WO1994003862A1 - Process and device for monitoring and for controlling of a compressor - Google Patents
Process and device for monitoring and for controlling of a compressor Download PDFInfo
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- WO1994003862A1 WO1994003862A1 PCT/US1993/005764 US9305764W WO9403862A1 WO 1994003862 A1 WO1994003862 A1 WO 1994003862A1 US 9305764 W US9305764 W US 9305764W WO 9403862 A1 WO9403862 A1 WO 9403862A1
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- compressor
- peak
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- pressure
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- 238000000034 method Methods 0.000 title claims abstract description 43
- 230000008569 process Effects 0.000 title claims abstract description 38
- 238000012544 monitoring process Methods 0.000 title claims abstract description 22
- 230000008859 change Effects 0.000 claims abstract description 19
- 230000009466 transformation Effects 0.000 claims description 14
- 238000001514 detection method Methods 0.000 claims description 10
- 238000000926 separation method Methods 0.000 description 14
- 230000007423 decrease Effects 0.000 description 12
- 238000011156 evaluation Methods 0.000 description 11
- 230000000694 effects Effects 0.000 description 6
- 239000012530 fluid Substances 0.000 description 6
- 230000006399 behavior Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 230000005284 excitation Effects 0.000 description 4
- 239000003990 capacitor Substances 0.000 description 3
- 238000011109 contamination Methods 0.000 description 3
- 230000003247 decreasing effect Effects 0.000 description 3
- 238000010304 firing Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 238000009499 grossing Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
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- 238000003909 pattern recognition Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
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- 230000000007 visual effect Effects 0.000 description 1
Classifications
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- 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
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06Q—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- G06Q50/00—Systems or methods specially adapted for specific business sectors, e.g. utilities or tourism
Definitions
- the present invention relates to a process and a device for monitoring and controlling of a compressor, said compressor comprising a rotor and a housing, said rotor being rotatably mounted within said housing for rotation about a rotational axis with variable or constant rotational speed, said compressor further comprising at least one compressor stage, each of said at o least one stages comprising a row of rotor blades mounted on said rotor and being arranged one following the other in a circumferential direction with respect to said rotational axis and of a row of stator blades mounted on said housing and being arranged one following the other in a circumferential direction with respect to said rotational axis. 5
- the invention provides for an early detection and reporting of changes in blade-loading for either multi- or single-stage compressors with the possibility of being able to control the compressor in accordance with the reported changes.
- a compressor may be operated as an isolated unit (for example as large pump or 0 process compressor in the chemical or petroleum industry) or in conjunction with a power-turbine engine, as would be the case in a power plant operation.
- the compressor may further be part of a gas turbine used for driving aeroplanes, ships or large vehicles.
- the compressor may be a radial type compressor or preferably an axial type compressor. 5
- Compressors consist of a series of rotating or stationary blade rows in which the combination of a rotor (circular rotating blade row) and a stator (circular stationary blade row) forms one stage. Inside the rotor, kinetic energy 0 is transferred to the gas flow (usually air) by the individual airfoil blades. In the following stator, this energy is manifested as a pressure rise in the gaseous air as a consequence of deceleration of the gaseous air flow. This deceleration of the gaseous air flow is induced as a result of the design of the stator section.
- the pressure ratio (exit pressure/ inlet pressure) of a single stage is limited 5 because of intrinsic aerodynamic factors, so several stages are connected together in many turbo compressors to achieve higher pressure ratios than could be achieved by a single stage.
- the maximum achievable pressure ratio of a turbo compressor is established by the so-called stability limit of the compressor given by the characteristic of the compressor and the gaseous air flowing through the compressor at any time. As the pressure in the compressor increases, the aerodynamic loading on the compressor blades must also increase. At full speed operation of a multistage compressor, the rear stages carry the majority of the aerodynamic load (and attendant stress), and the stability limit is established by the limits inherent in the design of these stages. When operating at lower speeds, the stability limit of the compressor is established by limitations deriving from characteristics related to the front stages of the compressor.
- a compressor stage In the normal stable working range of a compressor stage, axial flow of gaseous air through all of the vane channels between the compressor blades takes place equally and continuously as the air volume is transported through the channels.
- a compressor stage can also operate in a state known as an unstable working range.
