurality of contact elements is arranged symmetrically about the ...

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Номер записи: 24
07-01-2016 дата публикации

COMPACT AERO-THERMO MODEL STABILIZATION WITH COMPRESSIBLE FLOW FUNCTION TRANSFORM

Номер: US20160003164A1
Автор: Karpman Boris, Shishkin Serge L.
Принадлежит:

Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates a current state model as a function of the dynamic states and the model input, wherein a constraint on the current state model is based a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control system and including a series of utilities, the utilities are based on mathematical abstractions of physical properties associated with the component. The series of cycle synthesis modules may include a flow module for mapping a flow curve relating a compressible flow function to a pressure ratio and for defining a solution point located on the flow curve and a base point located off the flow curve. 1100. A control system () , comprising:{'b': 124', '130', '124, 'an actuator () for positioning a control device (), the control device defining a flow path through an aperture, the aperture defining a pressure drop along the flow path, and comprising a control surface, wherein the actuator () positions the control surface in order to regulate fluid flow across the pressure drop based on a model state;'}{'b': 111', '124, 'a control law () for directing the actuator () as a function of a model output; and'}{'b': '110', 'claim-text': [{'b': '220', 'an input object () for processing model input and setting a model operating mode;'}, {'b': 420', '110', '410, 'a set state module () for setting dynamic states of the model processor (), the dynamic states input to an open loop model () based on the model operating mode;'}, {'b': 410', '130, 'wherein the open loop model () generates a current state model as a function of the ...

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Номер записи: 25
04-01-2018 дата публикации

STATOR VANE ARRANGMENT AND A METHOD OF CASTING A STATOR VANE ARRANGMENT

Номер: US20180003066A1
Автор: BEXTON David, GREEN Richard R.
Принадлежит: ROLLS-ROYCE PLC

A stator vane arrangement for a turbomachine comprises a radially inner annular structure, a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the inner annular structure and the outer annular structure. At least one of the vanes has a passage extending from the inner annular structure to the outer annular structure. The inner annular structure has at least one radially inwardly extending boss and each boss has a passage extending there-through. The passage in each boss is aligned with a corresponding passage in a vane. Each boss comprises a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area. The first portion of each boss is positioned between and interconnecting the second portion of the boss and the inner annular structure. 1. A stator vane arrangement comprising a radially inner annular structure , a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the radially inner annular structure and the radially outer annular structure ,at least one of the vanes having a passage extending there-through from the radially inner annular structure to the radially outer annular structure,the radially inner annular structure having at least one boss extending radially inwardly there-from, the at least one boss having a passage extending there-through, the passage in the at least one boss being aligned with the passage in the at least one vane,the at least one boss comprising a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area, the first portion of the boss being positioned between and interconnecting the second portion of the boss and the radially inner annular structure, andthe radially inner annular structure, the radially outer annular ...

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Номер записи: 26
04-01-2018 дата публикации

ROTOR BLADE DAMAGE

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

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

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Номер записи: 27
04-01-2018 дата публикации

TEST RIG FOR A BACK-TO-BACK TEST OF A TURBINE

Номер: US20180003074A1
Автор: Christiansen Morten Grostoel Oernhoej, Jensen Brian Gabe, Malligsen Martin Bebe
Принадлежит:

Test rig for a back-to-back test of a turbine, including an axle supported in at least one bearing fixed to a carrier, a gear coupled to the axle and a motor coupled to the gear, whereby a gear bearing arrangement comprising two radially extending arms to be coupled to the gear and extending in opposite directions, which arms are pivotally connected to a pair of torque arms extending in a basically parallel direction, with the ends of the torque arms being pivotally coupled to a frame including lateral extensions extending in opposite directions with connection segments, to which segments respective second torque arms arranged in a basically vertical direction in respect to the pair of torque arms are pivotally connected, which second torque arms are pivotally connected to a respective connection element arranged at the carrier. 1. A test rig for a back-to-back test of a turbine , comprising an axle supported in at least one bearing fixed to a carrier , a gear coupled to the axle and a motor coupled to the gear , characterized by a gear bearing arrangement comprising two radially extending arms to be coupled to the gear and extending in opposite directions , which arms are pivotally connected to a pair of torque arms extending in a basically parallel direction , with the ends of the torque arms being pivotally coupled to a frame comprising lateral extensions extending in opposite directions with connection segments , to which segments respective second torque arms arranged in a basically vertical direction in respect to the pair of torque arms are pivotally connected , which second torque arms are pivotally connected to a respective connection element arranged at the carrier.2. The test rig according to claim 1 , wherein the first and second torque arms are vertically to each other when the rig is in a non-working condition.3. The test rig according to claim 1 , wherein the arms coupled to the gear are part of a ring-shaped flange-like gear mounting to be fixed to ...

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Номер записи: 28
05-01-2017 дата публикации

Positioning Device for an Optical Triangulation Sensor

Номер: US20170003393A1
Автор: MONKS Tim
Принадлежит: Third Dimension Software Limited

A tool or attachment jig for mounting an optical triangulation sensor on a turbine blade in a position to measure the gap between the distal tip of the turbine blade and the adjacent shroud. The tool includes a device for indicating the orientation of the sensor. This means that the tool can match a measurement from the optical triangulation sensor with a position on the circumference of the shroud. By taking a plurality of measurements as the turbine blade is rotated with respect to the annular casing, an angular profile for the gap between the turbine blade and the casing can be obtained in a much quicker and more efficient way than a conventional system. 1. A positioning device for locating a planar light beam emitted by an optical triangulation sensor across the radial gap between a distal edge of a turbine blade and the inner surface of an annular casing in which the turbine blade is rotatably mounted , the positioning device comprising:an attachment device mounting on the turbine blade;a frame supporting an optical triangulation sensor is a fixed position relative to the attachment device; andan orientation sensing device arranged to detect an orientation with respect to the direction in which gravity acts.2. The positioning device according to claim 1 , wherein the frame is integrally formed with the attachment device.3. The positioning device according to claim 1 , wherein the frame includes one or more engagement arms for orientating the optical triangulation sensor in a manner to enable a measurement of the radial gap between the distal edge of the turbine blade and the inner surface of the annular casing to be taken.4. The positioning device according to claim 1 , wherein the attachment device includes a shaped retention profile adapted to mate with the turbine blade at a fixed radial position thereon.5. The positioning device according to claim 4 , wherein the attachment device comprises a band which loops around the turbine blade.6. The positioning ...

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Номер записи: 29
02-01-2020 дата публикации

PHONIC WHEEL WITH OUTPUT VOLTAGE TUNING

Номер: US20200003074A1
Автор: YAKOBOV Ella
Принадлежит:

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

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Номер записи: 30
02-01-2020 дата публикации

TECHNIQUES FOR MEASURING FUEL INJECTOR FLOW IRREGULARITY WITHOUT REMOVAL FROM VEHICLE

Номер: US20200003144A1
Автор: Faied Louai
Принадлежит:

Diagnostic systems and methods for a fuel system of an engine of a vehicle utilize a fuel rail pressure sensor, an engine speed sensor, an exhaust oxygen (O2) sensor, and a controller configured to perform a diagnostic routine for the fuel system during which fuel injectors of the fuel system do not need to be removed from the engine. The diagnostic routine comprises operating the engine at a set of predetermined operating points and detecting one or more malfunctions of one or more of the fuel injectors based on measured fuel rail pressure, measured engine speed, and measured O2 concentration at each of the set of predetermined operating points. Any fuel injector malfunctions detected during the diagnostic routine could be output to a diagnostic device operated by a human technician, e.g., in a single diagnostic report. 1. A diagnostic system for a fuel system of an engine of a vehicle , the diagnostic system comprising:a fuel rail pressure sensor configured to measure a fuel rail pressure indicative of a pressure of a fuel in a fuel rail of the fuel system, wherein the fuel rail provides the fuel to fuel injectors of the fuel system;an engine speed sensor configured to measure an engine speed indicative of a rotational speed of a crankshaft of the engine;an exhaust oxygen (O2) sensor configured to measure an O2 concentration indicative of an oxygen level of exhaust gas produced by the engine; and operating the engine at a set of predetermined operating points; and', 'detecting one or more malfunctions of one or more of the fuel injectors while the one or more fuel injectors remain installed on the engine based on the measured fuel rail pressure, the measured engine speed, and the measured O2 concentration at each of the set of predetermined operating points., 'a controller configured to perform a diagnostic routine for the fuel system during which the fuel injectors do not need to be removed from the engine, the diagnostic routine comprising2. The system of claim ...

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Номер записи: 31
07-01-2021 дата публикации

APPARATUS AND METHOD FOR TESTING ADDITIVELY MANUFACTURED ENGINE COMPONENTS

Номер: US20210003480A1
Автор: Binek Lawrence, Morganson David W.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A method for inspecting a component made using an additive manufacturing process, the component having an internal conduit, is disclosed. In various embodiments, the method includes the steps of: attaching a fluid-blocking header to the component, the fluid-blocking header having an internal conformal surface configured to mate with an external conformal surface of the component; introducing a plugging media into the internal conduit; activating the fluid-blocking header to freeze the plugging media in a vicinity of the fluid-blocking header; pressurizing the internal conduit of the component; and analyzing a fluid flow characteristic at an outlet of the component to assess an occurrence of a blockage within the internal conduit. 1. A method for inspecting a component made using an additive manufacturing process , the component having an internal conduit , comprising:attaching a fluid-blocking header to the component, the fluid-blocking header having an internal conformal surface configured to mate with an external conformal surface of the component;introducing a plugging media into the internal conduit;activating the fluid-blocking header to freeze the plugging media in a vicinity of the fluid-blocking header;pressurizing the internal conduit of the component; andanalyzing a fluid flow characteristic at an outlet of the component to assess an occurrence of a blockage within the internal conduit.2. The method of claim 1 , wherein the component is an engine casing and the internal conduit includes a fuel rail claim 1 , the fuel rail fluidly coupled to a plurality of fuel injectors.3. The method of claim 2 , wherein the attaching the fluid-blocking header to the component includes attaching a first fluid-blocking header adjacent a first fuel injector.4. The method of claim 3 , wherein the activating the fluid-blocking header to freeze the plugging media in the vicinity of the fluid-blocking header includes running a coolant through the first fluid-blocking header.5. ...

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Номер записи: 32
04-01-2018 дата публикации

In-Situ Measurement Logging by Wireless Communication Unit for Communicating Engine Data

Номер: US20180004197A1
Автор: Dusseau Michael James, Feenstra Keith Richard, Scholten Michael Clay, Sybesma Hilbrand Harlan-Jacob
Принадлежит:

Systems and methods for recording and communicating engine data are provided. One example aspect of the present disclosure is directed to a method for monitoring performance. The method includes receiving, by one or more computing devices, a measurement from a sensor. The method includes assigning, by the one or more computing devices, a time to the measurement. The method includes storing, by the one or more computing devices, the received measurement and the assigned time to a file. The method includes transmitting, by the one or more computing devices, the file to a remove computing device associated with a ground system. 1. A wireless communication unit comprising:one or more memory devices; and receive a measurement from a sensor;', 'assign a time to the measurement;', 'store the received measurement and the assigned time to a file; and', 'transmit the file to a computing device associated with a ground system., 'one or more processors configured to2. The wireless communication unit of claim 1 , wherein the measurement comprises a temperature.3. The wireless communication unit of claim 1 , wherein the measurement comprises an indication of vibration.4. The wireless communication unit of claim 1 , wherein the measurement comprises a humidity.5. The wireless communication unit of claim 1 , wherein the measurement comprises failure data.6. The wireless communication unit of claim 1 , wherein the measurement comprises a current.7. The wireless communication unit of claim 1 , wherein the measurement comprises a voltage.8. The wireless communication unit of claim 1 , wherein the measurement comprises a frequency.9. The wireless communication unit of claim 1 , wherein the one or more processors are further configured to:receive a second measurement from a second sensor;assign the time to the second measurement; andstore the received second measurement and the assigned time to the file.10. The wireless communication unit of claim 1 , wherein the computing device ...

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Номер записи: 33
12-01-2017 дата публикации

Turbo-machine having a thermal transfer line

Номер: US20170009597A1
Автор: Alexander Rambach, Bernhard Fischer, Changsheng Xu, Dennis Bensing, José Ángel Carvajal Soto, Michael Opheys, Pascal Hoffmann
Принадлежит: SIEMENS AG

A turbo-machine having a plurality of component slots accessible from the outside, wherein a thermal transfer line is supplied to at least one section of a component slot such that, upon escape of leakage gas out of the section of the component slot, the leakage gas thermally interacts with the thermal transfer line, wherein the thermal transfer line has a plurality of temperature sensors at different locations on the thermal transfer line and the temperature sensors are designed to detect temperature values on the thermal transfer line at the different locations.

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Номер записи: 34
12-01-2017 дата публикации

CONTROL METHOD OF ELECTRONIC WASTE GATE ACTUATOR

Номер: US20170009692A1
Автор: Kim Deok Ryol, KIM Hyun, KIM Young Min
Принадлежит:

A control method includes an electronic waste gate actuator (EWGA) and a waste gate valve, connected to each other through a rod. The control method includes an operation condition determination step for determining whether an engine is in cold operation or hot operation by measuring engine soak time and initial coolant temperature when the engine starts and by comparing them with a predetermined reference soak time and reference coolant temperature. The control method also includes a cold control step for setting cold operation reference voltage, performing cold operation learning, and applying cold operation learning data to the cold operation reference voltage, when the engine is in cold operation. The control method further includes a hot control step for setting hot operation reference voltage, performing hot operation learning, and applying hot operation learning data to the hot operation reference voltage, when the engine is in hot operation. 1. A method for controlling an electronic waste gate actuator (EWGA) in an electronic waste gate actuator system in which the electronic waste gate actuator is connected to a waste gate valve via a rod , the method comprising:an operation condition determination step for determining whether an engine is in cold operation or in hot operation by measuring an engine soak time and an initial temperature of coolant when the engine starts and by respectively comparing the engine soak time and the initial temperature of the coolant with a predetermined reference soak time and a predetermined reference coolant temperature;a cold control step for setting a cold operation reference voltage, for performing cold operation learning, and for applying cold operation learning data to the cold operation reference voltage, when it is determined at the operation condition determination step that the engine is in cold operation; anda hot control step for setting a hot operation reference voltage, for performing hot operation learning, and ...

