EP1847715A1 - Procédé de fonctionnement d' un turbocompresseur et turbocompresseur - Google Patents

Procédé de fonctionnement d' un turbocompresseur et turbocompresseur Download PDF

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Publication number
EP1847715A1
EP1847715A1 EP06008134A EP06008134A EP1847715A1 EP 1847715 A1 EP1847715 A1 EP 1847715A1 EP 06008134 A EP06008134 A EP 06008134A EP 06008134 A EP06008134 A EP 06008134A EP 1847715 A1 EP1847715 A1 EP 1847715A1
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EP
European Patent Office
Prior art keywords
turbocompressor
surge limit
operating
limit curve
compressor
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.)
Withdrawn
Application number
EP06008134A
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German (de)
English (en)
Inventor
Thorsten Dr. Engler
Bernward Dr. Mertens
Stefan Dr. Mählmann
Uwe Dr. Sieber
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.)
Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP06008134A priority Critical patent/EP1847715A1/fr
Publication of EP1847715A1 publication Critical patent/EP1847715A1/fr
Withdrawn legal-status Critical Current

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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
    • F04D27/02—Surge control

Definitions

  • the invention relates to a method for operating a turbocompressor, in which an operating point is specified, which lies below the pumping limit represented by a surge limit curve in an operating diagram assigned to the turbocompressor. It also relates to a turbocompressor.
  • the operating behavior of a turbocompressor can be characterized by its operating diagram.
  • such an operating diagram is represented in a Cartesian coordinate system, wherein along the abscissa (x-axis) z.
  • B the speed of the compressor or a derived characteristic and along the ordinate (y-axis) z.
  • the x-coordinate may also denote the volume flow through the compressor or a similar characteristic.
  • a family of relevant characteristics of the turbocompressor is usually entered, which form a map in its entirety, z. As lines of constant efficiency or constant torque or the like.
  • the compressor-specific characteristic curves can be determined, for example, experimentally in the context of bench tests or also on the basis of theoretical considerations or numerical simulations.
  • the current operating state or operating point of the compressor is represented by a dot in the operating diagram.
  • An operating limit of the turbocompressor to avoid exceeding it in any case is, is the so-called surge line.
  • surge is meant the phenomenon that occurs when, for example, at a certain pressure ratio, a corresponding minimum volume flow is undershot. The flow breaks down to the pressure side of the compressor; There is a return flow through the compressor, as a result, the inlet pressure increases again and the outlet pressure decreases until the pumping limit is reached again.
  • Such a pumping operation characterized by cyclically conveying and returning the compressed medium, is usually accompanied by strong, low-frequency vibrations (with a typical frequency of 0.5 to 2 Hz), pressure surges and a rapid rise in the temperature of the compressor. Possible consequences are bearing, rubbing, wheel or blade damage with the associated operational failures.
  • the immediate introduction of active pump suppression measures at the occurrence of the first surge such as the opening of inflation or Umblaseventilen
  • the immediate hazard potential can be significantly limited by such pumping operations, but in this case, a temporary deviation from the nominal operating values and thus a temporary
  • significant reduction in performance inevitable which in particular the trouble-free availability of a coupled to the turbocompressor or the associated gas turbine generator is limited.
  • the stability of the power supply may be impaired when the electrical current generated in the generator is fed into a network. Therefore, there is a desire to avoid exceeding the surge limit in a turbocompressor by "intelligent" control of the operating behavior from the outset.
  • the surge limit for different operating conditions is represented by a surge limit curve, which makes the characteristic field stable and unstable Area separates.
  • the exact position and the exact course of the surge limit curve for the various Vorleitschaufelzinen can theoretically be determined only with limited accuracy; An experimental determination is comparatively complex and is not available in many cases.
  • a test copy is usually taken out of a series of similar turbocompressors and measured in a measuring stand.
  • comparatively small tolerances in the production of the series can already lead to noticeable shifts in the surge limit curve.
  • the position of the surge line in operation changes depending on the age of the turbocompressor and the cleanliness of the compressor blade as well as other, sometimes difficult to detect or quantifiable influencing factors.