- a stall condition can be present in the interaction between the air flow and the airfoil blades which can contribute to substantial variations in the internal pressure profile of the compressor. These pressure variations can, in turn, cause substantial stress to the blades of the compressor.
- this stress can damage the blades if the compressor continues to operate in the unstable working range for any length of time. Operation in the unstable working range is inefficient at best and potentially destructive; this mode of operation should be avoided as much as possible.
- the development of a stall in a stage of the compressor proceeds from the interaction of individual airfoil blades with the gaseous air flowing through the vanes associated with those individual blades.
- the gaseous air fluid flow should be axially continuous through the compressor; however, high blade loads can induce localized disruptions to that continuous flow.
- each blade has an associated flow boundary layer which covers each blade and coheres to the blade.
- the flow boundary layer associated with a rotor blade will rotate as an associated entity of the blade as the blade itself rotates.
- this flow boundary layer melds into an associated flow boundary entity known as the "delve region or wake region" which is characterized by a localized reduction in both pressure and flow velocity.
- this wake region correspondingly will extend until a critical mass or size is achieved; when the wake region on the downstream edge of the blade achieves this critical size, it fractures or fragments into (1) a (new) smaller wake region which is still coherent with the blade and (2) a "flow boundary layer part" which physically separates from the wake region.
- the compressor surge will be accompanied by fluctuations in the continuous overall air flow to the firing chamber in case of a gas turbine; these fluctuations can disrupt the environment in the firing chamber of the turbine in such a manner as to extinguish the "flame" in the firing chamber or (in some rare instances) establish the prerequisite environment for a backfire of the turbine through the compressor.
- a compressor should not be operated under such conditions; at best, operation will be inefficient for those stages wherein stall effects occur.
- Contemporary turbo engines are usually equipped with fuel or energy control systems which measure and output a variety of operating parameters for the overall engine. Included in such control systems are highly accurate pressure sensing devices or systems.
- pressure measuring systems are described in US Patent No. 4,322,977 entitled “Pressure Measuring System", filed May 27, 1980 in the names of Robert C. Shell, et al; US Patent No. 4,434,644 issued March 6, 1984, entitled “Pressure Ratio Measurement System", in the name of Frank J. Antonazzi; US Patent No. 4,422,355 issued December 27, 1983, entitled “Pressure Transducer”; US Patent No. 4,449,409, entitled “Pressure Measurement System With A Constant Settlement Time", in the name of Frank J. Antonazzi; US Patent No.
- US Patent 4,216,672 to Henry et al discloses an apparatus for detecting and indicating the occurrence of a gas turbine engine stall which operated by sensing sudden changes in a selected engine pressure. A visual indication is also provided.
- US Patent 4,055,994 to Roslyng et al discloses a method and a device of detecting the stall condition of an axial flow fan or compressor.
- the method and device measure the pressure difference between the total air pressure acting in a direction opposite to the direction of the revolution of the fan wheel and a reference pressure corresponding to the static pressure at the wall of a duct in substantially the same ra ⁇ ial plane.
- US Patent 4,618,856 to Frank J. Antonazzi discloses a detector for measuring pressure and detecting a pressure surge in the compressor of a turbine engine.
- the detector is incorporated in an analog to a digital pressure measuring system which includes a capacitive sensing capacitor and a o substantially invariable reference capacitor.
- traveling waves are to be identified with rotating stall waves.
- several wall mounted, high- response, static pressure transducers 0 are employed, from which sensor signals first and second Fourier coef ⁇ cients are being derived.
- this direct spectral approach does not directly yield information on compressor stability, since the height of the rotating stall wave peak is a function of both the damping of the system and the amplitude of the excitation.
- a damping model is fitted to the 5 data for an early time estimate of the damping factor.
- the prior art control systems can detect an existing tendency of the compressor towards a stall condition or a surge condition only at a very short time before the actual occurrence of stall or surge. In many 5 cases there is not enough time left after the above detection to take corrective actions for avoiding stall or surge.
- Another object of the invention is to provide a process for monitoring of an axial compressor allowing an online monitoring with fast response, using common calculation techniques for the signal evaluation.