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Номер записи: 35
27-01-2022 дата публикации

COOLING HOLE INSPECTION SYSTEM

Номер: US20220025770A1
Автор: Bewlay Bernard Patrick, Dees Jason Edward, Farrell Sean Robert, Knight Bryon Edward, TRIMMER Andrew Lee, Wang Guanghua
Принадлежит:

An inspection system includes a thermographic sensor configured to capture thermographic data of a component having holes as a fluid is pulsed toward the holes, and one or more processors configured to temporally process the thermographic data to calculate temporal scores and spatial scores for the corresponding holes. The scores can be used to obtain a reference dataset and a test dataset. A performance score can be assigned to the component based on the difference between the datasets. 1. A method of performance scoring airflow through a turbine engine component having a first surface and a second surface spaced from the first surface , and a plurality of film holes with inlets formed in the second surface fluidly coupled to outlets formed in the first surface , the method comprising:generating a reference dataset for at least a subset of the plurality of film holes, the reference dataset comprising a reference airflow value indicative of the airflow through the film holes for each of the film holes in the subset of the plurality of film holes, where the reference airflow value is a normalized value;determining a test dataset for a turbine engine component comprising test airflow values for at least some of the film holes in the subset of the plurality of film holes;calculating a difference between the test dataset and the reference dataset; andcalculating a performance score for the turbine engine component based on the difference.2. The method of wherein the normalized value is determined from an aggregate of measured airflow values for multiple turbine engine components.3. The method of wherein the subset of the plurality of film holes comprises all of the plurality of film holes.4. The method of wherein the first surface is an exterior bounding an interior defined by the second surface claim 1 , wherein the interior comprises multiple cooling air circuits and the plurality of film holes comprises different groups of film holes claim 1 , with each grouping ...

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Номер записи: 36
14-01-2016 дата публикации

HOT ENVIRONMENT VANE ANGLE MEASUREMENT

Номер: US20160010491A1
Автор: DiVincenzo Gregory, Singh Bhupindar
Принадлежит:

A turbine is provided and includes an outer duct, a turbine casing formed to define a turbine interior, the turbine casing being disposed within the outer duct to define an annulus, a vane element pivotably coupled to the turbine casing via a spindle to extend spanwise into the turbine interior and a sensor element supportively coupled to the outer duct and configured to sense a characteristic of the spindle within the annulus from which a pivot angle of the vane element is derivable. 1. A turbine , comprising:an outer duct;a turbine casing formed to define a turbine interior, the turbine casing being disposed within the outer duct to define an annulus;a vane element pivotably coupled to the turbine casing via a spindle to extend spanwise into the turbine interior; anda sensor element supportively coupled to the outer duct and configured to sense a characteristic of the spindle within the annulus from which a pivot angle of the vane element is derivable.2. The turbine according to claim 1 , wherein the sensor element is further configured to generate data reflective of the characteristic and the turbine further comprises:a processing unit configured to derive the pivot angle of the vane element from the data; anda communication system by which the processing unit is receptive of the data from the sensor element.3. The turbine according to claim 1 , wherein a magnitude of the pivot angle is derived in accordance with a baseline angle.4. The turbine according to claim 1 , wherein temperatures within the turbine interior exceed temperatures within the annulus by about 1 claim 1 ,000-1 claim 1 ,500° F.5. The turbine according to claim 1 , wherein the sensor element is configured to electro-magnetically claim 1 , optically claim 1 , capacitatively or mechanically sense the characteristic.6. The turbine according to claim 1 , wherein:the sensor element comprises a microwave sensor including a waveguide,the spindle comprises a threaded screw pivotable with the vane element ...

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Номер записи: 37
14-01-2016 дата публикации

SYSTEM AND METHOD OF CONTROL FOR A GAS TURBINE ENGINE

Номер: US20160010493A1
Автор: "ODea Dennis M.", Dhanuka Sulabh K., Huntington Richard A., Minto Karl Dean, Mittricker Franklin F.
Принадлежит:

A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more oxidant passages and one or more fuel passages. The distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is configured to measure a fuel flow rate for a respective fuel passage of the one or more fuel passages of the respective combustor based at least in part on a fuel pressure drop along the respective fuel passage. 1. A system comprising: a plurality of first oxidant passages configured to supply a first oxidant flow to the first combustor;', 'a plurality of first fuel passages configured to supply a first fuel flow to the first combustor;', 'a plurality of first oxidant pressure sensors, wherein each first oxidant pressure sensor of the plurality of first oxidant pressure sensors is fluidly coupled to a respective first oxidant passage of the plurality of first oxidant passages and is configured to transmit a respective first oxidant pressure signal; and', 'a plurality of first fuel pressure sensors, wherein each first fuel pressure sensor of the plurality of first fuel pressure sensors is fluidly coupled to a respective first fuel passage of the plurality of first fuel passages and is configured to transmit a respective first fuel pressure signal; and, 'a first combustor, comprisinga controller coupled to the plurality of first oxidant pressure sensors and to the plurality of first fuel pressure sensors, wherein the controller is configured to determine a first oxidant flow rate through each first oxidant passage of the plurality of first oxidant passages based at least in part on the respective first oxidant pressure ...

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Номер записи: 38
14-01-2016 дата публикации

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

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

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

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Номер записи: 39
14-01-2016 дата публикации

Optical based system and method for monitoring turbine engine blade deflection

Номер: US20160010496A1
Автор: Clifford Hatcher, JR., Raymond S. Nordlund
Принадлежит: Siemens Energy Inc

An optical based system and method for monitoring turbine engine blade deflection during engine operation. An optical camera is coupled the exterior of an engine inspection port, so that its field of view captures images of a rotating turbine blade, such as the blade tip. The camera's image capture or sampling rate matches blade rotation speed at the same rotational position, so that successive temporal images of one or more blades show relative movement of the blade tip within the image field of view. The captured successive images are directed to a blade deflection monitoring system (BDMS) controller. The controller correlates change in a blade's captured image position within the camera field of view between successive temporal images with blade deflection. The BDMS alarms or trips engine operation if the monitored blade deflection falls outside permissible operation parameters.

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Номер записи: 40
14-01-2016 дата публикации

SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES

Номер: US20160010505A1
Автор: Boss Jason Michael, Fuller Fredrick Levi, Geraci Gerald Marco, Moore Lawrence James, Pomykai Michael Richard, Zabek Bernard Baran
Принадлежит:

A method for inspecting a turbomachine is provided. The method includes the steps of, attaching a gimbal mount to the turbomachine, inserting a probe into the turbomachine through the gimbal mount, and adjusting a position of the probe via the gimbal mount. A removing step removes the probe from the turbomachine. An attaching step attaches a traverse actuator system to the gimbal mount. The traverse actuator system is connected to the gimbal mount through a pressure isolation system. A reinserting step is used to reinsert the probe back into the turbomachine. An inspecting step is used to inspect or test the turbomachine. 1. A method for inspecting a turbomachine , the method comprising the steps of:attaching a gimbal mount to the turbomachine;inserting a probe into the turbomachine through the gimbal mount;adjusting a position of the probe via the gimbal mount;removing the probe from the turbomachine;attaching a traverse actuator system to the gimbal mount, the traverse actuator system is connected to the gimbal mount through a pressure isolation system;reinserting the probe back into the turbomachine; andinspecting or testing the turbomachine.2. The method of claim 1 , wherein the gimbal mount further comprises:a plurality of turnbuckles located at equal intervals around the gimbal mount; and wherein the gimbal mount is configured to be mounted to a port or a vessel flange of the turbomachine, and adjustment of the turnbuckles translates into a tangential or axial adjustment of a sensor head position for the probe.3. The method of claim 2 , wherein there are four turnbuckles located at 90 degree intervals around the gimbal mount claim 2 , the adjusting a position of the probe step further comprising:adjusting a first set of turnbuckles spaced by 180 degrees to move the probe in an axial direction with respect to the turbomachine, and adjusting a second set of turnbuckles spaced by 180 degrees to move the probe in a tangential direction with respect to the ...

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Номер записи: 41
14-01-2016 дата публикации

SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES

Номер: US20160010506A1
Автор: Boss Jason Michael, Fuller Fredrick Levi, Geraci Gerald Marco, Moore Lawrence James, Pomykai Michael Richard, Zabek Bernard Baran
Принадлежит:

A system for inspecting a turbomachine is provided. The system includes a pressure isolation system configured to maintain a pressure resistant seal around a probe. The pressure isolation system has a probe bearing located adjacent to a pressure seal. The probe bearing is configured to facilitate back and forth movement of the probe by reducing friction. A gimbal mount is connected to the pressure isolation system. The pressure isolation system has a valve seal located between the gimbal mount and the pressure seal. The valve seal is configured to isolate the pressure seal from the gimbal mount when the probe is not in the valve seal. The system is configured to move the probe into and out of the turbomachine. 1. A system for inspecting a turbomachine , the system comprising:a pressure isolation system configured to maintain a pressure resistant seal around a probe, the pressure isolation system having a probe bearing located adjacent to a pressure seal, the probe bearing configured to facilitate back and forth movement of the probe by reducing friction;a gimbal mount connected to the pressure isolation system; andwherein the pressure isolation system has a valve seal located between the gimbal mount and the pressure seal, the valve seal is configured to isolate the pressure seal from the gimbal mount when the probe is not in the valve seal, and the system is configured to move the probe into and out of the turbomachine.2. The system of claim 1 , wherein the valve seal is at least one of:a ball valve seal or a guillotine seal.3. The system of claim 1 , wherein the probe bearing is comprised of at least one of:roller bearings, ball bearings, or low friction material.4. The system of claim 1 , wherein the pressure seal is connected to a pressurized source or a vacuum source.5. The system of claim 1 , the gimbal mount further comprising:a plurality of turnbuckles located at equal intervals around the gimbal mount; andwherein the gimbal mount is configured to be mounted ...

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Номер записи: 42
11-01-2018 дата публикации

ENGINE PERFORMANCE MODELING BASED ON WASH EVENTS

Номер: US20180010481A1
Автор: Anthony Rob, Dauenhauer David Geoffrey, DiMuro Ronald Matthew, Munnerlyn Will, Pfeiffer Brian William, Schroeder Adam Joseph
Принадлежит:

One example aspect of the present disclosure is directed to a method for measuring engine performance. The method includes receiving a plurality of parameters related to engine performance. The method includes receiving an indication of an engine wash event. The method includes determining an effectiveness of the engine wash event based on the plurality of parameters. The method includes performing a comparison of the effectiveness of the engine wash event with an expected effectiveness of the engine wash event. The method includes performing a control action based on the comparison. 1. A system comprising:one or more memory devices; and receive a plurality of parameters related to engine performance;', 'receive an indication of an engine wash event;', 'determine an effectiveness of the engine wash event based on the plurality of parameters;', 'perform a comparison of the effectiveness of the engine wash event with an expected effectiveness of the engine wash event; and', 'perform a control action based on the comparison., 'one or more processors configured to2. The system of claim 1 , wherein the control action comprises scheduling a new engine wash event based on the comparison.3. The system of claim 1 , wherein the control action comprises scheduling a service based on the comparison.4. The system of claim 1 , wherein the control action comprises scheduling a maintenance action based on the comparison.5. The system of claim 1 , wherein the one or more processors are further configured to:receive a second plurality of parameters related to engine performance;receive an indication of a second engine wash event;determine an effectiveness of the second engine wash event based on the second plurality of parameters; andperform a second comparison, wherein the second comparison is a comparison of the effectiveness of the second engine wash event with an expected effectiveness of the second engine wash event.6. The system of claim 5 , wherein the expected effectiveness ...

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Номер записи: 43
11-01-2018 дата публикации

METHOD FOR DETECTING CONTINUOUS INJECTION DURING THE OPERATION OF AN INTERNAL COMBUSTION ENGINE, INJECTION SYSTEM FOR AN INTERNAL COMBUSTION ENGINE AND INTERNAL COMBUSTION ENGINE

Номер: US20180010542A1
Автор: Dölker Armin
Принадлежит:

A method for detecting continuous injection during the operation of an internal combustion engine with an injection system having a high-pressure accumulator for a fuel, wherein —a high pressure in the injection system is monitored as a function of time, wherein —in order to detect continuous injection it is checked whether the high pressure has dropped by a predetermined continuous injection differential pressure value within a predetermined continuous injection time interval, wherein —it is checked whether a reduction valve which connects the high-pressure accumulator to a fuel reservoir has been triggered, and wherein —continuous injection is detected if —a reduction valve has not been triggered in a predetermined checking time interval before the dropping of the high pressure, and if —the high pressure has dropped by the predetermined continuous injection differential value amount within the predetermined continuous injection time interval. 111-. (canceled)12. A method for detecting continuous injection during operation of an internal combustion engine with an injection system having a high-pressure accumulator for a fuel , the method comprising the steps of:monitoring a high pressure in the injection system as a function of time;detecting continuous injection by checking whether the high pressure has dropped by a predetermined continuous injection differential pressure absolute value within a predetermined continuous injection time interval; andchecking whether a deactivation valve which connects the high-pressure accumulator to a fuel reservoir has been triggered,wherein continuous injection is detected when no deactivation valve has been triggered in a predetermined checking time interval before the dropping of the high pressure, and when the high pressure has dropped by the predetermined continuous injection differential pressure absolute value within the predetermined continuous injection time interval.13. The method according to claim 12 , including ...

