EP2619461B1 - Dispositif et procédé pour l'utilisation en sécurité d'un compresseur à la limite de pompage - Google Patents

Dispositif et procédé pour l'utilisation en sécurité d'un compresseur à la limite de pompage Download PDF

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Publication number
EP2619461B1
EP2619461B1 EP11813656.3A EP11813656A EP2619461B1 EP 2619461 B1 EP2619461 B1 EP 2619461B1 EP 11813656 A EP11813656 A EP 11813656A EP 2619461 B1 EP2619461 B1 EP 2619461B1
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EP
European Patent Office
Prior art keywords
compressor
blade
impeller
state
blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
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EP11813656.3A
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German (de)
English (en)
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EP2619461A1 (fr
Inventor
Malte Köller
Olaf Magnor
Daniel Reitebuch
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
IAV GmbH Ingenieurgesellschaft Auto und Verkehr
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IAV GmbH Ingenieurgesellschaft Auto und Verkehr
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Publication of EP2619461A1 publication Critical patent/EP2619461A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/70—Type of control algorithm
    • F05D2270/708—Type of control algorithm with comparison tables

Definitions

  • the present invention relates to a device according to the preamble of claim 6 and a method according to the preamble of claim 1 for safe operation of a compressor at the surge line.
  • a device and such a method is for example from the US-A-4,955,269 bekant.
  • Compressors are thermal turbomachines and are used for compressing gases, in particular air. Compressors find in engine construction for continuously or periodically operating internal combustion engines far-reaching application and are used for example in reciprocating engines to increase performance, in gas turbines for generating electrical energy or in jet engines for propulsion of aircraft to compress the necessary air for combustion. The drive of the compressor takes place for example by the utilization of the energy contained in the exhaust gas, but can also be done mechanically or electrically.
  • the compressor can be designed according to its application, for example, in a jet engine as axial compressor to achieve high mass flows.
  • a mass flow is to be understood as an air mass which is conveyed through the compressor for a specific time.
  • variables related to geometric conditions or environmental conditions such as throughput or volumetric flow, may be used to characterize the operation of the compressor.
  • the air to be compressed flows axially to the compressor from the environment and is transported by the compressor in the jet engine and thereby compressed.
  • the compressor is generally constructed of a mounted on a shaft impeller with compressor blades, which rotates in a housing with corresponding guide vanes and thus forms a compressor stage.
  • the provided with a blade root compressor blades are mounted playfully on the impeller so that the compressor blade center itself at a sufficiently fast rotation of the impeller due to the resulting outward centrifugal force and sit firmly in the impeller.
  • the blades are firmly connected to the impeller.
  • the Guide vanes are fixed to the housing.
  • several compressor stages can be arranged one behind the other in the compressor for jet engines, so as to form a multi-stage compressor.
  • the compressor can be preceded by a blower and a second compressor.
  • the drive of the impeller is via the shaft, which is driven by a turbine at the end of the jet engine.
  • the compressor capacity is set by the impeller speed and by the mass flow in the compressor.
  • the drive power of the shaft can be changed by the turbine to adjust the speed of the impeller.
  • the mass flow in the compressor can be varied by means of adjustable guide vanes, blow-off valves or blade tip gap change. This makes it possible to set an operating point of the compressor, which defines itself for example by a pressure ratio and a mass flow, by compressor power and speed or other alternatives.
  • the pressure ratio of a compressor stage is limited by the fact that the compressed air in the compressor stage can not follow the compressor blade contour arbitrarily, but separates starting from the trailing edge of the compressor blade.
  • the maximum step pressure ratio increases with increasing mass flow and represents the outermost limit of the stable operating range as a pumping limit.
  • the maximum mass flow of the compressor stage is limited by a plug limit as soon as a flow velocity at the level of the sound velocity develops in a flow cross section, usually at the compressor inlet limited mass flow.
  • a pressure difference is established between the upper and lower sides. Since a compressor blade is an elastic component, it will yield to the pressure difference between top and bottom and bend. With increasing load, the deflection and thus the deflection of the compressor blades increase.
  • the operating range of the compressor is thus limited on the one hand by the surge limit and on the other hand by the stuffing limit.
  • the pumping limit is an unfavorable for the compressor, unstable operating condition in which it destroys the Compressor can come. This unstable operating condition must be avoided, especially when using the compressor in jet engines, in order to ensure operational safety.