  • the position of the surge limit curve in the operating diagram is only adjusted if this appears reasonable as a result of new operating experience or through improved calculation methods. Therefore, the operating point of the turbocompressor must be set in principle taking into account a sufficient with sufficient safety, but also with a high probability unnecessarily large selected distance to the actual surge limit. As a result, the operating range of the turbocompressor or the gas turbine is unnecessarily limited, especially in the map areas with principally high power output by choosing a correspondingly large safety distance high losses occur.
  • the invention is therefore based on the object to provide a method for operating a turbocompressor, with high operational safety and avoiding pumping a particularly great flexibility in terms of the choice of operating point and depending on the operational boundary conditions a particularly high operating efficiency and / or ensures a particularly high power output.
  • This object is achieved in that the surge limit curve is updated during operation of the turbocompressor based on measured values determined during operation on the turbocompressor.
  • the invention is based on the consideration that a particularly large operating range of a turbocompressor and thus a particularly favorable operating conditions under all conceivable operating conditions can be realized if only a comparatively small safety distance to the surge limit must be specified and maintained.
  • the actual surge limit curve in the underlying operating diagram should be known with the highest possible accuracy.
  • any power reserves exhaustive operation of the turbocompressor should be considered that this actual, à priori, however, only approximately known surge limit is not static size, but in the course of operation under the influence of various factors, such as life, number of Operating hours, degree of soiling, corrosion, increased bearing clearance, etc. vary, in other words can shift or even change shape.
  • the time intervals relevant for the updating of the surge limit curve can be determined in advance on the basis of empirical values. They can also be irregular and be adjusted as needed during operation. Advantageously, however, there is a continuous acquisition of the measured values and updating of the surge limit curve in periodic time steps, e.g. daily at extreme ambient temperatures or event driven, e.g. at low line frequencies / speeds. Although shorter time intervals require an increased processing effort for the recorded data, but are useful to take into account the influence of unsteady processes, such as the startup or shutdown of the turbocompressor or load changes, adequately.
  • the current value of a state parameter which represents at least approximately a measure of the distance between the respective operating state and the actual surge limit is advantageously determined, the current surge limit curve being determined on the basis of this current value of the state parameter.
  • the current surge limit curve being determined on the basis of this current value of the state parameter.
  • a set of possible surge limit curves, along which the value of the state parameter is always constant the one selected as the current surge limit curve, which is to be assigned to the actual surge margin, which results from the current value of the state parameter.
  • the measured value of the state parameter itself may possibly be faulty, it is expedient to record a plurality of measured values simultaneously or at least in a timely manner and B. to form an average value from these measured values.
  • the measured value from the recorded series can be used to select the surge limit curve, which offers the largest "safety margins".
  • the current surge limit curve can, for example, by parallel displacement of the original surge limit curve in the operating diagram, optionally using the method of least squares or the like and adapted to the current measured values of the stall parameter.
  • time-dependent pressure fluctuations in the flow channel of the turbocompressor are included in the determination or calculation of the current value of the state parameter. It proves to be particularly advantageous in this case to measure the pressure fluctuation in the gap region between the rotor blades of a blade row, in particular the first blade row seen in the flow direction of the flow medium to be compressed, and the compressor housing delimiting the flow channel.
  • a parameter characteristic of the angle of incidence of the turbine blades of the turbocompressor and / or a pressure ratio between suction-side and outlet-side pressure and / or a characteristic variable characteristic of the rotational speed of the turbocompressor are advantageously determined by measurement.
  • a value of the state parameter determined in such a way from comparatively easily accessible measured variables is suitable for a particularly reliable evaluation of the surge margin and for a reliable prediction of pumping states.
  • an initial surge limit curve based on theoretical considerations, in particular on model calculations and numerical simulations, and / or comparative measurements on other machines of the same or similar type is advantageously used, for example by estimating the value of the state parameter as a rough estimate and from this set of theoretically possible surge limit curves the corresponding one is selected.
  • an impending or actual exceeding of the surge limit is counteracted by reducing the fuel mass flow fed to a drive unit driving the compressor and / or changing the angle of attack of the pilot vanes.
  • a drive unit driving the compressor and / or changing the angle of attack of the pilot vanes.