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Номер записи: 44
14-01-2021 дата публикации

METHOD FOR SPEED EXCURSION DATA ACQUISITION

Номер: US20210010388A1
Автор: Bowen John S., Bravo Eduardo, Kim Hyun D., Lorenz Frederick B., Struck Bruno E., Taylor Brian J.
Принадлежит: Solar Turbines Incorporated

A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag. 1. A method of monitoring a gas turbine engine , the method comprising:logging a gas producer rotor speed obtained from a sensor and a timestamp associated with the gas producer rotor speed;detecting a start of an overspeed event if the gas producer rotor speed exceeds a trigger threshold;in response to detecting the start of the overspeed event, detecting an end of the overspeed event if the gas producer rotor speed falls below a setpoint threshold;in response to detecting the overspeed event, generating a tag to include an overspeed event value, the gas producer rotor speed, and the timestamp;reading the tag to detect the overspeed event; andin response to detecting the overspeed event, recording a plurality of tags including the overspeed event value, the gas producer rotor speed, the timestamp, from the start of the overspeed event to the end of the overspeed event.2. The method of claim 1 , wherein the method further comprises in response to detecting the end of the overspeed event claim 1 , recording a plurality of tags including the gas producer rotor speed claim 1 , and the timestamp for generally fifteen minutes after the overspeed event.3. The method of claim 2 , wherein the method further comprises temporarily stores a plurality of tags including the gas producer rotor speed claim 2 , and tag timestamp and in response to the start of the overspeed event claim 2 , recording the gas producer rotor speed claim 2 , and the timestamp from generally one minute prior to the start of the overspeed ...

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Номер записи: 45
14-01-2021 дата публикации

SHAFT VIBRATION MONITORING SYSTEM AND ROTARY MACHINE

Номер: US20210010389A1
Автор: Saburi Satoshi
Принадлежит:

A shaft vibration monitoring system is equipped with a plurality of sensors, a sensor abnormality determination unit, and a shaft vibration monitoring unit. The plurality of sensors detect vibration of the rotary shaft. The sensor abnormality determination unit is configured to compare the detection signals to be output from the plurality of sensors and determine whether an abnormality occurs in at least one of the plurality of sensors. The shaft vibration monitoring unit is configured to monitor the vibration of the rotary shaft, on the basis of the detection signals to be output from the plurality of sensors and the determination result of the sensor abnormality determination unit. 1. A shaft vibration monitoring system of a rotary machine equipped with a rotary shaft and a bearing rotatably supporting the rotary shaft around an axis of the rotary shaft , the shaft vibration monitoring system comprising:a plurality of sensors which are configured to detect vibration of the rotary shaft;a sensor abnormality determination unit which is configured to compare detection signals output from the plurality of sensors and determine whether an abnormality occurs in at least one of the plurality of sensors; anda shaft vibration monitoring unit which is configured to monitor vibration of the rotary shaft on the basis of detection signals output from the plurality of sensors and a determination result of the sensor abnormality determination unit.2. The shaft vibration monitoring system according to claim 1 , wherein a shaft vibration abnormality determination unit which is configured to determine whether an abnormal vibration occurs in the rotary shaft on the basis of detection signals output from the plurality of sensors; and', 'a signal correction unit which is configured to correct a detection signal of the sensor determined to abnormal when the sensor abnormality determination unit determines that an abnormality occurs in at least one of the plurality of sensors., 'the ...

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Номер записи: 46
10-01-2019 дата публикации

VALVE DEVICE FOR A TURBOCHARGER

Номер: US20190010864A1
Автор: Hoffmann Maximilian
Принадлежит:

A valve device for an exhaust-gas bypass path of a turbocharger, including: a plate-like valve element, movable between a closed position and an open position and which has a shaft, which is connected to a valve element carrier for limited movement in the shaft direction; a rotatably held spindle, to which the valve element carrier is fixedly connected; a valve seat for the valve element, which valve seat surrounds an exhaust-gas through-opening; and an annular sheet-metal spring element, which has an opening through which the valve element shaft extends, an outer ring region, an inner ring region, which is axially offset relative to the outer ring region and adjoins the spring element opening, and an annular transition region therebetween; the width of the spring element transition region being variable around the spring element opening such that the valve element can be adapted to the valve seat as easily as possible. 1. A valve device for an exhaust-gas bypass path of a turbocharger , said valve device having:a plate-like valve element, which has a sealing surface lying in a plane and a shaft extending away from the sealing surface and is movable between a closed position and an open position;a valve element carrier, to which the valve element is connected by means of its shaft, but is movable to a limited extent relative to the valve element carrier in a direction perpendicular to the valve element sealing surface;a spindle, which is held so as to be rotatable about a spindle longitudinal axis and is fixedly connected to the valve element carrier, such that the valve element is movable between its closed position and its open position by rotation of the spindle;a valve seat surrounding an exhaust-gas through-opening, against which valve seat the valve element sealing surface bears with a sealing pressure in an at least substantially gastight manner in the closed position of the valve element; anda substantially annular spring element produced from a sheet metal ...

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Номер записи: 47
14-01-2016 дата публикации

REAL TIME MONITORING OF GUIDE VANE POSITIONS WITH A CAMERA

Номер: US20160012576A1
Автор: Hatcher, JR. Clifford, Williams James P.
Принадлежит:

An image capturing system includes an imaging device positioned at a location in a stationary portion of a turbo machine, the imaging device having a field of view proximate to one or more vanes of a variable vane stage of the turbo machine and configured to capture an image of the field of view. The system also includes an image analyzer in communication with the imaging device configured to determine an angle of rotation of the one or more vanes of the variable vane stage based on the captured image of the field of view. 1. An image capturing system comprising:an imaging device positioned at a location in a stationary portion of a turbo machine, the imaging device having a field of view proximate to one or more vanes of a variable vane stage of the turbo machine and configured to capture an image of the field of view; andan image analyzer in communication with the imaging device configured to determine an angle of rotation of the one or more vanes of the variable vane stage based on the captured image of the field of view.2. The system of claim 1 , wherein the one or more vanes of the variable vane stage rotate through an angular range from a first angle to a second angle such that a respective portion of the one or more vanes of the variable vane stage is located within the field of view.3. The system of claim 2 , wherein the imaging device comprises:a plurality of cameras, wherein each camera has a respective field of view that together define the field of view of the imaging device, and wherein which of the respective fields of view the respective portion of the one or more vanes is located within depends on the angle of rotation of the one or more vanes of the variable vane stage.4. The system of claim 3 , wherein the one or more vanes comprises one vane.5. The system of claim 3 , wherein the one or more vanes comprises a plurality of vanes and each vane is associated with one of the plurality of cameras.6. The system of claim 3 , wherein the plurality of ...

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Номер записи: 48
15-01-2015 дата публикации

TIP CLEARANCE CONTROL METHOD

Номер: US20150016949A1
Автор: SMITH Marcus Donegan Wood
Принадлежит:

A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run. The method further comprises measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run. The thermal condition of at least part of the engine in accordance with the measured performance parameters is then recorded. Finally the recorded thermal condition is retrieved and the temperature of the casing is controlled during at least part of the second run in a manner dependent on it. 1. A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine , the method comprising the steps:a) performing a first run of the gas turbine engine;b) shutting down the gas turbine engine;c) starting the gas turbine engine for a second run;d) measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run;e) recording the thermal condition of at least part of the engine in accordance with the measured performance parameters;f) retrieving the recorded thermal condition and controlling the temperature of the casing during at least part of the second run in a manner dependent on it2. A method according to where the recorded thermal condition is used in control of the casing temperature to account for residual heat present in relevant parts of the gas turbine engine as a consequence of the first run.3. A ...

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Номер записи: 49
18-01-2018 дата публикации

METHOD AND SYSTEM FOR SOAK-BACK MITIGATION BY ACTIVE COOLING

Номер: US20180016933A1
Автор: Elbibary Mohamed, Laborie Daniel Jean-Louis
Принадлежит:

A method of mitigating soak-back in a gas turbine engine including an engine core compartment and an active engine core compartment cooling system are provided. The active engine core compartment cooling system includes an aperture extending through a core engine cowl forming a radially outer wall of the engine core compartment. The active engine core compartment cooling system also includes a cooling fan mounted within the engine core compartment and including a cooling fan inlet and a cooling fan outlet. The cooling fan inlet is coupled in flow communication with the aperture. The cooling fan outlet is coupled in flow communication with the engine core compartment. The active engine core compartment cooling system further includes a cooling fan controller configured to at least one of control a rotational speed of the cooling fan and control a position of at least one flow control valve coupled in series flow communication with the cooling fan. 1. An active engine core compartment cooling system comprising:an aperture extending through a core engine cowl that forms a radially outer wall of the engine core compartment;a cooling fan mounted within the engine core compartment and comprising a cooling fan inlet and a cooling fan outlet, the cooling fan inlet coupled in flow communication with said aperture, the cooling fan outlet coupled in flow communication with the engine core compartment; anda cooling fan controller configured to at least one of control a rotational speed of said cooling fan and control a position of at least one flow control valve coupled in series flow communication with said cooling fan.2. The system of claim 1 , wherein said aperture extends from the engine core compartment to a bypass duct at least partially surrounding the engine core compartment.3. The system of claim 1 , wherein said cooling fan is electrically powered.4. The system of claim 1 , wherein said gas turbine engine comprises a rotor and a stator claim 1 , said cooling fan ...

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Номер записи: 50
18-01-2018 дата публикации

SENSOR FAULT DETECTION METHOD

Номер: US20180016935A1
Автор: SCOTHERN David P
Принадлежит: ROLLS-ROYCE PLC

A method of determining a faulty sensor of a sensor array of a gas turbine engine (), the sensor array comprising at least first, second and third sensors (A, B, C), the method comprising the steps of: 110. A method of determining a faulty sensor of a sensor array of a gas turbine engine () , the sensor array comprising at least first , second and third sensors (A , B , C) , the method comprising the steps of:{'b': 1', '1', '1', '1', '1', '1', '1', '1', '1, 'sub': A', 'B', 'C', 'A', 'B', 'A', 'C', 'B', 'C, 'a. measuring a first set of sensor outputs (S, S, S) prior to engine startup from each sensor (A, B, C), and calculating a first difference (S-S, S-S, S-S) in the measured value for each sensor pair (A; B, A;C, B;C);'}{'b': 2', '2', '2', '2', '2', '2', '2', '2', '2, 'sub': A', 'B', 'C', 'A', 'B', 'A', 'C', 'B', 'C, 'b. after a period of time, measuring a second set of sensor outputs (S, S, S) prior to engine startup from each sensor (A, B, C), and calculating a second difference (S-S, S-S, S-S) in measured value for each sensor pair (A;B, A;C, B;C);'}{'b': 1', '1', '2', '2', '1', '1', '2', '2', '1', '1', '2', '2, 'sub': A', 'B', 'A', 'B', 'A', 'C', 'A', 'C', 'B', 'C', 'B', 'C, 'c. calculating a further difference ((S-S) -(S-S), (S-S)-(S-S), (S-S)-(S-S)) between the calculated first and second differences for each sensor pair (A;B, A;C, B;C); and'}d. identifying a failed sensor (A, B, C) where two or more sensor pairs (A;B, A;C, B;C) comprising a common sensor (A, B, C) have a further difference above a predetermined threshold.2. A method according to claim 1 , wherein each of the first claim 1 , second and third sensors comprises a strain gauge transducer claim 1 , and may be configured to sense one of temperature and pressure.3. A method according to claim 1 , wherein each of the sensors is a redundant sensor configured to sense the same pressure or temperature when the engine is running.4. A method according to claim 1 , wherein each of the sensors is located ...

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Номер записи: 51
18-01-2018 дата публикации

DEVICE AND METHOD FOR SERVICE-LIFE MONITORING

Номер: US20180016936A1
Автор: Arrieta Hernan Victor, Borufka Hans-Peter, Knodel Eberhard
Принадлежит:

In the case of a device and a method for monitoring the service life of an engine or of a turbine having a compressor blisk and/or a turbine blisk, momentary stresses of blisk substructures, such as the blade (), the disk (), and the join region () between the blade () and the disk (), are calculated on the basis of operating parameters that are measured in the course of engine or turbine operation; and accumulated damage to the individual substructures, that was caused by the momentary stresses, is estimated. 1. A device for monitoring service life of an engine or of a turbine having a blisk , the blisk being a compressor blisk or a turbine blisk , the blisk having blisk substructures including a disk , a blade and a shroud , the blisk being defined as the blade and the disk being formed as one unit , the device comprising:a read-in device for inputting operating parameters measured during the course of engine or turbine operation;a stress calculator for calculating momentary stresses of the blisk substructures on the basis of the measured operating parameters, the blisk substructures for which the momentary stresses are calculated including the shroud and the blade; anda damage estimator for estimating the accumulated damage to the blade and the shroud caused by the momentary stresses.2. The device as recited in wherein the blisk substructures for which the momentary stresses are calculated further include the disk.3. The device as recited in wherein the stress calculator calculates the momentary stresses of at least two of the stress conditions of: creep claim 1 , low-cycle fatigue claim 1 , high-cycle fatigue and hot-gas corrosion.4. The device as recited in wherein the stress calculator further calculates the momentary stresses for thermomechanical fatigue.5. The device as recited in wherein the damage estimator operates as a function of damage tolerances.6. The device as recited in wherein the stress calculator calculates momentary stresses at a join region ...