  • the course of the surge limit of the operating range is subject to operational and aging-related changes.
  • the pump size is influenced by the changes in ambient conditions during flight operation, compressor inlet conditions, the thermal inertia of the components and the intrusion of foreign objects. Changes in the top clearance of the compressor blades towards the housing, changes in the bearing clearance due to aging and wear, deformations and deposits of the blade geometries and on the housing have an influence on the surge limit.
  • the surge margin for new engines is designed to be about 25% of the pressure ratio, so that it has been reduced to 5% by the age-related lowering of the surge limit by the end of the life of the compressor.
  • the efficiency optimum of a compressor is generally close to the surge limit in the stable operating range, resulting in a consumption disadvantage due to the safety-relevant design of the surge margin. Therefore, from the prior art devices and methods for operating compressors are known, with which the compressors are to be protected against this dangerous operating condition with optimal Verêtr Obersrad. For example, bleed valves are used to lower the pressure ratio across a compressor stage. In many cases, an adjustment rotatably mounted vanes is provided with which the pressure ratio or the mass flow can be varied, thus ensuring a safe, stable operating condition. Furthermore, an active change of the top clearance of the compressor blade by heating or cooling of the compressor housing is known. As a prerequisite, however, a reliable detection of the operating state of the compressor and accordingly the distance of the current operating point of the compressor to the surge limit is necessary.
  • the compressor blade tip deflection may be calculated from the time difference of the measured compressor blade tip transit time at a sensor on the housing and an ideal transit time that would result from an ideally rigid compressor blade and the known tangential velocity of the compressor blade tip.
  • the transit time is understood as the point in time at which the compressor blade tip is located at least partially in the sensor region of the sensor on the housing of the compressor. In this case, for example, the entry into the sensor area, the passage through the sensor area or the exit from the sensor area can be defined in order to define the transit time.
  • the method is therefore based on the identification of signs of an unstable compressor state. It is known that these precursors show up a few milliseconds before the onset of compressor instability, so that there is no longer sufficient time to carry out countermeasures, for example reducing the fuel mass, opening the blow-off valves or adjusting the guide vanes.
  • the publication DE 10 2008 036 305 A1 describes a method in which a power consumption of the compressor is determined from the transit times of the individual compressor blades. For this, the real transit times are compared with the ideal model transit times and their difference evaluated as a result of the deflection of the compressor blades. From the deflection of the compressor blades can be calculated a compressor torque and, accordingly, with the compressor speed, a compressor power. In stable operating conditions, a balance between the drive power and the compressor power sets. A disturbance of this power balance is considered to be incipient instability and the approach to the surge line is indicated.
  • the condition such as wear, fouling, erosion and deformation on the compressor blades, as well as the change in the position of the compressor blades, which reorient themselves at each engine start by the Schaufelfußspiel, have an influence on the measured passage time in relation to the nominal passage time, based on the deflection or the deflection of the compressor blades is determined and closed at the operating point and its distance from the surge line.
  • the methods known in the prior art can not detect and eliminate this influence, so that it can lead to false detection. A reliable determination of the operating point of the compressor and thus the surge margin of the operating point is not possible.
  • the object of the invention is to provide a method and a device with which a reliable detection of the operating state of the compressor is made possible.
  • the detection should be independent of influences from a changed state or a changed position of the compressor blades.
  • the state of each individual compressor blade defines a deviation from an ideal state and has an influence on the real measured transit time.
  • the transit time is understood as the point in time at which the compressor blade tip is located at least partially in a sensor region of a sensor on the housing of the compressor.
  • the entry into the sensor area, the passage through the sensor area or the exit from the sensor area can be used to define the transit time.
  • each compressor blade on the impeller may change each time it is started. Since the compressor blades are mounted playfully in the impeller and only at startup of the compressor at a minimum speed due to centrifugal self-align and anchor in the leadership, these deviations come from operational use to operational use to conditions. Even with compressors with fixedly attached to the impeller compressor blades, a change in position, for example by assembly work done.