- the process comprising the following steps: a) measuring of pressure fluctuations within at least one of said compressor stages in the region of said housing by means of at least one pressure sensing device, each device delivering a sensor signal, respectively; 5 b) deriving a frequency signal from each of said sensor signals, said frequency signal being indicative of amplitudes of frequency components of said respective sensor signals in a respective frequency interval; c) checking whether each of said frequency signals comprises at least 0 one characteristic peak in a region of a characteristic frequency assigned to one of said compressor stages, respectively and determining at least one peak parameter indicative of the form of said characteristic peaks, said characteristic frequency being defined as the product of said rotational speed and the blade 5 number of the rotor blades of the respective compressor stage; d) generating a status change signal indicative of a change of operational status of said compressor in case of said peak parameter having a value lying beyond a determined value range.
- the characteristic peak is observed. This peak is sensitive to changes in the flow conditions near the maximum available mass flow rate.
- the wake regions of the rotating blades passing the pressure sensing device produce a pressure 5 variation at that sensing device with the characteristic frequency.
- the frequency signal derived from the respective sensor signal shows a respective characteristic peak the form of which is defined by respective peak parameters (peak height, peak width or the like). It has been found that, with increasing load approaching the mentioned maximum mass flow rate for the respective rotor frequency, the characteristic peak becomes more distinct (increasing height and/or increasing width) which may be attributed to the wake regions increasing with load. However, with further increasing load a decreasing characteristic peak is observed.
- the first signs of a compressor full stall leading to a later shut down of a gas turbine can be 5 identified by observing the characteristic peak more than half an hour before the actual shut down.
- the invention provides for an early warning of a stall condition so that appropriate measures to avoid engine stall can be undertaken.
- the frequency signal may easily be derived from the detector signals by using common evaluation techniques, for example fast Fourier transformation (FFT) or fast Hartley transformation (FHT). No model calculations are necessary.
- FFT fast Fourier transformation
- FHT fast Hartley transformation
- the pressure fluctuations due to the wake regions of the rotating blades can best be measured by said pressure sensing device being arranged at said housing between the rotor blades and the stator blades of the respective compressor stage.
- the frequency may be obtained by fast Fourier transformation, the respective electronic transformation units being readily obtainable.
- For the process according to the invention only the time varying part of the absolute pressure is of interest.
- These pressure fluctuations may be directly measured by means of a piezoelectric, a piezo- resistive pressure sensor or especially a piezocapacitive pressure sensor.
- Another less preferred pressure sensing device is a strain gauge pressure sensor.
- the peak parameter indicative of the form of the characteristic peak may be the peak height or the peak width. In both cases, the parameter is easy to determine and easy to be compared with a limit value or with the limits of an allowed region.
- the frequency interval in which the frequency signal has to be evaluated is determined to have a reduced width of less than 4000 Hz.
- a preferred width is 2000 Hz so that the frequency signal has to be determined only between the characteristic frequency minus 1000 Hz and the characteristic frequency plus 1000 Hz.
- the form of the characteristic peak in the mentioned two stages is in opposite direction such that also small changes in the fluid flow status can be detected.
- said peak parameter is defined as a rated sum of individual peak parameters of each of said at least two different characteristic peaks, said individual peak parameters being determined by the peak shape of the respective characteristic peak. In this way, only one parameter is to be observed.
- this rated sum may be defined as the sum of the reciprocal of the peak height of the characteristic peak assigned to the last pressure stage, the reciprocal of the peak height of the characteristic peak assigned to the next to the last pressure stage and the peak height of the characteristic peak assigned to the second to the last pressure stage.
- the frequency signal derived form the sensor signal of a single sensor generally exhibits not only the characteristic peak of the stage in the pressure sensing device as located, but also the characteristic peaks of upstream- located stages due to the movement of the pressure waves through the compressor.
- the amplitude of the characteristic peak decreases with distance to the pressure sensing device so that in some cases it is more advantageous to use a separate pressure sensing device for each stage (and characteristic peak) which is of interest.
- the characteristic peaks of measuring stages may be easily differentiated since, in general, the number of rotor blades and thus the characteristic frequency is different.
- the invention relates further to a process for controlling of an axial compressor, which is based on the above des- cribed process for monitoring of an axial compressor with the additional feature that a status change signal, derived from said process, is used for controlling said axial compressor.