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Номер записи: 52
18-01-2018 дата публикации

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

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

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

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Номер записи: 53
21-01-2021 дата публикации

FLUTTER SENSING AND CONTROL SYSTEM FOR A GAS TURBINE ENGINE

Номер: US20210017912A1
Автор: Morris Robert J., Rosenkrans William E.
Принадлежит:

A method of operation for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, reducing a rotational speed of a fan relative to a shaft through a gear train, driving the shaft with a low pressure turbine, driving a high pressure compressor with a high pressure turbine, communicating airflow from the fan through a bypass passage defined by a nacelle, the nacelle extending along an engine axis and surrounding the fan, discharging the airflow through a variable area fan nozzle defining a discharge airflow area, detecting an airfoil flutter condition associated with adjacent airfoils of the fan, and moving the variable area fan nozzle to vary the discharge airflow area and mitigate the airfoil flutter condition. 1. A method of operation for a turbofan engine , comprising:reducing a rotational speed of a fan relative to a shaft through a gear train, the fan including a plurality of airfoils;driving a low pressure compressor;driving the shaft with a low pressure turbine, the low pressure turbine including three stages;driving a high pressure compressor with a two-stage high pressure turbine, wherein each of the high pressure and low pressure compressors includes a plurality of stages;communicating airflow from the fan through a bypass passage defined by a nacelle, the nacelle extending along an engine longitudinal centerline axis and surrounding the fan, and having a bypass ratio of greater than 10;discharging the airflow in the bypass passage through a variable area fan nozzle defining a discharge airflow area;detecting an airfoil flutter condition associated with adjacent airfoils of the fan;providing a flutter sensing system including at least one sensor that actively and selectively detects the airfoil flutter condition in operation, and communicates with a controller that causes the variable area fan nozzle to move between a first position and a second position to vary the discharge airflow area, the first ...

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Номер записи: 54
17-04-2014 дата публикации

MEASUREMENT INSTALLATION FOR BLADE FAILURE TESTING IN A TURBOMACHINE

Номер: US20140105727A1
Автор: ADNOT Jean-Francois, Marcellin Patrick, Rousselin Stéphane
Принадлежит: SNECMA

Turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of said turbomachine, said device comprising a hollow cylindrical pipe positioned inside one of the rotating shafts of said turbomachine in order to guide at least one wire for transmitting this information, characterized in that said device further comprises a part for attaching said pipe to said rotating shaft. 1. Turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of said turbomachine , said device comprising a hollow cylindrical pipe positioned inside one of the rotating shafts of said turbomachine in order to guide at least one wire for transmitting this information ,characterized in that said device further comprises a part for attaching said pipe to said rotating shaft.2. Turbomachine according to claim 1 , wherein the attachment part bears a part for guiding the wire towards its ingress into said pipe claim 1 , said guiding part comprising a region claim 1 , for gathering the excess lengths of said wire claim 1 , formed by a wall extending in the axial direction and at least one wall extending in the radial direction.3. Turbomachine according to claim 1 , wherein the disc bearing the fan blades is a disc-ring.44. Turbomachine according to claim 3 , wherein the rotating shaft is a low-pressure shaft () claim 3 , said shaft extending axially in the upstream direction until it is below said disc-ring.5. Turbomachine according to claim 1 , wherein said attachment part attaches to said rotating shaft by axially gripping splines which extend radially inside said shaft.6. Turbomachine according to claim 2 , wherein the guiding part extends axially in the upstream direction until it is in line with one of the axial ends of the fan disc.7. Turbomachine according to claim 6 , wherein the ...

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Номер записи: 55
17-04-2014 дата публикации

METHOD TO IMPROVE THE THERMAL PROPERTIES OF A RESISTANCE ELEMENT EMBEDDED IN AN ALUMINA DEPOSIT ON A SURFACE OF A SUBSTRATE AND APPLICATION OF SAID METHOD

Номер: US20140105741A1
Автор: GISLARD Vanessa Aurelie, Ruelle Melanie Alice Camille
Принадлежит: SNECMA

The invention relates to a method for improving the heat resistance of a resistive element embedded in an alumina deposit covering a surface of a substrate, the alumina deposit comprising a surface portion and a deep portion which is sandwiched between the surface portion and the surface of the substrate and in which the resistive element is located, which method is characterised in that it comprises a densification of the surface portion of the alumina deposit. 1. A method for improving the heat resistance of a resistive element embedded in an alumina deposit covering a surface of a substrate , the alumina deposit comprising a surface portion and a deep portion which is sandwiched between the surface portion and the surface of the substrate and in which the resistive element is located , wherein said method comprises a step of densificating the surface portion of the alumina deposit.2. A method according to claim 1 , wherein said densificating the surface portion of the alumina deposit is achieved by:a) impregnating said surface portion by a solution comprising alumina particles and an aluminium phosphate;b) drying the surface portion so impregnated ; andc) applying a heat treatment to the surface portion so dried.3. A method according to claim 2 , wherein the solution used in step a) is an aqueous solution which comprises 20 to 45% by mass of aluminium phosphate.4. A method according to claim 2 , wherein in that step b) is achieved at ambient temperature for a period of 1 to 4 hours.5. A method according to claim 2 , wherein step c) comprises in succession:{'sub': '1', 'heating the surface portion of the alumina deposit to a temperature Tof between 90 and 100° C. for a period of 1 to 3 hours;'}{'sub': '2', 'heating the surface portion of the alumina deposit to a temperature Tof between 240 and 280° C. for a period of 1 to 3 hours; and'}{'sub': '3', 'heating the surface portion of the alumina deposit to a temperature Tof between 350 and 390° C. for a period of 1 to ...

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Номер записи: 56
28-01-2016 дата публикации

TURBINE OF A TURBOCOMPOUND ENGINE WITH VARIABLE LOAD AND A CONTROLLER THEREOF

Номер: US20160024961A1
Автор: Richards Bryn Geoffrey Roddick
Принадлежит:

A turbine of a turbocompound engine () for extracting energy from the exhaust fluid flow of an and a controller () thereof is described. The turbine () comprises a housing (); a turbine wheel () rotatably coupled within the housing () and rotatable by a fluid flow to provide a rotational output (); a variable load () applying a load to the rotational output; and a controller (). The controller () is configured to: receive information () relating to the operating conditions of the turbine (); calculate an optimum operating velocity () of the rotational output based on the operating conditions; and supply a signal () to the variable load () to vary the load applied to the rotational output () in response to said operating conditions so that the rotational output () rotates at a corrected operating velocity (). Such an arrangement increases the ability to operate the turbine at its optimum operating velocity. 123-. (canceled)24. A turbine for extracting energy from a fluid flow , the turbine comprising:a housing;a turbine wheel rotatably coupled within the housing and rotatable by a fluid flow to provide a rotational output;a variable load applying a load to the rotational output; and receive information relating to the operating conditions of the turbine;', 'calculate an optimum operating velocity of the rotational output based on the operating conditions; and', 'supply a signal to the variable load to vary the load applied to the rotational output in response to said operating conditions so that the rotational output rotates at a corrected operating velocity., 'a controller configured to25. The turbine according to claim 24 , wherein the variable load acts to accelerate the rotational output.26. The turbine according to claim 24 , wherein the variable load acts to brake the rotational output.27. The turbine according to wherein the variable load is applied to the rotational output by an electric machine.28. The turbine according to claim 24 , wherein the controller ...

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Номер записи: 57
26-01-2017 дата публикации

METHOD FOR SHUTTING DOWN AN ELECTRICALLY CONTROLLED COMPONENT OF A VEHICLE IN A CASE OF ERROR OF A PROCESSING UNIT CONTROLLING THE COMPONENT

Номер: US20170022922A1
Автор: HAAG Wolfgang, Huber Jochen
Принадлежит:

A method for shutting down an electrically controlled component of a vehicle in a case of error of a processing unit, the component being controlled by a control circuit, which receives at least one control signal from the processing unit and controls the component as a function of the at least one received control signal, the processing unit outputting the at least one control signal to a control terminal, the processing unit being designed for outputting an error signal having a defined level to the control terminal in a case of error. 1. A method for shutting down an electrically controlled component of a vehicle in a case of error of a processing unit , the component being controlled by a control circuit , which receives at least one control signal from the processing unit and controls the component as a function of the at least one received control signal , the processing unit outputting the at least one control signal to a control terminal , the method comprising:outputting, by the processing unit, an error signal having a defined level to the control terminal in a case of error.2. The method as recited in claim 1 , wherein the at least one control signal is one of: a trigger signal claim 1 , an analog signal claim 1 , a data signal.3. The method as recited in claim 1 , wherein the processing unit outputs the error signal as a signal having a HIGH level to the control terminal in a case of error.4. The method as recited in claim 1 , wherein for purposes of control claim 1 , the control circuit connects the component to an energy source.5. The method as recited in claim 4 , wherein the component is connected by the control circuit directly to an energy source via internal output stages.6. The method as recited in claim 1 , further comprising:checking proper functioning of the shutdown by outputting, on the control terminal, a test signal having a LOW level, subsequently outputting the error signal as a signal having a HIGH level, and checking a resulting total ...

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Номер записи: 58
28-01-2016 дата публикации

Method and systems for detection compressor surge

Номер: US20160025596A1
Автор: Carlo Angelo Yon, Christopher Childs, Matthew John Mckeever, Robert Joseph Iasillo, Sanjeev Shyam Heda, Scott Alan Wood, Steven William Backman
Принадлежит: General Electric Co

A system for remote detection of surge in a fleet of turbine engines includes an on-site monitoring device coupled to each turbine engine of the fleet of turbine engines. The on-site monitoring device is configured to continuously receive operating parameter measurements indicative of operational and thermodynamic conditions of the turbine engine. The operational condition includes a compressor exit condition of the turbine engine compressor. The on-site monitoring device is configured to compile and transmit a snapshot of the operating parameter measurements to a remote monitoring unit. The remote monitoring unit is positioned remote from each turbine engine of the fleet of turbine engines. The remote monitoring unit is configured to receive the snapshot of operating parameter measurements from the on-site monitoring device. The remote monitoring unit is further configured to detect surge in the turbine engine based on analysis of the snapshot of operating parameter measurements.

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Номер записи: 59
25-01-2018 дата публикации

OIL DEBRIS MONITORING FOR FAILURE DETECTION ISOLATION

Номер: US20180023414A1
Автор: Erdinc Ozgur, Giering Michael J., Hagen Gregory S., Harris Meggan, Khibnik Alexander I., Lin Yiqing
Принадлежит:

A method of detecting debris within a lubricant stream, the method includes generating data indicative of debris and sensor system functionality within a lubricant stream with a sensor system. The data is communicated to a controller. Features calculated from the data are indicative of a debris within the lubricant stream. The calculated features are compiled over time during operation. The compiled features are classified. An oil debris monitoring system for a turbine engine is also disclosed. 1. A method of detecting debris within a lubricant stream , the method comprising:generating data indicative of debris and sensor system functionality within a lubricant stream with a sensor system;communicating the data to a controller;calculating features from the data that are indicative of a debris within the lubricant stream;compiling the calculated features over time during operation; andclassifying the compiled features.2. The method as recited in claim 1 , wherein classifying the compiled features includes determining an occurrence rate for the features.3. The method as recited in claim 2 , including comparing the determined occurrence rate with an expected range claim 2 , and identifying an engine operational characteristic responsive to the comparison with the expected range.4. The method as recited in claim 1 , wherein the features comprise a plurality of features of the lubricant stream that are detected and identified concurrently.5. The method as recited in claim 1 , wherein the features comprise at least one of a time-rate of generation and an overall accumulated number of occurrences.6. The method as recited in claim 5 , wherein a time-rate of generation that corresponds with a desired operation of a turbine engine is compared to the determined time-rate of generation to identify an engine operational characteristic.7. The method as recited in claim 1 , wherein compiling the features is performed during operation of a turbine engine for analysis during a non- ...

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Номер записи: 60
24-01-2019 дата публикации

WEAR INDICATION SENSOR DESIGNS AND METHODS OF INTEGRATION

Номер: US20190024532A1
Автор: Caldwell Dustin D., Dardona Sameh, Kasprow Thomas D., Sheedy Paul
Принадлежит:

In combination a wear indication sensor and a component of a gas turbine engine is provided. The wear indication sensor is secured to a first surface of the component of the gas turbine engine. The wear indication sensor comprises: a first terminal; a second terminal electrically connected to the first terminal; two or more of resistors electrically connecting the first terminal to the second terminal, each of the two or more resistors including a first end electrically connected to the first terminal and a second end electrically connected to the second terminal, wherein each of the two or more resistors has a known resistance; and a first electrode electrically connecting the first terminal to the first end of each of the two or more resistors; wherein the first end of each of the two or more resistors is electrically connected to the first electrode through primary conductive lines. 1. In combination a wear indication sensor and a component of a gas turbine engine , wherein the wear indication sensor is secured to a first surface of the component of the gas turbine engine , the wear indication sensor comprising:a first terminal;a second terminal electrically connected to the first terminal;two or more of resistors electrically connecting the first terminal to the second terminal, each of the two or more resistors including a first end electrically connected to the first terminal and a second end electrically connected to the second terminal, wherein each of the two or more resistors has a known resistance; anda first electrode electrically connecting the first terminal to the first end of each of the two or more resistors;wherein the first end of each of the two or more resistors is electrically connected to the first electrode through primary conductive lines.2. The combination of the wear indication sensor and the component of the gas turbine engine of claim 1 , wherein the two or more resistors are electrically connected in parallel with each other.3. The ...