  • turbocompressor preferably has a monitoring and control device, wherein the monitoring and control device comprises a number of measuring sensors, the data side with a for determining the current operating condition and for the determination and / or calibration of a current surge limit curve configured evaluation unit are connected. That is, the operating state the turbocompressor is continuously monitored as to whether it approaches the dynamically updated surge limit curve in the operating diagram, so that a corresponding warning signal is output when a predetermined, preferably freely selectable minimum distance is undershot.
  • the monitoring and control device advantageously comprises a control unit which accesses the data input side to the current surge limit curve determined in the evaluation unit and which is connected to a number of actuators acting on relevant manipulated variables of the turbocompressor.
  • the control unit is configured in such a way that the operating point of the turbocompressor always remains below the surge limit represented by the current surge limit curve due to a corresponding time-dependent actuation of the actuators.
  • the operator via a control panel or the like and the fully automatic control override or “override” set down manual control commands, and advantageously only those that increase the distance of the operating point to the current surge limit curve.
  • the turbocompressor comprises at least one pressure sensor designed to detect temporal pressure fluctuations in the flow channel, which is preferably arranged in the region of the radial gap assigned to the first rotor blade row.
  • the pressure fluctuations of interest here which are constant at a constant speed of the turbocompressor, result from the fact that the rotor blades, due to the rotation of the compressor shaft, move past the respective measurement point of the compressor housing at a comparatively high speed.
  • the respective pressure sensor should have a comparatively high sampling rate of typically at least 50 kHz.
  • the turbocompressor further comprises a device for regulating the fuel mass flow, which drives a turbo compressor Drive unit is supplied, and / or an adjusting device for the pilot vanes of the turbocompressor.
  • the turbocompressor is advantageously a gas turbine compressor, so that the drive unit is the turbine unit of the gas turbine and the controllable fuel mass flow is the fuel mass flow supplied to the burners of the associated combustion chamber.
  • the advantages achieved by the invention are in particular that a particularly reliable and safe operation of the turbocompressor is made possible by the taking place during the operation of the turbocompressor dynamic adaptation or updating of the surge limit curve based on determined by measurement, characteristic state parameters, at the same time each stable Operating area can be fully utilized as possible without, as previously available power reserves unused by unnecessarily large selected safety distances to "give away".
  • the predictions from simplified but easy-to-handle models can be adapted or calibrated to reality; on the other hand, an aging-related or contamination-related shift of the surge limit curve is automatically recorded and can be adequately taken into account in the control or regulation of the turbocompressor.
  • the turbocompressor 2 shown in FIG. 1 serves to compress a flow medium M, in this case air.
  • the configured as axial compressor turbocompressor 2 includes a number of each combined into blade rows, each annularly arranged on a rotatable compressor shaft 4 blades 6.
  • kinetic energy is transferred to the flow medium M in reversal of the principle of a turbine, whereby this within the flow channel 10 bounded inwards through the compressor shaft 4 and outwards through the compressor housing 8 is conveyed in the direction of the compressor axis 12 from the inlet 14 to the outlet 16 and is thereby compressed as a result of the cross section of the flow channel 10 decreasing steadily towards the outlet side.
  • the flow rate at the outlet 16 is less than at the inlet 14.
  • the inlet side is also referred to as suction side.
  • fixed guide vanes 18, each attached to the compressor housing 8, each grouped into rows of guide vanes, are provided, so that rows of rotor blades and guide vanes alternate in the flow direction 20 of the flow medium.
  • the guide vanes 18 projecting into the flow channel 10 serve to guide the flow of the flow medium M.
  • a unit formed from a row of blades and a row of guide blades directly following it is also referred to as a compressor stage.
  • the turbocompressor 2 is a gas turbine compressor part of a gas turbine and is not shown here Turbine unit driven, wherein the compressor shaft 4 is rigidly connected to the turbine shaft.
  • the air compressed in the turbocompressor 2 is supplied together with a fossil fuel to the burners arranged in a combustion chamber of the gas turbine, wherein a hot and under high pressure working medium is formed by combustion of the fuel-air mixture thus generated.
  • the working medium drives the turbine shaft and thus also the compressor shaft 4 connected to it via a momentum transfer to the turbine rotor blades arranged rotatingly on the turbine shaft.