- a status change signal derived from said process, is used for controlling said axial compressor.
- at least one of the stages is in the separation flow pre-stall status (with the compressor being driven at maximum efficiency, that is near the upper limit of its mass flow rate).
- the separation effect decreases and is accompanied by a corresponding increase of the characteristic peak for a specific stage.
- This increase may be used as an input for controlling the axial compressor in a way to increase the compressor load.
- a decrease of the characteristic peak may be used for controlling the axial compressor in a way to decrease the compressor load.
- the characteristic peak in the second to the last stage first increases with a growth of the wake regions and then decreases with the beginning of the flow separation (pre-stall status).
- the monitoring of this tendency may serve as a basis for control of the compressor in the sense of avoiding an overload of the compressor, that is to avoid compressor stall or compressor surge and avoiding to operate the compressor in an uneconomic way too far below the optimum mass flow rate.
- a peak parameter as a rated sum of individual peak parameters of each of said characteristic peaks.
- the invention further relates to a device for monitoring of an axial compressor in accordance with the above- described process for the monitoring of an axial compressor.
- the invention also relates to a device for controlling an axial compressor in accordance with the above mentioned process for controlling an axial processor.
- Figure 1 is a simplified graphic representation of an axial compressor as part of a gas turbine showing the location of dynamic pressure probes
- Figure 2 is a schematic representation of the compressor of Figure 1 illustrating the three final compressor stages at the high- pressure end of the compressor;
- Figure 3 is a block diagram of the dynamic pressure probes connected to an evaluation unit
- Figure 4 illustrates a frequency signal with a characteristic peak
- Figures 5a,b,c show three successive forms of the characteristic peak of Figure 4 obtained by increasing the load starting with Figure 5a;
- Figure 6 is a table for demonstrating the dependency of the form of the characteristic peaks of the three last stages on load. DESCRIPTION OF THE PREFERRED EMBODIMENT
- FIG. 1 and 2 wherein a typical compressor part of a gas turbine engine is depicted (including the present invention).
- the compressor 10 is comprised of a low pressure part 12 and a high pressure part 14.
- Rotor blades 16 of the compressor are mounted on a shaft 18 of a rotor 20.
- Stator blades 22 (guide vanes) are mounted in a housing (casing) 24 of said compressor 10 and are therefore stationary.
- Air enters at an inlet 26 of the gas turbine engine and is transported axially to compressor stages of the compressor under increasing pressure to an outlet 28.
- An axis 30 of said compressor is defined as the axis of rotation of the rotor 20.
- the present invention may also be employed in connection with a radial type compressor.
- Each of the mentioned compressor stages consists of two rows of blades with equal blade number, namely a row of rotor blades 16 and a row of stator blades 22.
- the blades of each row are arranged one following the other in a circumferential direction with respect to said axis 30.
- Figure 2 shows the last stage of the compressor at its outlet 28 (high pressure axial end of the compressor) with rotor blades 16a and stator blades 22a.
- the second- last and the third last compressor stages are depicted with rotor blades 16b and stator blades 22b and rotor blades 16c and stator blades 22c, respectively.
- the compressor 10 comprises an accessory gear box 30 enabling the adjustment of orientation of blades in order to change the load of the respective stages.
- Figure 1 further shows a bleed air collector 31 between the low pressure part 12 and the high pressure part 14.
- the compressor used in connection with the invention, is of common construction,
- pressure sensing devices in form of dynamic pressure sensors, are mounted in the axial gaps between rotor blades 16 and stator blades 22 of stages of the high pressure part 14 of compressor 10.
- these dynamic pressure sensors are mounted in the last three stages nearest the outlet 28 of the compressor 10.
- the dynamic pressure sensor associated to the last stage is indicated with 32a and the following dynamic pressure sensors (in the downstream direction of the compressor 10) with 32b and 32c.
- each sensor 32 measures the pressure fluctuations of the respective stage, occurring at the inner circumferential face 34. Since the respective sensor 32 is located in the region of the axial gap between the rows of rotor blades 16 and stator blades 22,
- each sensor is sensitive for the so called wake regions (Dellenregionen) being developed by the axial air flow at the downstream edge 38 of each rotary blade.