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Номер записи: 61
24-04-2014 дата публикации

METHOD FOR MONITORING A PASSIVE PRESSURE REGULATION VALVE

Номер: US20140109876A1
Автор: Dölker Armin
Принадлежит: MTU Friedrichshafen GmbH

Proposed is a method for monitoring a passive pressure limiting valve () via which fuel is discharged from the rail () of a common rail system into the fuel tank (), in which method, upon the detection of a defective rail pressure sensor (), a switch is made from a rail pressure regulation mode into an emergency mode, wherein in the emergency mode, the rail pressure is successively increased until the pressure limiting valve () reacts, in which method, in the emergency mode, the pressure limiting valve () is set as open when the starting phase of the internal combustion engine has additionally been detected as having ended, and in which method, in addition, the opening duration of the pressure limiting valve () is monitored. 1. Method for monitoring a passive pressure limiting valve via which fuel is discharged from the rail of a common rail system into the fuel tank , wherein upon the detection of a defective rail pressure sensor , a switch is made from a rail pressure regulation mode into an emergency mode , wherein in the emergency mode , the rail pressure is gradually increased until the pressure limiting valve responds , wherein the pressure limiting valve is set as open in the emergency mode if the starting phase of the combustion is also detected as having ended , and wherein the opening duration of the pressure limiting valve is additionally monitored.2. Method according to claim 1 , wherein the opening duration is monitored in that upon setting an open pressure limiting valve claim 1 , a first time limit and a second time limit are defined for further operation claim 1 , a yellow alarm is triggered upon reaching the first the time limit to warn the operator and a red alarm is triggered upon reaching the second time limit as a recommendation that the pressure limiting valve should be replaced.3. Method according towhereinthe current opening duration is saved when the combustion engine is switched off and said duration continues to be recorded when the ...

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Номер записи: 62
24-01-2019 дата публикации

TWISTING TORQUE SENSOR

Номер: US20190025142A1
Автор: Renault Lionel
Принадлежит: SAFRAN HELICOPTER ENGINES

The invention relates to a twisting torque sensor, comprising a transmission shaft () subjected to the torque to be measured, a reference shaft (), and a device for measuring an angular deformation representing the torque to be measured between the two shafts. The torque sensor is characterised in that the transmission shaft () comprises a bore () extending from one end of the transmission shaft (), referred to as input () of the shaft, to an opposite end, and in that the torque sensor comprises an enclosure () for confining the temperature of the two shafts, and a fluid circulation circuit including a portion made up of said bore (), an injector () for injecting the fluid into the bore () at said input () of the shaft, and a fluid temperature sensor () in the fluid circulation circuit, the measured temperature being intended for correcting the torque measurement. 1. Twisting-torque sensor , comprising a first shaft , referred to as the transmission shaft , subjected to the torque to be measured , a second shaft , referred to as the reference shaft , and a device for measuring an angular deformation between the transmission shaft and the reference shaft , said angular deformation representing the torque to be measured , a temperature-confinement enclosure of the first and second shafts, and', a portion constituted by said bore of the transmission shaft,', 'a fluid injector into the bore at said input of the shaft, and', 'a temperature sensor, referred to as the main temperature sensor, suitable for measuring the temperature of the fluid in the fluid-circulation circuit, the measured temperature of the fluid being intended for a correction of the torque measurement., 'a fluid-circulation circuit, comprising], 'wherein the transmission shaft comprises a bore-P forming an internal wall and extending from one end of the transmission shaft, referred to as the input of the shaft, to an opposite end, referred to as the output of the shaft, and in that the torque sensor ...

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Номер записи: 63
23-01-2020 дата публикации

Continuous gap measurement

Номер: US20200025549A1
Автор: Joel A. Johnson, Ronald J. Heaps
Принадлежит: US Department of Energy

A gap measurement device. The device has a circuit having a variable inductor and a capacitor. The variable inductor has an indicator. The device has a gap that includes a gap measurement and a gap length. The gap measurement is related to the inductance. The gap is configured to receive at least a portion of the variable inductor while the variable inductor moves along the gap length. The movement of the variable inductor along the gap length causes the inductance to change in response to the gap measurement.

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Номер записи: 64
28-01-2021 дата публикации

SHAFT SHEAR DETECTION IN A GAS TURBINE ENGINE

Номер: US20210025287A1
Автор: AHMAD Zubair, ROACH Andrew
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 comprising a first spool and a second spool different from the first spool. A first parameter indicative of one of power of the first spool and a load transfer through a shaft of the second spool is obtained and a second parameter indicative of the other one of power of the first spool and the load transfer through the shaft of the second spool is obtained. A detection threshold is determined as a function of the first parameter. The second parameter is compared to the detection threshold. The shaft event is detected when the second parameter is beyond the detection threshold and then a signal indicative of the shaft event is transmitted. 1. A method for detecting a shaft event in a gas turbine engine comprising a first spool and a second spool different from the first spool , the method comprising:obtaining a first parameter indicative of one of power of the first spool and a load transfer through a shaft of the second spool, and obtaining a second parameter indicative of the other one of power of the first spool and the load transfer through the shaft of the second spool;determining a detection threshold as a function of the first parameter;comparing the second parameter to the detection threshold; anddetecting the shaft event when the second parameter is beyond the detection threshold and then transmitting a signal indicative of the shaft event.2. The method of claim 1 , wherein the parameter indicative of power is one of: a discharge pressure of a compressor of the engine claim 1 , a fuel flow to a combustor of the engine and a core airflow through the first spool.3. 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 first parameter and the second parameter comprises measuring the load transfer ...

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Номер записи: 65
29-01-2015 дата публикации

METHOD AND APPARATUS FOR MEASURING TURBINE SHELL CLEARANCE

Номер: US20150030433A1
Автор: JR. Fred Thomas, Willett
Принадлежит:

An apparatus for measuring turbine rotor-to-stator clearances and a method for assembling a turbomachine based on the measured clearances are disclosed. In an embodiment, at least one clearance sensor is inserted into a stator of a turbomachine. Using the sensor, tops-on clearance between a rotor blade tip and an inner surface of a stator is measured while an upper stator shell, a rotor, a lower stator shell are assembled together; and a tops-off clearance is measured while the lower stator shell and a rotor are assembled together. A tops-on/tops-off shift, i.e., a difference between the tops-on clearance and the tops-off clearance, is determined. The turbine can be assembled by adjusting a relative position of the rotor and stator to account for the tops-on/tops-off shift. 1. An apparatus comprising:at least one sensor inserted in a stator, the at least one sensor being configured to measure:a tops-on clearance between a rotor blade tip and an inner surface of a stator, wherein in the tops-on condition, the clearance is measured while an upper stator shell and a lower stator shell are assembled together, and a rotor is installed within the assembled stator, anda tops-off clearance between the rotor blade tip and the inner surface of the stator while the lower stator shell and the rotor are assembled together, and the upper stator shell is not affixed to the lower stator shell; anda computing device operably connected with the at least one sensor, the computing device being configured to determine a tops-on/tops-off shift, wherein the tops-on/tops-off shift is equal to a difference between the tops-on clearance and the tops-off clearance.2. The apparatus of claim 1 , wherein the at least one sensor further comprises between about 3 and about 6 sensors axially spaced along the stator.3. The apparatus of claim 1 , wherein the at least one sensor further comprises a plurality of sensors spaced such that one sensor is axially aligned with each of a plurality of stages ...

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Номер записи: 66
23-01-2020 дата публикации

Using scanned vanes to determine effective flow areas

Номер: US20200026821A1
Автор: Bradley W. Burkett
Принадлежит: Rolls Royce Engine Services Oakland Inc

A computing device for determining effective flow areas of a turbine or turbine engine includes optically scanning and digital modeling of turbine components to produce virtual vanes, virtual vane segments, and virtual ring assemblies. The computing device determines both individual effective flow areas between vanes and the total effective flow area of a vane ring assembly. Based on the virtual vanes and determined effective flow areas, the computing device may compare one or more turbine components to a reference turbine to determine whether the turbine is out of specification and aid in repair, modification, or reassembly of the turbine or turbine engine.

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Номер записи: 67
02-02-2017 дата публикации

MAGNETIC SENSOR SYSTEM FOR DETECTING ABNORMAL MOVEMENT IN A GAS TURBINE SHAFT

Номер: US20170030215A1
Автор: Kulczyk Wojciech Konrad
Принадлежит:

The present invention relates to a system () for detecting abnormal movement of a gas turbine shaft. The system comprises: a magnetic circuit () comprising a first magnetic portion () and a second portion (), and including at least one air gap between the first portion and the second portion; and a detection coil () wound around the first magnetic portion. The second portion is coupled to or moveable with the shaft to reduce the air gap, on axial movement of the shaft to change the reluctance of the magnetic circuit and thereby induce a voltage in the coil. The system may comprise a controller () for shutting off power to the gas turbine when the induced voltage exceeds a threshold voltage. 1. A system for detecting breakage of a gas turbine shaft comprising:a magnetic circuit, forming one or more closed loop paths containing a magnetic flux, comprising a first magnetic portion and a second portion, and including at least one air gap between the first portion and the second portion; and,a detection coil wound around the first magnetic portion;wherein, the second portion is coupled to or moveable with the shaft to reduce the air gap, on axial movement of the shaft, to change the reluctance of the magnetic circuit and thereby induce a voltage in the coil.2. A system according to claim 1 , wherein the first magnetic portion comprises a permanent magnet.3. A system according to claim 1 , wherein the first magnetic portion comprises an electromagnet.4. A system according to claim 3 , wherein the first magnetic portion comprises a further coil wound around a soft magnetic material to form the electromagnet.5. A system according to claim 4 , wherein a constant current is applied to the further coil.6. A system according to wherein an alternating current is applied to the further coil.7. A system according to claim 3 , wherein a constant current is applied to the detection coil to power the electromagnet.8. A system according to claim 1 , wherein the first magnetic portion ...

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Номер записи: 68
02-02-2017 дата публикации

DYNAMIC SYSTEM ESTIMATION DEVICE AND METHOD

Номер: US20170030216A1
Автор: FURUKAWA Hiroyuki, KAKIUCHI Daiki, KIMURA Mai
Принадлежит: IHI CORPORATION

A dynamic system estimation device and method, whereby estimation for more performance parameters than there are sensors can be performed, the estimation taking temporal changes into account. The dynamic system estimation device includes: a prescribed number of sensors that detect prescribed observation values from a gas turbine engine; and a Kalman filter that uses a dynamic model of the gas turbine engine and estimates the state of the gas turbine engine, on the basis of the observation values detected by the sensors. The gas turbine engine includes an element having changes in temporal performance recorded by performance parameters. The Kalman filter enables more than the prescribed number of performance parameters to be estimated, as a result of introducing a first-order lag element in place of the element. 1. A dynamic system estimation device that estimates a state and performance parameters of a dynamic system , comprising:a predetermined number of sensors which detect predetermined observed values from the dynamic system; anda Kalman filter that estimates the state of the dynamic system by using a dynamic model of the dynamic system based on the observed values detected by the sensors,wherein the dynamic system includes elements in which temporal changes of performance are described by the performance parameters, and the Kalman filter also enables estimation of performance parameters, of which number is larger than the predetermined number, by introducing first-order lag elements in place of the elements.2. The estimation device according to claim 1 , wherein each of the performance parameters is given as a ratio of an output value of the first-order lag element to an input value of the first-order lag element.3. The estimation device according to claim 1 , wherein the dynamic system is a gas turbine engine claim 1 , and the observed values detected by the sensors include a number of revolutions claim 1 , a temperature and a pressure in the gas turbine ...

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Номер записи: 69
02-02-2017 дата публикации

Use of ss data trends in fault resolution process

Номер: US20170030217A1
Автор: Amy Rose Grace, Andrew D. Ruestow, Anya R. Brunschwig, Bryan P. Donovan, Charles Pelosi, Gregory J. Kacprzynski
Принадлежит: United Technologies Corp

An automated method for resolving fault in an engine is disclosed. The method may include providing a reasoner module for recommending a set of maintenance actions to resolve fault in the engine, inputting steady state performance data from the engine into the reasoner module, and using the reasoner module to recommend a set of maintenance actions based at least in part on the steady state performance data. A fault resolution system for a gas turbine engine is also disclosed. The fault resolution system may include at least one computer processor operatively configured to receive steady state performance data from the gas turbine engine, and recommend a set of maintenance actions to resolve fault in the gas turbine engine based at least in part on the steady state performance data.

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Номер записи: 70
04-02-2016 дата публикации

TURBOFAN AIRCRAFT ENGINE

Номер: US20160032826A1
Автор: Feldmann Manfred, Gier Jochen, Hackenberg Hans-Peter, Heinrich Eckart, Huebner Norbert, Humhauser Werner, Klingels Hermann, Maar Karl, RIEGLER Claus, RUED Klaus Peter, Stanka Rudolf, Steinhardt Erich, Weber Stefan
Принадлежит:

A turbofan aircraft engine has at least one stage pressure ratio is at least 1.5, and a quotient of the total blade count divided by 110 is less than a difference ([(p/p)−1]) of the total pressure ratio minus one, and the total pressure ratio is greater than 4.5, and the turbine has at least two and no more than five turbine stages; and/or a product (An) of an exit area (A) of the second turbine and a square of a rotational speed of the second turbine at the design point is at least 4.5·10[in·rpm], and a blade tip velocity (u) of at least one turbine stage of the second turbine at the design point is at least 400 meters per second. A jet and method are also provided. 1. A turbofan aircraft engine comprising:a primary duct including a combustion chamber, a first turbine disposed downstream of the combustion chamber, a compressor disposed upstream of the combustion chamber and coupled to the first turbine, and a second turbine having a plurality of turbine stages having rotor blades and disposed downstream of the first turbine and coupled via a speed reduction mechanism to a fan for feeding a secondary duct of the turbofan aircraft engine;{'sub': St', 'BV', '1', '2, 'the second turbine having a total stage count (n) of all turbine stages of the second turbine, a total blade count (N) of all rotor blades and stator vanes of all turbine stages of the second turbine, a stage pressure ratio (Π) of the pressure at the inlet to the pressure at the outlet at each turbine stage, and a total pressure ratio (p/p) of the pressure at the inlet of a first turbine stage to the pressure at the exit of a last turbine stage of the second turbine at a design point,'}{'sub': BV', '1', '2, 'a quotient (N/110) of the total blade count divided by 110 being less than a difference ([(p/p)−1]) of the total pressure ratio minus one, with the total pressure ratio being greater than 4.5; and'}at least one stage pressure ratio is at least 1.5; andthe second turbine having at least two and no more ...