  • the ideal transit time is understood to mean the point in time which would result for an ideal impeller with equidistant compressor blade arrangement and infinitely stiff compressor blades without deviations from state and position.
  • the transit time is understood as the point in time at which the compressor blade tip is located at least partially in the sensor region of the sensor on the housing of the compressor.
  • the entry into the sensor area, the passage through the sensor area or the exit from the sensor area can be defined in order to define the transit time.
  • the compressor blades align.
  • the deviations of the compressor blade from the ideal state in terms of condition and position remain constant for this operation and can be compensated. Only loosen when lowering the compressor below a certain minimum speed the compressor blades are corresponding to the foot play and the deviations are again undetermined ..
  • the invention provides a method with which a reliable detection of the operating state is made possible regardless of the state and position of the compressor blades and thereby an optimal compressor operation.
  • the deviations from the ideal state of each individual compressor blade during startup of the compressor after reaching the minimum speed for aligning the compressor blades are determined. Based on this compressor blade individually determined deviation can be carried out a correction of the measured during operation passage times of each compressor blade. This correction allows an accurate determination of the operating state and a Wirkwirkgsgradoptimal operation of the compressor below the surge limit.
  • the deviations of the compressor blades are compared with the ideal state redetermined, adapted and included in the evaluation.
  • the thus measured measured passage times are used to determine the deflection due to the deflection of the compressor blade, according to the invention advantageously only the deflection is determined as a result of the fluid mechanics. An independent of the condition and the position of the compressor blades operating point determination is achieved.
  • the invention further provides a device with which the deviations are determined and a correction of the passage times takes place.
  • the apparatus includes at least one sensor for indicating the passage of a compressor blade, henceforth called a compressor blade sensor, and at least one sensor for indicating the rotation of the rotor, henceforth called impeller sensor.
  • the compressor blade sensor outputs a trigger signal as a compressor blade passes.
  • a marking or the like may be provided on the compressor blade tip. From the signal, the transit time is determined.
  • the impeller sensor outputs a trigger signal corresponding to the rotation of the impeller. From this, for example, the speed of the impeller can be calculated. Again, appropriate markings may be provided.
  • the trigger signals of the sensors are related to each other by means of a central time base, so that an accurate assignment of the trigger signals of the impeller and compressor blades can take place. Accordingly, the comparison of the compressor blade sensor and the impeller sensor can be used to compare the measured and ideal transit time for each individual compressor blade.
  • a compressor nominal model is used in accordance with the invention, which images the impeller with the compressor blades as an ideal impeller with equidistant compressor blade arrangement with infinitely rigid ideal compressor blades without deviations from condition and position.
  • the compressor nominal model may be modeled as a memory array in which memory cells equal to the number of compressor blades are present. Each individual compressor blade is assigned an individual memory cell.
  • the compressor nominal model of the measured rotational speed of the impeller is adjusted in phase, so that a direct comparison between the real impeller and the ideal impeller, represented by the compressor nominal model, is possible. As a result, a memory cell rotation equal to the rotation of the real impeller is achieved.
  • a synchronized with the rotation of the impeller counter can be used, with which the individual memory cell of the memory array can be addressed.
  • the compressor nominal model now provides for each individual compressor blade passing through the compressor blade sensor the individual ideal transit time, that is, the time that a geometrically ideal and infinitely rigid compressor blade would produce at the sensor.
  • the difference between the ideal transit time and the actual transit time of the respective compressor blade measured at the compressor gives the deviation, ie the relative transit time.
  • a differentiator is provided in the device according to the invention in order to carry out the corresponding operation.
  • the relative transit time is equal to zero for the ideal case and, in the real case, is composed of a state-related and position-dependent deviation and the actual useful signal, ie the flow-related deviation.
  • the flow-mechanical component of the deviation can be regarded as negligible, so that the state and conditional deviation prevails.
  • This condition-related and position-dependent deviation is assigned to a compressor adaptation model in a compressor-specific manner, with the compressor adaptation model corresponding to the compressor nominal model correspondingly having the same number of memory cells.