- These wake regions rotating with the respective rotary blade 16 are regions with lower density and flow velocity and with varying flow direction.
- an elongated adaptor (not shown) which, with one of its ends, is mounted to the opening 40 and, at its other end, carries the sensor.
- the illustrated location of the sensor 32 at the high- pressure axial end of 3 5 the high pressure part 14 of the compressor 10 is preferred for a compressor operating at high speed (design speed).
- pressure sensors may be mounted in the axial gaps between rotor- and stator blades at the other axial end of the high pressure part in Figure 3, with a fourth sensor 32d.
- the minimum is one sensor.
- Dynamic pressure sensors preferably piezoelectric pressure sensors, are used because of their reliability, high temperature operability and sensitivity for high frequency pressure fluctuations up to 20 000 Hz (for example Kistler Pressure Sensor, Type 6031).
- each sensor is provided with an amplifier 42, amplifying the respective sensor signal.
- These amplifiers 42 are connected o via lines 44, 46 to an evaluation unit 48.
- the evaluation unit 48 contains several Fast Fourier Transformer (FFT) analyzers 50 which respectively receive signals from the mentioned amplifier 42a-42d through analogue digital converters 5 ADC (or multi- plexers) 52a-d which are connected between each of the respective amplifiers (AMP) 42a-d and FFT analyzers 50a-d.
- FFT Fast Fourier Transformer
- the signals from the FFT analyzers 50a-d are transmitted to a computer unit 54 comprising several subunits, amongst them a stall detector 56, the 0 functioning of which is described above.
- a stall detector 56 further detectors for the status of the compressor may be installed, for example a contamination detector 58 for detecting fouling of the blades of the low pressure part 12 of compressor 10 and a blade excitation detector 60 for detecting pressure fluctuations which are able to induce high amplitude blade vibrations, 5 which vibrations may damage the compressor.
- the stall detection according to the present invention may also be performed independently of contamination detection and blade excitation detection.
- a unit 62 for signal preparation may be connected between the FFT analyzers 50a-d and the detectors 56, 58, 60.
- the unit 62 contains filter algorythms for handling and smoothing raw digital data as received from the FFT analyzers.
- a control program periodically switches the sensor signals of each of the individual dynamic pressure sensors 42a-d via 5 the ADC-52a-d to the FFT analyzers 50a-d.
- the resulting frequency signals from the FFT analyzers, after smoothing via unit 62, are forwarded to said detectors 56, 58, 60 for comparison with respective reference patterns. If the comparison analysis indicates deviations beyond a predetermined allowable
- a respective compressor control unit 66 connected to evaluation unit 48, is also shown in Figure 3 serving for controlling the compressor 10.
- the compressor control unit 66 takes measures to avoid the risk of damaging compressor 10, for example by lowering the load (adjustment of orientation of blades by means of gear box 30 or by reducing the fuel injection rate of the combustion section to reduce the rotational speed). In some instances, the compressor control unit 66 may stop the compressor 10.
- the smoothed frequency signal is evaluated, said frequency signal being indicative of the amplitudes of frequency components of the respective sensor signal in a respective frequency interval.
- the stall detector 56 examines the frequency signals in a specific frequency region around a specific frequency, the so called characteristic frequency c. said frequency c being defined as the product of the present rotational speed n of rotor 20 and the blade number z of the rotor blades of the respective compressor stage:
- the frequency interval around c m ⁇ y have a width of less than 4000 Hz and preferably is 2000 Hz so that the upper limit L may be c + 1000 Hz and the lower limit L may be c - 1000 Hz (see Figure 5).
- the blade number of rotor blades equals the blade number of stator blades within the same stage.
- the frequency signal shows a respective characteristic peak 70 at c- It has been found, that the form of this characteristic peak is varying in a characteristic manner, if the load of the respective stage is increased starting from a normal stage load with peak 70a shown in Figure 5A. In a first phase, the peak becomes more characteristic as shown in Figure 5B (peak 70b). Both the height and the width of the characteristic peak increase as the load increases. This behavior is due to an increase of the wake regions (Dellenregionen) of the rotating blades, producing more characteristic pressure variations with the characteristic frequency at the location of the respective sensor 32.