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Номер записи: 71
04-02-2016 дата публикации

FUEL SYSTEM DIAGNOSTICS

Номер: US20160032853A1
Автор: Huang Jian, Munshi Sandeep
Принадлежит:

A method and apparatus for in situ operating an internal combustion engine comprising determining at least one combustion characteristic for a combustion chamber of the internal combustion engine, comprising an actual heat release signal for the combustion chamber; and inputting the actual heat release signal into a diagnostic logic tree for diagnosing changes in combustion characteristics due to at least one of: a malfunctioning fuel injector, a start of combustion timing error; and a change in fuel quality; and performing a mitigation technique to compensate for the changes in combustion characteristics. 1. A method for in situ operating an internal combustion engine comprising:determining at least one combustion characteristic for a combustion chamber of said internal combustion engine, comprising an actual heat release signal for said combustion chamber; and a malfunctioning fuel injector associated with said combustion chamber,', 'a start of combustion timing error; and', 'a change in fuel quality; and, 'inputting said actual heat release signal into a diagnostic logic tree for diagnosing changes in combustion characteristics due to at least one ofperforming a mitigation technique to compensate for said changes in combustion characteristics.2. The method of claim 1 , further comprising:determining a desired heat release signal as a function of engine operating conditions;comparing a difference between said actual heat release signal and said desired heat release signal with a predetermined tolerance; anddiagnosing said fuel injector is malfunctioning when said difference is outside a range of said predetermined tolerance.3. The method of claim 2 , further comprising diagnosing that said malfunctioning fuel injector is: (a) introducing too much fuel when said difference is greater than a positive value of said predetermined tolerance; and claim 2 , (b) introducing too little fuel when said difference is less than a negative value of said predetermined tolerance. ...

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Номер записи: 72
31-01-2019 дата публикации

MONITORING SYSTEM FOR A GAS TURBINE ENGINE

Номер: US20190032508A1
Автор: Dees Jason Edward, Osgood Daniel Endecott, Ruggiero Eric John, Stewart William, Wang Guanghua
Принадлежит:

An optical monitoring system includes a controller configured to determine a predicted status of a component based on an operational time of a rotary machine and an individual model. The controller is also configured to receive a first signal indicative of an infrared spectrum image of the component from one or more cameras. Further, the controller is configured to determine a current status of the component based on the first signal and compare the current status to the predicted status of the component. Additionally, the controller is configured to update the predicted status of the component such that the predicted status matches the current status of the component and update at least one parameter of the individual model of the component based on the comparison. 1. An optical monitoring system comprising a controller configured to:determine a predicted status of a component within an interior of a rotary machine based at least in part on an operational time of the rotary machine and an individual model of the component;receive a first signal indicative of an infrared spectrum image of the component from one or more cameras;determine a current status of the component based at least in part on the first signal;compare the current status to the predicted status of the component; andupdate the predicted status of the component such that the predicted status matches the current status of the component and update at least one parameter of the individual model of the component based at least in part on the comparison.2. The optical monitoring system of claim 1 , wherein the predicted status of the component comprises a predicted amount of spallation of a thermal barrier coating of the component claim 1 , a predicted amount of spallation of an environmental barrier coating of the component claim 1 , a predicted number of blocked cooling holes of the component claim 1 , a predicted amount of oxidation of the component claim 1 , a predicted amount of corrosion of the ...

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Номер записи: 73
31-01-2019 дата публикации

DETERMINATION OF A FUEL DELIVERY FAULT IN A GAS TURBINE ENGINE

Номер: US20190032509A1
Автор: King Stephen P., MULDAL Carl L., RIMELL Andrew
Принадлежит: ROLLS-ROYCE PLC

A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured fuel delivery flow number of the combustor fuel system against a predicted fuel delivery flow number of the combustor fuel system. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured fuel delivery flow number differ from their predicted values by more than respective predetermined thresholds. 1. A method of determining a fuel delivery fault in a gas turbine engine having a combustor , a combustor fuel system for delivering fuel to the combustor , and a turbine which is driven by hot gas from the combustor , the method including:comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile;comparing a measured fuel delivery flow number of the combustor fuel system against a predicted fuel delivery flow number of the combustor fuel system; andindicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured fuel delivery flow number differ from their predicted values by more than respective predetermined thresholds.2. A method according to claim 1 , wherein the indication that a fuel delivery fault has been detected includes identifying the probable location of the fuel delivery fault.3. A method according to claim 1 , wherein the combustor fuel system has a manifold which delivers a fuel flow to fuel injectors of the combustor claim 1 , and the comparison of flow numbers includes comparing a measured ...

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Номер записи: 74
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: 75
31-01-2019 дата публикации

OPTICAL MEASUREMENT DEVICE, OPTICAL MEASUREMENT METHOD, AND ROTATING MACHINE

Номер: US20190033061A1
Автор: KONDOU Akio, MIYAMOTO Takahiro, ONISHI Tomoyuki
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

There is provided: a pair of slanted fiber groups; a pair of parallel fiber groups; a light source for emitting two slanted light beams from a pair of slanted light-emitting fibers, and emitting two parallel light beams from a pair of parallel light-emitting fibers; a target provided to the outer peripheral surface of a rotor; a pair of light-receiving elements for detecting the intensity of light received by each of a pair of slanted light-receiving fibers; a pair of light-receiving elements for detecting the intensity of light received by each of a pair of parallel light-receiving fibers; and a computation unit for performing a computation that includes an interval affected by thermal elongation on the basis of four waveforms indicating changes in the intensity detected by each of the light-receiving elements. 1. An optical measurement device comprising:a pair of first fiber bundles having a pair of first light-emitting fibers, distal ends of which are arranged at a specified interval and a pair of first light-receiving fibers, distal ends of which are arranged at the specified interval, in a light sensor, the pair of first fiber bundles being arranged to be slanted to respectively form two sides of a triangle in triangulation;a pair of second fiber bundles having a pair of second light-emitting fibers, distal ends of which are arranged at the specified interval, and a pair of second light-receiving fibers, distal ends of which are arranged at the specified interval, in the light sensor, the pair of second fiber bundles being arranged in parallel with each other;a light source that outputs light to the pair of first light-emitting fibers and the pair of second light-emitting fibers to emit two slanted light beams from the pair of first light-emitting fibers and emit two parallel light beams from the pair of second light-emitting fibers, whereina target of the light emitted from the first light-emitting fibers and the second light-emitting fiber is provided on an ...

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Номер записи: 76
04-02-2021 дата публикации

ELECTRONIC STEAM TRAP

Номер: US20210033245A1
Автор: WINGERATH Christian Matthias
Принадлежит:

A self-contained electronic steam trap drains condensate from a steam system. The steam trap includes a drain pipe adapted for fluid communication with a steam supply system. Pressure and temperature sensors measure pressure and temperature in an internal passageway of the steam trap. A condensate discharge valve is disposed at or upstream of an output port of the drain pipe. The condensate discharge valve is controlled based on the measured pressure and temperature and a calculated steam saturation temperature. Both a cycling mode and a regulation mode of automatic valve operation are described. 1. An automated electronic steam trap comprising:a steam trap having an internal passageway connected between an inlet port configured to receive steam/condensate and an outlet port configured to discharge condensate collected by the steam trap;a condensate discharge valve disposed at or upstream of the outlet port for venting condensate from the steam trap when actuated to an open position;pressure and temperature sensors disposed to monitor pressure and temperature conditions in the internal passageway upstream of the condensate discharge valve; andan electronic control processing circuit configured to automatically actuate said valve in response to inputs from the pressure and temperature sensors.4. The automated electronic steam trap of further comprising:a wireless communication circuit configured to wirelessly transmit data indicating valve position to a remote location.5. The automated electronic steam trap of claim 1 , wherein said valve comprises a valve operation mechanism driven by a rotatably moving electrical motor.6. The automated electronic steam trap of claim 1 , wherein said valve comprises a valve operation mechanism driven by a linearly moving electrical motor.7. The automated electronic steam trap of claim 1 , wherein said valve comprises a valve operation mechanism driven by an electrically actuated pneumatically or hydraulically powered movement ...

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Номер записи: 77
12-02-2015 дата публикации

Borescope assembly and method of installing borescope plugs

Номер: US20150040581A1
Автор: Kenneth Damon Black
Принадлежит: General Electric Co

A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.

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Номер записи: 78
09-02-2017 дата публикации

MONITORING SYSTEM FOR TURBOMACHINERY

Номер: US20170037742A1
Автор: Cameron Paul F., Canchi Venkatesh, De Stefano Alessio, Estupinan Miguel J., IV Joseph Stinson, Kemp Frances Julia, Leon Marco Ezra, McElhinney, Monti Andrea, Murgia Fabrice Mario, Pham Thompson Hoang An, Sanjeevi Anbarasu, Scabarozi John Gregory, Schiff Garrett Linn, Tiwari Pankaj Yogendra, Watkins Neal
Принадлежит: Solar Turbines Incorporated

A method of monitoring a plurality of turbomachines is disclosed herein. The method includes a fleet data system periodically receiving first event data from a first monitoring connection system and second event data from a second monitoring connection system. The method also includes the fleet data system storing the first event data and the second event data related to events that have occurred over a predetermined timeframe and sending at least the event data related to the events from the first event data to a monitoring device. The event data includes an event name, an event status, and a timestamp related to when the event occurred. 1. A method of monitoring a plurality of turbomachines , comprising:a first monitoring connection system periodically receiving first event data from a first control system for a first turbomachine of the plurality of turbomachines;a second monitoring connection system periodically receiving second event data from a second control system for a second turbomachine of the plurality of turbomachines;a fleet data system receiving the first event data from the first monitoring connection system and the second event data from the second monitoring connection system;the fleet data system storing the first event data and the second event data related to events that have occurred over a predetermined timeframe;the fleet data system sending at least the event data related to the events from the first event data that have occurred over a selected timeframe to a monitoring device; andthe monitoring device displaying the data related to the events from the first event data that occurred within the selected timeframe on an output display of the monitoring device including an event name, an event status, and a timestamp related to when the event occurred.2. The method of claim 1 , wherein the selected timeframe is determined based on a user input.3. The method of claim 1 , wherein the data related to the selected timeframe from the first event ...

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Номер записи: 79
09-02-2017 дата публикации

PRESSURE ACCUMULATOR DEVICE FOR A MOTOR VEHICLE FUEL INJECTION SYSTEM, AND METHOD FOR OPERATING A PRESSURE ACCUMULATOR DEVICE OF SAID TYPE

Номер: US20170037805A1
Автор: ANETSBERGER Daniel, CHIA Tet Kong Brian, SASSLER Walter
Принадлежит:

An electrically driven solenoid coupled to a spring-operated valve, regulates pressure in an accumulator by opening when a predefined threshold pressure in a pressure accumulator is exceeded. The solenoid provides an assistive force to a spring-closed valve, reducing the amount of pressure required to open the valve responsive to the amount of current provided to the solenoid. The threshold pressure at which the valve opens is thus determined by the amount of current provided to the solenoid. Increasing the current decreases the threshold pressure; decreasing the current increases the threshold pressure. 1. A method for operating a pressure accumulator device for a motor vehicle fuel injection system , the method comprising:applying fuel at a high pressure, to a pressure accumulator, by a fuel pump;removing pressure from the accumulator by a controllable, pressure reduction valve, the controllable pressure reduction valve comprising a solenoid-operated valve, configured to open responsive to an applied pressure, the applied pressure at which the solenoid-operated valve opens being determined by an amount of electric current provided to a solenoid coil of the solenoid-operated valve;automatically opening the pressure reduction valve in the event of a predetermined threshold pressure in the pressure accumulator being exceeded; andwherein to check the pressure regulation of the pressure accumulator, the threshold pressure of the pressure reduction valve is increased, and the change in the fluid pressure in the pressure accumulator with respect to time is detected.2. The method of claim 1 , wherein an actual pressure in the pressure accumulator is monitored and compared with a predetermined setpoint pressure; anda difference between the actual pressure and the setpoint pressure is compared with a difference threshold value, wherein if a differential threshold value is exceeded, the threshold pressure of the pressure reduction valve is increased and the characteristic of ...

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Номер записи: 80
08-02-2018 дата публикации

BORESCOPE PLUG

Номер: US20180038241A1
Автор: "ONeill Lisa P.", Betancourt Fabian D., Ramlogan Amarnath
Принадлежит:

A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster. The base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity. 1. A borescope plug comprising:a base attachable to a case and defining a base cavity;a shank having a base engagement element at a first end of the shank; anda plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster,wherein the base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity.2. The borescope plug of claim 1 , further comprising a flange located between the second end of the shank and the plug member claim 1 , wherein the flange is larger than the borescope aperture.3. The borescope plug of claim 1 , further comprising a retainer that retains the base engagement element within the base cavity.4. The borescope plug of claim 3 , wherein the retainer is integrally formed with the base.5. The borescope plug of claim 4 , wherein the retainer comprises a crimping feature.6. The borescope plug of claim 3 , wherein the retainer fits around a portion of the shank and keeps the shank and the base movably together while allowing the shank and plug member to rotate about a plug axis.7. The borescope plug of claim 1 , wherein the base includes a first anti-rotation element and the base engagement element includes a second anti-rotation element claim 1 , wherein the first anti-rotation element engages with the second anti-rotation element such that the shank and ...