  • the compressor adaptation model is integrated with a switching unit with which switching is made between working mode and learning or adaptation mode. If the adaptation mode is enabled, for example by speed thresholds of the impeller, the adaptation can take place.
  • the compressor blade individual state and positional deviations from the compressor adaptation model are used to correct the relative transit time of the respective compressor blade to a corrected relative transit time, such that only the flow-mechanical fraction calculates the deflection the compressor blade is calculated.
  • the state and location-related deviations stored in the compressor adaptation model can be stored as a distance or as a factor in the form of a time, a path or an angle and so on.
  • the measured transit time or the relative transit time calculated therefrom can be used.
  • the impeller speed or tangential velocity of the compressor blade tips is used to calculate an absolute deviation as the path or angle from the ideal condition.
  • geometric parameters of the compressor and its components can be included in the evaluation.
  • the compressor nominal model can be combined with the compressor adaptation model.
  • a sensor configuration can be used, which consists of at least two compressor blade sensors and an impeller sensor. If only one sensor is present, blade oscillations with the same or multiple frequency of the impeller frequency can not be detected. By increasing the number of compressor blade sensors and their irregular distribution over the compressor circumference also these frequencies can be detected. Sensors with different functions can be used. However, a combination of transmission sensitivity and distance sensitivity would have the advantage of allowing gap control for the compressor blades.
  • the calculation of the angle of attack from the available information offers.
  • the calculated angle of incidence is continuously entered into a writable map and thus determined and recorded during the operating time of the engine whose operating map. It is also known from experiments on the test bench, at which angle of attack it comes to the flow separation and thus to the compressor pumping, so that the surge limit is firmly stored in the map. Non-volatile memory behavior keeps this information even after the engine has been shut down, so that there is a fixed safety threshold for the stable operation of the jet engine.
  • the method according to the invention can be applied to a compressor stage or to several or selected compressor stages, which are particularly affected by the risk of pumping.
  • the method of the present invention is capable of not only detecting compressor instabilities by compressor blade viewing, but also distinguishing between rotating separations and compressor blade flutter as rotating separations circulate unlike compressor blade flutter.
  • the inventive method allows an optimal adjustment of the actuators of a compressor, since the actual operating state of the compressor and the position of the surge limit are known.
  • the compressor can thus be operated with optimum efficiency, without having to be driven into the unstable operating state. As a result, the specific consumption is lowered.
  • the compressor can be designed, for example, lighter and smaller.
  • the method according to the invention does not require the approach to the surge line in order to be able to determine its position. As a result, safety is increased.
  • the method according to the invention continuously adapts the operating map, so that the operation of the compressor is continuously adapted to its aging state. As a result, the specific consumption decreases. If, for example, a compressor instability occurs, which can be detected by the method, this behavior is corrected in the operating map by adjusting the surge limit.
  • the method according to the invention predicts the failure behavior of the compressor so that unplanned maintenance is avoided and the available service life is known. As a result, operating costs, maintenance costs, conventional costs and storage costs are reduced and availability is increased.
  • the method according to the invention is also compatible with methods of active gap control, in which the gap between the compressor blade tips and the housing is controlled or regulated. Furthermore, the use of variable vanes and the bleed air take-off can be optimized.
  • the exemplary configured device consists of a compressor blade sensor (1) which outputs a trigger signal corresponding to the passage of a compressor blade and an impeller sensor (2) which outputs a trigger signal corresponding to one revolution of the impeller of the compressor.
  • the two trigger signals are provided with a time stamp.
  • the device is equipped with a compressor nominal model (4) and a compressor adaptation model (5) which run through in phase by means of a controller (6) to the speed of the impeller.
  • the controller (6) performs an intervention according to the control deviation.
  • the compressor nominal model (4) as well as the compressor adaptation model (5) consists of a plurality of memory cells (4a, 5a), the number of memory cells of each model corresponding to the number of compressor blades.
  • the memory cells are addressed in phase according to the speed of the impeller by the controller (6) .