- This separation phase may be called separated flow pre-stall phase since the separation of boundary layers and the collection of separated flow regions at the inner circumferential face 34 does not remarkably reduce the pressure ratio of the respective stage. Stall effects 0 (rotating stall) with microscopic areas (bubbles) with blockage of flow in most cases will be observed when the characteristic peak has vanished ( Figure 5c).
- the observation of the characteristic peak therefore is a sensitive tool for monitoring and/or controlling of a compressor.
- the characteristic peaks of the last three stages of the high pressure part 14 are observed.
- the last stage is the 13th stage so that the respective peak parameter (especially peak height) is called pl3. Consequently, the other two peak parameters are called pl2 and pll.
- the table in Figure 6 indicates the behaviors of the peak parameters pl3, pl2 and pll with increasing load, wherein the upwardly oriented arrows indicate increasing and the downwardly oriented arrows indicate decreasing load and peak height, respectively with the number of arrows indicating the respective strength.
- the column at the utmost right is called "stall level", said stall level (general peak parameter) being expressed by the following formula:
- the characteristic peak of stage 13 is unchanged (form according to Fig. 5d); the characteristic peak of stage 12 develops from Fig. 5b to 5c and the characteristic peak of stage 11 develops from Fig. 5a to 5b.
- the peak parameter more or less sharply increases as shown in Figure 6, right hand side.
- the peak parameter SL may also be used for closed-loop- control of the compressor. If the measured peak parameter SL leaves the allowed region between the lower threshold TL and the upper threshold TU, the compressor 0 control unit receives the respective control signal in order to change one or more operational parameters of the compressor to change the load of the compressor into the desired direction.
- a B C PP + _____ + . — (3) pl3 pl2 pll 5
- coefficient C is chosen to be larger than coefficient B and coefficient B is chosen to be larger than coefficient A.
Abstract
Description
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Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP93916564A EP0654161B1 (en) | 1992-08-10 | 1993-06-16 | Process and device for monitoring and for controlling of a compressor |
JP6505281A JPH08503757A (en) | 1992-08-10 | 1993-06-16 | Method and apparatus for monitoring and controlling a compressor |
AU46372/93A AU4637293A (en) | 1992-08-10 | 1993-06-16 | Process and device for monitoring and for controlling of a compressor |
DE69325375T DE69325375T2 (en) | 1992-08-10 | 1993-06-16 | METHOD FOR MONITORING AND CONTROLLING A COMPRESSOR AND DEVICE THEREFOR. |
KR1019950700570A KR100296671B1 (en) | 1992-08-10 | 1993-06-16 | Apparatus and processes for control and monitoring of compressors |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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EP92113586.9 | 1992-08-10 | ||
EP92113586 | 1992-08-10 |
Publications (1)
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WO1994003862A1 true WO1994003862A1 (en) | 1994-02-17 |
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PCT/US1993/005764 WO1994003862A1 (en) | 1992-08-10 | 1993-06-16 | Process and device for monitoring and for controlling of a compressor |
Country Status (11)
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US (1) | US5594665A (en) |
EP (1) | EP0654161B1 (en) |
JP (1) | JPH08503757A (en) |
KR (1) | KR100296671B1 (en) |
AT (1) | ATE181402T1 (en) |
AU (1) | AU4637293A (en) |
CA (1) | CA2141544A1 (en) |
DE (1) | DE69325375T2 (en) |
ES (1) | ES2132243T3 (en) |
MX (1) | MX9304823A (en) |
WO (1) | WO1994003862A1 (en) |
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Also Published As
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KR100296671B1 (en) | 2001-10-24 |
KR950703180A (en) | 1995-08-23 |
JPH08503757A (en) | 1996-04-23 |
EP0654161B1 (en) | 1999-06-16 |
AU4637293A (en) | 1994-03-03 |
EP0654161A1 (en) | 1995-05-24 |
US5594665A (en) | 1997-01-14 |
EP0654161A4 (en) | 1998-05-20 |
ES2132243T3 (en) | 1999-08-16 |
CA2141544A1 (en) | 1994-02-17 |
DE69325375T2 (en) | 1999-10-21 |
DE69325375D1 (en) | 1999-07-22 |
ATE181402T1 (en) | 1999-07-15 |
MX9304823A (en) | 1994-05-31 |
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