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Номер записи: 81
08-02-2018 дата публикации

FLUTTER SENSING AND CONTROL SYSTEM FOR A GAS TURBINE ENGINE

Номер: US20180038285A1
Автор: Morris Robert J., Rosenkrans William E.
Принадлежит:

A gas turbine engine includes a fan section that has a fan. A fan casing surrounds the fan section. A compressor section defines an engine axis. A gear train reduces a rotational speed of the fan relative to a shaft. A low pressure turbine is coupled to the shaft. A nacelle extends along the engine axis and surrounds the fan casing, a bypass ratio of greater than 10. A variable area fan nozzle defines a discharge airflow area. A flutter sensing system includes a controller programmed to move the variable area fan nozzle to vary the discharge airflow area in response to detecting an airfoil flutter condition associated with adjacent airfoils of the fan. 1. A gas turbine engine comprising:a fan section including a fan;a fan casing surrounding the fan section;a compressor section defining an engine axis;a gear train that reduces a rotational speed of the fan relative to a shaft;a low pressure turbine coupled to the shaft;a nacelle extending along the engine axis and surrounding the fan casing;a bypass ratio of greater than 10;a variable area fan nozzle defining a discharge airflow area; anda flutter sensing system including a controller programmed to move the variable area fan nozzle to vary the discharge airflow area in response to detecting an airfoil flutter condition associated with adjacent airfoils of the fan.2. The gas turbine engine as recited in claim 1 , wherein the discharge airflow area extends between the variable area fan nozzle and a core engine casing that surrounds the compressor section.3. The gas turbine engine as recited in claim 2 , wherein the flutter sensing system includes a sensor in communication with the controller claim 2 , and the controller is programmed to move the variable area fan nozzle between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area in response to the airfoil flutter condition.4. The gas turbine engine as recited ...

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Номер записи: 82
08-02-2018 дата публикации

FLUTTER SENSING AND CONTROL SYSTEM FOR A GAS TURBINE ENGINE

Номер: US20180038286A1
Автор: Morris Robert J., Rosenkrans William E.
Принадлежит:

A gas turbine engine includes a fan section that has a fan with a plurality of airfoils, a compressor section, a gear train that reduces a rotational speed of the fan relative to a shaft in operation, a turbine section that has a first turbine and a second turbine, and a bypass ratio of greater than 10. The first turbine drives the shaft. A nacelle extends along an engine axis and surrounds the fan. A variable area fan nozzle defines a discharge airflow area. A fan airfoil flutter sensing system has a first sensor that actively and selectively detects a fan airfoil flutter condition in operation, and communicates with a controller programmed to move the variable area fan nozzle and vary the discharge airflow area to mitigate the flutter condition. 1. A gas turbine engine , comprising:a fan section including a fan with a plurality of airfoils;a compressor section;a gear train that reduces a rotational speed of the fan relative to a shaft in operation;a turbine section including a first turbine and a second turbine, the first turbine driving the shaft;a nacelle extending along an engine axis and surrounding the fan;a bypass ratio of greater than 10;a variable area fan nozzle defining a discharge airflow area; anda fan airfoil flutter sensing system including a first sensor that actively and selectively detects a fan airfoil flutter condition in operation, and communicates with a controller programmed to move the variable area fan nozzle and vary the discharge airflow area to mitigate the flutter condition.2. The gas turbine engine of claim 1 , wherein the flutter sensing system is a closed-loop system.3. The gas turbine engine of claim 2 , wherein the controller is programmed to cause the variable area fan nozzle to move in response to detecting a cross-wind condition.4. The gas turbine engine of claim 2 , wherein the controller is programmed to differentiate between the flutter condition and a non-flutter condition.5. The gas turbine engine of claim 4 , wherein the ...

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Номер записи: 83
08-02-2018 дата публикации

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON ACCELERATION POWER

Номер: US20180038287A1
Автор: CHAREST Alexandre, LAMARRE Sylvain, MEUNIER Gabriel
Принадлежит:

Systems and methods for controlling an gas turbine engine are provided. The method comprises receiving a requested engine speed and obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow. A required fuel flow to obtain the requested engine speed is determined as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow. A command to a fuel flow metering valve is output in accordance with the required fuel flow. 1. A system for controlling a gas turbine engine , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed;', 'obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow; and', 'determining the required fuel flow to obtain the requested engine speed as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the required fuel flow based on an acceleration ...

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Номер записи: 84
12-02-2015 дата публикации

TURBOMACHINE AIRFOIL POSITIONING

Номер: US20150044017A1
Автор: Smith Paul Kendall
Принадлежит: GENERAL ELECTRIC COMPANY

Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine. 1. A turbomachine comprising:a diffuser; a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades;', 'a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and', 'a third airfoil row of the first type adjacent the second airfoil row,, 'a plurality of airfoil rows, includingwherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.2. The turbomachine of claim 1 , selected from a group consisting of: a turbine claim 1 , an engine claim 1 , and a compressor.3. The turbomachine of claim 2 , wherein the turbomachine is a gas turbine.4. The turbomachine of claim 1 , wherein the at least one of the plurality of airfoil rows is clocked to a ...

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Номер записи: 85
12-02-2015 дата публикации

TURBINE THRUST CONTROL SYSTEM

Номер: US20150044024A1
Автор: Donnelly Stephen Raymond
Принадлежит: GENERAL ELECTRIC COMPANY

Systems and programs for controlling thrust in a turbine by adjusting the clearance between a packing seal and a rotating component are disclosed. In one embodiment, a system includes a controller configured to move a packing seal to a selected clearance position in response to a thrust pressure exceeding a target pressure, and a sensor coupled to the controller and configured to detect the thrust pressure. 1. A system for controlling thrust in a turbine , the system comprising:a controller configured to move a packing seal to a selected clearance position in response to a thrust pressure exceeding a target pressure; anda sensor coupled to the controller and configured to detect the thrust pressure.2. The system for controlling thrust in a turbine of claim 1 , wherein the controller is coupled to the packing seal through a mechanical coupling component.3. The system for controlling thrust in a turbine of claim 1 , wherein the thrust pressure acts on a rotor comprising a thrust fitting.4. The system for controlling thrust in a turbine of claim 3 , wherein the thrust fitting projects radially outward from a rotor claim 3 , and the packing seal is radially distal to the thrust fitting.5. The system for controlling thrust in a turbine of claim 3 , wherein the thrust fitting defines a step section within the turbine.6. The system for controlling thrust in a turbine of claim 1 , wherein the packing seal comprises a plurality of packing seals.7. The system for controlling thrust in a turbine of claim 6 , wherein the selected clearance position comprises a plurality of selected clearance positions corresponding to each of the plurality of packing seals claim 6 , and the system is further configured to move each of the plurality of packing seals to the corresponding one of the plurality of selected clearance positions.8. The system for controlling thrust in a turbine of claim 1 , wherein the thrust pressure comprises a first thrust pressure and a second thrust pressure claim ...

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Номер записи: 86
07-02-2019 дата публикации

ELECTRICAL RESISTANCE WEAR INDICATOR

Номер: US20190040759A1
Автор: Agoos Ian F., Benoit Corey A., Dreger, III Edward F., Warren Eli Cole
Принадлежит:

In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first component including: a first plate; a second plate opposite the first plate; a plurality of wires extending from first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires; and a potting material configured to partially fill the first component and fill voids between the plurality of wires, such that the plurality of wires are electrically insulated from each other by the potting material. 1. In combination a wear indicator and a component of a gas turbine engine , wherein the wear indicator is secured to a surface of the component of the gas turbine engine , the wear indicator comprising: a first plate;', 'a second plate opposite the first plate;', 'a plurality of wires extending from first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires; and', 'a potting material configured to partially fill the first component and fill voids between the plurality of wires, such that the plurality of wires are electrically insulated from each other by the potting material., 'a first component including2. The combination of claim 1 , wherein the first component is configured to delaminate when impacted by a blade of the gas turbine engine.3. The combination of claim 1 , further comprising: a second component of the wear indicator having a blind hole partially enclosing the first component claim 1 , wherein the wear indicator is secured to a surface of the component of the gas turbine engine through the second component.4. The combination of claim 1 , wherein the component is a blade outer air seal.5. The combination of claim 1 , further comprising a measurement device electrically connected to the first plate through a ...

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Номер записи: 87
07-02-2019 дата публикации

FAILURE DETECTION APPARATUS FOR FUEL SYSTEMS OF ENGINE

Номер: US20190040811A1
Автор: KITADA Junya, Maeda Satoshi, MATSUNAGA Hideo
Принадлежит: MITSUBISHI JIDOSHA KOGYO KABUSHIKI KAISHA

A failure detection apparatus for fuel systems of an engine includes a first failure determiner executing, while the engine is in each of a first injection form and a second injection form, a failure determination process on the corresponding fuel system, a second failure determiner executing, when the first failure determiner determines occurrence of a failure in one of the injection forms, a failure determination process on the fuel system corresponding to the other injection form, a failure locator determining whether or not the failure has occurred, for each of the fuel systems responsible for the first and second injection forms, based on a result by the second failure determiner, and a purge process prohibiter prohibiting execution of a purge process for the engine. The second failure determiner causes the purge process prohibiter to prohibit execution of the purge process, when executing the failure determination process on the fuel system. 1. A failure detection apparatus for fuel systems of an engine capable of switching between a first injection form and a second injection form , the failure detection apparatus comprising:a first failure determiner executing, while the engine is in operation in each of the first and second injection forms, a failure determination process on the corresponding fuel system;a second failure determiner executing, when the first failure determiner determines occurrence of a failure during operation in one of the injection forms, a failure determination process on the fuel system corresponding to the other injection form during operation in the other injection form;a failure locator assertively determining whether or not the failure has occurred, for each of the fuel systems responsible for the first and second injection forms, based on a result of the failure determination process by the second failure determiner; anda purge process prohibiter prohibiting execution of a purge process of causing fuel evaporative emissions ...

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Номер записи: 88
07-02-2019 дата публикации

COMPONENTS CONFIGURED TO AUTONOMOUSLY DETECT AND ACCOMMODATE STRUCTURAL CHANGES

Номер: US20190041280A1
Автор: Barua Ananda, Erno Daniel J., Hallman Darren L., Subramaniyan Arun Karthi, Sun Changjie
Принадлежит:

A component has a first structural configuration and a second structural configuration. The component includes a sensor assembly including a plurality of interconnected structural members defining a plurality of load paths. A first structural member and a second structural member define a first load path when the component is in the first structural configuration. The first structural member and a third structural member define a second load path when the component is in the second structural configuration. The second load path is configured to bypass the second structural member. The sensor assembly is configured to detect a characteristic of the component that changes when the component switches between the first structural configuration and the second structural configuration. 1. A component having a first structural configuration and a second structural configuration , said component comprising: a first structural member;', 'a second structural member coupled to said first structural member, wherein said first structural member and said second structural member define a first load path when said component is in the first structural configuration; and', 'a third structural member coupled to said first structural member, wherein said first structural member and said third structural member define a second load path when said component is in the second structural configuration, and wherein the second load path is configured to bypass said second structural member,, 'a sensor assembly including a plurality of interconnected structural members defining a plurality of load paths, said plurality of interconnected structural members comprisingwherein said sensor assembly is configured to detect a characteristic of said component that changes when said component switches between the first structural configuration and the second structural configuration.2. The component in accordance with claim 1 , wherein said sensor assembly comprises at least one terminal coupled to ...

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Номер записи: 89
16-02-2017 дата публикации

FIVE-DEGREE-OF-FREEDOM ADJUSTMENT AND POSITIONING METHOD AND APPARATUS FOR ASSEMBLY/MEASUREMENT OF ROTOR AND STATOR OF AIRCRAFT ENGINE

Номер: US20170044928A1
Автор: Gu Wei, HUANG Jingzhi, TAN Jiubin, WEN ZhongPu
Принадлежит:

A five-degree-of-freedom adjustment and positioning method and apparatus for assembly/measurement of rotor and stator of an aircraft engine; said method comprises adjusting a plane motion and a rotation of a tested piece through composite motion comprising five degrees of freedom: a 360° rotatory motion around a Z axis, a plane motion along an X axis and a plane motion along a Y axis, a rotatory motion around the X axis and a rotatory motion around the Y axis; said apparatus comprises: a clamping mechanism (1), a turning platform component (A), a translational platform component (B) and a rotational platform component (C). The present invention designs a five-degree-of-freedom adjustment and positioning method and apparatus having properties of large load bearing, high precision and high stiffness, thus improving assembly efficiency and measurement accuracy of the aircraft engine. 1. A five-degree-of-freedom adjustment and positioning method for assembly/measurement of rotor and stator of an aircraft engine , the method comprising: adjusting a plane motion and a rotation of a tested piece through a composite motion comprising five degrees of freedom: a 360° rotatory motion around a Z axis , a plane motion along an X axis , a plane motion along a axis , a rotatory motion around the X axis and a rotatory motion around the Y axis , wherein the X axis and the Y axis are orthogonal to each other , and the Z axis is perpendicular to a plane determined by X and Y axes , specific processes of adjustments are as follows:{'sub': 0', '0, 'a plane motion adjustment: 1) firstly driving a tested piece to rotate at 360° through the Z axis, measuring a radial error of a specified cross-section of the tested piece by using a sensor, and obtaining an eccentricity Δx at the X axis and an eccentricity Δy at the Y axis of the tested piece; 2) adjusting the tested piece to move along the X axis according to Δx, and setting motion displacement as Δx; adjusting the tested piece to move ...