  • the compressor nominal model (4) outputs an ideal transit time corresponding to the current compressor blade, which is compared in a differentiator (7) with the measured transit time and outputs a relative transit time. Thereafter, adapted in a Lemmodus state and position deviations of the respective compressor blade from the compressor adaptation model (5) are offset with the relative transit time. So that the compressor adaptation model (5) can be adapted, a switch (8) is provided, which switches over into an adaptation mode when a condition (9) is met . If condition (9) is not fulfilled, the device is operated in working mode. The device outputs at least operating point information calculated from the corrected relative transit time and other quantities in an evaluation unit (10) .
  • the compressor nominal model (4) may be replaced by a function which outputs the ideal transit time in dependence on the impeller speed, since this is the same for all compressor blades and the model impeller of the ideal impeller.
  • the compressor adaptation model ( 5) can be replaced by a characteristic map whose characteristic diagram points can be addressed discretely and output the deviation of the respective compressor blade.
  • the map points can be done for example by means of a synchronized with the impeller counter.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Procédé de calcul du point de fonctionnement d'un compresseur avec au moins un rotor, avec des aubes de compresseur fixées au rotor, avec un carter et au moins deux capteurs (1, 2), un calcul de l'orientation des aubes de compresseur se produisant sur la base duquel le point de fonctionnement et son écartement par rapport à la limite de pompage sont calculés, en mesurant des instants de passage des aubes de compresseur au niveau d'un capteur (1, 2) et en calculant un signal représentatif de la vitesse de rotation du rotor de compresseur, caractérisé en ce que dans un mode d'apprentissage ou d'adaptation, des écarts, par rapport à un état idéal, propres à chaque aube de compresseur et provoqués par l'état et la position des aubes, sont calculés en mesurant des instants de passage propres à chaque aube de compresseur et que ces écarts sont comparés à des instants de passage idéaux et que dans un mode de travail, les instants de passage propres à chaque aube de compresseur sont mesurés et utilisés pour corriger les écarts calculés et provoqués par l'état et la position des aubes.
  2. Procédé selon la revendication 1, caractérisé en ce que les écarts, propres à chaque aube de compresseur et provoqués par l'état et la position des aubes, des aubes de compresseur sont calculés lors de l'accélération du compresseur selon l'orientation des aubes de compresseur.
  3. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le calcul des écarts propres à chaque aube de compresseur et provoqués par l'état et la position des aubes se produit une fois une certaine vitesse de rotation du rotor atteinte.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que les écarts propres à chaque aube de compresseur et provoqués par l'état et la position des aubes sont mémorisés sous la forme d'un écartement ou d'un facteur prenant la forme d'une durée, d'une trajectoire ou d'un angle.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que les écarts propres à chaque aube de compresseur et provoqués par l'état et la position des aubes sont mémorisés dans un mode d'adaptation, dans un modèle d'adaptation de roue de compresseur (5), et sélectionnés dans un mode de travail.
  6. Dispositif de calcul du point de fonctionnement d'un compresseur, avec au moins un capteur d'aube de compresseur (1), avec au moins un capteur de rotor (2), avec un dispositif de définition de l'heure du système, au moins un champ de mémoire étant intégré, caractérisé en ce qu'au moins un champ de mémoire comporte un nombre de cellules de mémoire (4a, 5a) identique au nombre d'aubes de compresseur à surveiller, un dispositif de synchronisation du champ de mémoire étant prévu avec la rotation de rotor, de sorte que les instants de passage mesurés peuvent être comparés aux instants de passage idéaux et peuvent servir à corriger les écarts propres à chaque aube de compresseur et provoqués par l'état et la position des aubes.
  7. Dispositif de calcul du point de fonctionnement d'un compresseur selon la revendication 6, caractérisé en ce qu'une unité d'analyse (10) est prévue à l'aide de laquelle le point de fonctionnement du compresseur et de façon correspondante l'écartement par rapport à une limite de pompage peut être défini, l'unité d'analyse (10) possédant au moins une entrée via laquelle les instants de passage corrigés sont amenés.
  8. Dispositif de calcul du point de fonctionnement d'un compresseur selon la revendication 6 ou 7, caractérisé en ce qu'un commutateur (8) est prévu pouvant s'enclencher lorsqu'une condition (9) est remplie pour commuter entre un mode d'apprentissage et de travail et un mode d'adaptation.
EP11813656.3A 2010-09-24 2011-09-19 Dispositif et procédé pour l'utilisation en sécurité d'un compresseur à la limite de pompage Not-in-force EP2619461B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010046490A DE102010046490A1 (de) 2010-09-24 2010-09-24 Verfahren zur Regelung des Betriebszustandes von Strömungsarbeitsmaschinen
PCT/DE2011/001739 WO2012095062A1 (fr) 2010-09-24 2011-09-19 Dispositif et procédé pour l'utilisation en sécurité d'un compresseur à la limite de pompage