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Номер записи: 90
16-02-2017 дата публикации

METHOD OF MONITORING RUBBING BETWEEN A ROTARY PARTY AND A STATIONARY PART IN A ROTATING TURBOMACHINE, MONITORING ARRANGEMENT AND TURBOMACHINE

Номер: US20170044929A1
Автор: GARBIN Riccardo, NURZAD Dario, PEPE Antonello, SEPE Marzia
Принадлежит: Nuovo Pignone Srl

The arrangement for monitoring rubbing between a rotary part and a stationary part in a rotating turbomachine comprises at least one mechanical oscillations detector for measuring mechanical oscillations at at least one point of the turbomachine, at least one particles detector for measuring debris passing in at least one section of a flow path of the turbomachine, and an electronic monitoring unit electrically or electromagnetically connected to the oscillations detector and the particles detector, and arranged to acquire and process signals generated by the oscillations detector and the particles detector. The electronic monitoring unit uses the oscillations measurement primarily for estimating presence of rubbing and the debris measurement primarily for estimating severity of rubbing. 2. The method of claim 1 , wherein mechanical oscillations are measured at a set of points of the turbomachine claim 1 , wherein oscillations measurements at the set of points are used for estimating a location of rubbing.3. The method of claim 1 , wherein debris is measured at an outlet of the turbomachine.4. The method of claim 1 , wherein rubbing severity estimation is carried out if rubbing presence estimation is positive.5. The method of claim 1 , further comprising determining an operating mode of the turbomachine wherein the rubbing presence estimation and/or the rubbing severity estimation are/is based on the determined operating mode.6. The method of claim 1 , wherein the turbomachine is in an online washing operating mode with high mass flow of detergent substance.7. The method of claim 1 , wherein the turbomachine is a combustion gas turbine engine.8. An arrangement for monitoring rubbing between a rotary part and a stationary part in a rotating turbomachine claim 1 , the arrangement comprising:at least one mechanical oscillations detector;at least one particles detector; andan electronic monitoring unit electrically or electromagnetically connected to the at least one ...

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Номер записи: 91
16-02-2017 дата публикации

FREE PISTON ENGINE

Номер: US20170044975A1
Автор: YAAKOBY Shaul
Принадлежит:

An internal combustion engine for providing a linear reciprocating movement of an output shaft along a longitudinal axis. The engine has a double sided cylinder that is bounded by an engine head at each side of the cylinder. An exhaust unit is positioned at each side of the cylinder. A piston is positioned within a cylinder inner space and freely slides with respect to the cylinder along the longitudinal axis. Two piston rods are aligned with the longitudinal axis. Each piston rod is connected at a different side of the piston. Each of the piston rods has exhaust openings. 1. An internal combustion engine configured to generate a linear reciprocating movement of an output shaft along a longitudinal axis , comprising:a double sided cylinder bounded by an engine head at each side thereof;an exhaust unit positioned at each side of the cylinder and connected to one corresponding engine head;a double-sided piston positioned within a cylinder inner space of the cylinder and freely sliding with respect to the cylinder along the longitudinal axis; andtwo piston rods aligned with the longitudinal axis, each piston rod connected at a different side of the piston; 'each of the piston rods comprises a plurality of exhaust openings.', 'wherein2. The engine according to claim 1 , wherein:the exhaust openings comprise at least one of holes, longitudinal slots, or grooves.3. The engine according to claim 1 , wherein:each of the piston rods is provided with a cavity extending at least from an open end of the piston rod, said open end being remote from the piston, to an exhaust opening, said exhaust opening being closer to the piston than the open end.4. The engine according to claim 1 , wherein:the exhaust openings form an integral part of the piston rods.5. The engine according to claim 1 , wherein:each of the piston rods is a sliding valve.6. The engine according to claim 1 , wherein:the piston is configured within the cylinder such that a sliding movement of the piston within the ...

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Номер записи: 92
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: 93
03-03-2022 дата публикации

PROBE PLACEMENT OPTIMIZATION IN GAS TURBINE ENGINES

Номер: US20220065126A1
Автор: Key Nicole Leanne, Lou Fangyuan
Принадлежит: PURDUE RESEARCH FOUNDATION

A method of optimizing probe placement in a turbomachine is disclosed which includes determining wavenumber (Wn) of N dominant wavelets generated by upstream and downstream stators and blade row interactions formed around an annulus, establishing a design matrix A utilized in developing flow properties around the annulus having a dimension of m×(2N+1), iteratively modifying probe positions placed around the annulus and determining a condition number of the design matrix A for each set of probe positions until a predetermined threshold is achieved for the condition number representing optimal probe position, wherein the condition number is defined as norm A·norm A+, wherein A+ represents inverse of A for a square matrix and a Moore-Penrose pseudoinverse of A for a rectangular matrix.

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Номер записи: 94
03-03-2022 дата публикации

SYSTEM AND METHOD FOR DETECTING VIBRATIONS IN ROTATING MACHINERY

Номер: US20220065688A1
Автор: CICIRIELLO Lucia
Принадлежит:

Embodiments of the invention are shown in the figures, where a system for vibration detection is shown, the system comprising: one or more drivelines including a rotatable component rotatable about a rotational axis relative to another component; an electrical machine having a rotor and a stator rotatable with respect to one another, the rotor being arranged to at least one of drive and be driven by a part of the driveline, the electrical machine being adapted to provide signals indicative for at least one of a motion and a force between the rotor and the stator and a torque applied on the rotor; and an analysis unit adapted to receive the signals and to detect a vibration signature of the rotatable component with respect to the other component based on the signals. 1. A system comprising:at least one driveline including a rotatable component rotatable about a rotational axis relative to another component;at least one electrical machine having a rotor and a stator rotatable with respect to one another, the rotor being arranged to at least one of drive and be driven by a part of the driveline, the electrical machine being adapted to provide signals indicative for at least one of a motion and a force between the rotor and the stator and a torque applied on the rotor; andan analysis unit adapted to receive the signals and to detect a vibration signature of the rotatable component of the driveline with respect to the other component based on the signals.2. The system according to claim 1 , wherein a fluid is arranged in a clearance between the rotatable component and the other component and wherein the rotor of the electrical machine and the rotatable component are fixedly connected to one another.3. The system according to claim 1 , wherein the signals are based on asymmetric magnetic forces in the electrical machine claim 1 , wherein the electrical machine comprises a plurality of coils claim 1 , wherein the signals are based on differences among voltages or ...

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Номер записи: 95
03-03-2022 дата публикации

MONITORING OF THE STATE OF HEALTH OF AT LEAST TWO VIBRATION SENSORS OF A BYPASS TURBOMACHINE

Номер: US20220065689A1
Автор: ALEKSANDER Boris
Принадлежит: SAFRAN AIRCRAFT ENGINES

The invention relates to a monitoring process of the state of health of at least two vibration sensors of a twin turbomachine comprising a low-pressure body and a high-pressure body, a vibration sensor being located at the front of the turbomachine, a vibration sensor being located at the rear of the turbomachine, each of the sensors being configured to measure vibrations of the low-pressure and high-pressure bodies at the front and at the rear of the turbomachine, the process being executed in a processing unit () of the turbomachine communicating with each of the sensors and comprising the following steps:

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Номер записи: 96
14-02-2019 дата публикации

UNITARY ACTUATOR VALVE FOR DOWNHOLE OPERATIONS

Номер: US20190048684A1
Автор: Achanta Anjani, Boyer Luke Alan, Hetz Shay, Hudson Jack, Kao Conrad, Snitkoff Joshua Raymond, Speights John Patrick, Stolboushkin Eugene
Принадлежит: Baker Hughes, a GE company, LLC

A member includes a unitary body defining a first portion integrally joined with a second portion through one or more shear tabs 1. A member comprising:a unitary body defining a first portion integrally joined with a second portion through one or more shear tabs.2. The member according to claim 1 , wherein the first portion defines a piston portion having a first end section including an activation member claim 1 , a second end section claim 1 , and an intermediate portion extending therebetween.3. The member according to claim 2 , wherein the second portion defines a piston ring member disposed adjacent the first end section and includes a first section having a first diameter and a second section having a second diameter that is greater than the first diameter.4. The member according to claim 3 , wherein the second end section includes at least one ball receiving recess and a ball arranged in the ball receiving recess.5. The member according to claim 3 , wherein the second end section includes a plurality of cantilevered fingers claim 3 , each of the plurality of cantilevered fingers including a first radially outwardly directed projection and a second radially outwardly directed projection axially spaced from the first radially outwardly directed projection.6. The member according to claim 5 , wherein the second end section includes a hub including a recess and a stopper integrally joined to the hub through at least one shear element claim 5 , the stopper limiting axial movement of the piston member.7. The member according to claim 6 , where the stopper includes a central bore including an annular shoulder portion selectively receivable of the second radially outwardly directed projection.8. The member according to claim 5 , wherein the second end section includes a plurality of slots defining the plurality of cantilevered fingers.9. The member according to claim 8 , wherein each of the plurality of slots defines a spiral slot.10. An actuator valve (AV) ...

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Номер записи: 97
14-02-2019 дата публикации

TURBINE DIAGNOSTIC FEATURE SELECTION SYSTEM

Номер: US20190048740A1
Автор: AGARWAL Anurag, Alla Rajesh, Escriche Lorenzo, Gruber Frank
Принадлежит:

A turbine diagnostic machine learning system builds one or more turbine engine performance models using one or more parameter or parameter characteristics. A model of turbine engine performance includes ranked parameters or parameter characteristics, the ranking of which is calculated by a model builder based upon a function of AIC, AUC and p-value, resulting in a corresponding importance rank. These raw parameters and raw parameter characteristics are then sorted according to their importance rank, and selected by a selection component to form one or more completed models. The one or more models are operatively coupled to one or more other models to facilitate further machine learning capabilities by the system. 1. A machine learning system , comprising:a processor that executes computer executable components stored in memory;a raw parameter analyzer that identifies characteristics associated with a set of respective raw parameters;a model builder that builds a classification model based on one parameter at a time of the set of raw parameters and computes Akaike Information Criterion, Area under Curve, and Hypothesis acceptance as per alpha error (p-value);a ranking component that computes importance rank for respective raw parameters based on the respective computed Akaike Information Criterion, Area under Curve, and p-value;a sorting component that sorts features based on respective raw parameter importance ranking; anda selection component that selects at least two features based on the sorting to utilize in connection with building the classification model.2. The system of claim 1 , wherein the ranking component computes the importance rank as a function of Akaike Information Criterion claim 1 , Area under Curve claim 1 , and Hypothesis acceptance as per alpha error (p-value).3. The system of further comprising a clustering component that combines two or more of the selected features into respective clusters and computes Akaike Information Criterion claim 1 , ...

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Номер записи: 98
25-02-2016 дата публикации

DETECTING ROTOR ANOMALIES DURING TRANSIENT SPEED OPERATIONS

Номер: US20160054171A1
Автор: Maalouf Mel Gabriel
Принадлежит:

A computing system for detecting anomalies in a rotor during a transient speed operation is provided which includes a first computing device programmed to identify a baseline sample set including a plurality of baseline samples. The computing device collects a plurality of current vibration samples from at least one vibration sensor during the transient speed operation, including a first current vibration sample including a first rotational speed measurement of the rotor and a first vibration measurement. The computing device selects one or more baseline samples from the baseline sample set based at least in part on the first rotational speed. Each baseline sample includes a baseline vibration value. The computing device compares the first vibration measurement to one or more baseline vibration values of the selected one or more baseline samples. The computing device transmits an alert to a monitoring device based at least in part on the comparing. 1. A computing system for detecting anomalies in a rotor during a transient speed operation , said computing system comprising a first computing device programmed to:identify a baseline sample set, wherein the baseline sample set includes a plurality of baseline samples associated with the rotor;collect a plurality of current vibration samples from at least one vibration sensor during the transient speed operation, the plurality of current vibration samples including a first current vibration sample including a first rotational speed measurement of the rotor and a first vibration measurement;select one or more baseline samples from the baseline sample set based at least in part on the first rotational speed, each baseline sample including a baseline vibration value;compare the first vibration measurement to one or more baseline vibration values of the selected one or more baseline samples; andtransmit an alert to a monitoring device based at least in part on the comparing.2. The computing system of claim 1 , wherein ...

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Номер записи: 99
22-02-2018 дата публикации

TURBOFAN GAS TURBINE ENGINE SHAFT BREAK DETECTION SYSTEM AND METHOD

Номер: US20180051585A1
Автор: Coffey Scot, Haugland Ronnie, Xiong Yufei
Принадлежит: HONEYWELL INTERNATIONAL INC.

A system and method for detecting a shaft break in a turbofan gas turbine engine includes sensing fan rotational speed and sensing turbine engine rotational speed. A rate of change of rotational speed difference between the sensed fan rotational speed and the sensed turbine engine rotational speed is determined in a processor, and a determination that a shaft break has occurred is made in the processor based at least in part on the rate of change of the rotational speed difference. 1. A method for detecting a shaft break in a turbofan gas turbine engine , the turbofan engine including at least a fan and a turbine , the method comprising the steps of:sensing fan rotational speed;sensing turbine engine rotational speed;determining, in a processor, a rate of change of rotational speed difference between the sensed fan rotational speed and the sensed turbine engine rotational speed; anddetermining, in the processor, that a shaft break has occurred based at least in part on the rate of change of the rotational speed difference.2. The method of claim 1 , wherein the step of determining the rate of change of rotational speed difference comprises:subtracting, in the processor, the sensed turbine engine rotational speed from the sensed fan rotational speed to determine a rotational speed difference; anddetermining, in the processor, the rate of change of rotational speed difference.3. The method of claim 2 , wherein the step of determining that a shaft break has occurred comprises:comparing the rate of change of rotational speed difference to a predetermined threshold value; anddetermining that the shaft break has occurred if the rate of change of rotational speed difference is less than or equal to the predetermined threshold value.4. The method of claim 2 , wherein the step of determining the rate of change of rotational speed difference comprises filtering the rotational speed difference through a first-order high-pass filter.5. The method of claim 1 , wherein the step of ...

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Номер записи: 100