Publications (2)

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EP2619461A1 EP2619461A1 (fr) 2013-07-31
EP2619461B1 true EP2619461B1 (fr) 2016-06-08

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US (1) US9835162B2 (fr)
EP (1) EP2619461B1 (fr)
DE (1) DE102010046490A1 (fr)
WO (1) WO2012095062A1 (fr)

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CN103217280B (zh) * 2013-03-18 2015-10-28 西安交通大学 航空发动机转子剩余寿命的多变量支持向量机预测方法
CN111524439B (zh) * 2020-04-02 2023-02-03 青岛海尔空调电子有限公司 压缩机模拟工装的控制方法

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US4518917A (en) * 1982-08-31 1985-05-21 Westinghouse Electric Corp. Plural sensor apparatus for monitoring turbine blading with undesired component elimination
US4573358A (en) * 1984-10-22 1986-03-04 Westinghouse Electric Corp. Turbine blade vibration detection apparatus
US4955269A (en) 1988-02-04 1990-09-11 Westinghouse Electric Corp. Turbine blade fatigue monitor
US6010303A (en) 1998-08-05 2000-01-04 United Technologies Corporation Apparatus and method of predicting aerodynamic and aeromechanical instabilities in turbofan engines
NO313926B1 (no) 2000-11-08 2002-12-23 Abb Research Ltd Kompressorstyring
US6532433B2 (en) 2001-04-17 2003-03-11 General Electric Company Method and apparatus for continuous prediction, monitoring and control of compressor health via detection of precursors to rotating stall and surge
US6474935B1 (en) 2001-05-14 2002-11-05 General Electric Company Optical stall precursor sensor apparatus and method for application on axial flow compressors
US20120210694A1 (en) * 2007-04-11 2012-08-23 Holmquist Eric B Turbo machine spool parameter detection
US7775114B2 (en) * 2007-09-26 2010-08-17 Siemens Energy, Inc. Method of on-line turbine blade slope and sensor position verification
DE102008036305B4 (de) 2008-07-31 2016-11-03 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Verfahren zum Betreiben eines Verdichters

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EP2619461A1 (fr) 2013-07-31
US9835162B2 (en) 2017-12-05
WO2012095062A1 (fr) 2012-07-19
DE102010046490A1 (de) 2012-03-29
US20130223981A1 (en) 2013-08-29

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