  • a generator which is likewise not shown here, is usually coupled to generate electrical current.
  • the guide vanes 18 of the first row of guide vanes seen in the direction of flow 20, the so-called pilot vanes 22, are adjustable in their angle of attack relative to a reference plane spanned by the compressor axis 12 and a radial beam perpendicular thereto.
  • adjusting device 24 is provided to adjust the Vorleitschaufeln 22 a in Figure 1 only schematically indicated adjusting device 24 is provided. With increasing angle of attack, the free cross-section decreases at this point of the flow channel 10.
  • n * of the compressor shaft 4 the amount of air sucked per unit time and thus the mass flow through the turbocompressor 2 increases with increasing angle of the Vorleitschaufeln 22, hereinafter with LSV designated, from.
  • n * n n 0 ⁇ R ⁇ T R 0 ⁇ T 0 to the rotational speed n, the air temperature T and the gas constant R at nominal conditions, characterized by the index 0, is related.
  • pilot vanes 22 may also be an adjustment of the blades of farther downstream vane rows, e.g. the rows 1 to 3, be provided.
  • the pumping limit characterized by the value of LSV max is a function of the (reduced) speed n *.
  • the surge limit is therefore represented by a curved surge limit curve 28.
  • the stable operating points of the turbocompressor 2 above the unstable, where pumping phenomena occur.
  • the pressure ratio ⁇ of the turbocompressor 2 defined as the quotient of the outlet-side pressure to the inlet of the flow medium M, could also be plotted on the y-axis.
  • a state parameter (designated P stall or P i ) is determined, which represents at least approximately a measure of the distance of the respective operating state from the actual surge line.
  • a high-resolution pressure sensor 32 is arranged on the outside of the compressor housing 8 facing the flow channel 10 in such a way that it maps the time profile of the pressure in the radial gap 34 between the first impeller and the rotor blade tips 36 first blade row and the compressor housing 8 measures.
  • p i is measured during the "flyby" of the moving blades 6 at a constant sampling rate.
  • K and K are setting factors.
  • the stall parameter P stall thus defined represents at least in principle an absolute measure of the instantaneous surge margin, although in practice usually generalizations of this concept based on the determination of a sonic / pressure spectrum with correspondingly more complicated Formulas and calculation methods are used.
  • P stall instead of the designation P stall , the term P i is also used, the index i indicating that generalizations to more than one such parameter are also common.
  • the lines P i const. in principle, lines constant surge margin, which can be supported by tests and possibly supported by model calculations in the operating diagram 26 of the turbocompressor 2 and register. This is shown schematically in FIG.
  • the currently valid value of the state parameter P i which, as described above, can be calculated on the basis of the continuously measured quantities p i , LSV, n *, ⁇ and possibly even further variables, then applies the current control of the turbocompressor 2 defining surge limit curve 28.
  • Pump limit curve 28 also includes a control unit 42.
  • the control unit 42 acts via its associated actuators on the adjusting device 24 for the pilot vanes 22, that is on the angle LSV, and on the fuel mass flow N for the gas turbine regulating fuel regulating device. The regulation takes place such that the operating point 30 of the turbocompressor 2 always remains below the surge limit represented by the current surge limit curve 28.
  • the trend associated with any changes in position of both the operating point 30 and the surge limit curve 28, ie in particular the rate of change of both variables, is determined and evaluated.
  • a predetermined minimum pumping limit distance is undershot counteracting control commands for controlling LSV and N are then given, the strength of which depends on the strength of the trend and thus on the "risk of collision" between the operating point 30 and the surge limit curve 28.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
EP06008134A 2006-04-19 2006-04-19 Procédé de fonctionnement d' un turbocompresseur et turbocompresseur Withdrawn EP1847715A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06008134A EP1847715A1 (fr) 2006-04-19 2006-04-19 Procédé de fonctionnement d' un turbocompresseur et turbocompresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06008134A EP1847715A1 (fr) 2006-04-19 2006-04-19 Procédé de fonctionnement d' un turbocompresseur et turbocompresseur

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EP1847715A1 true EP1847715A1 (fr) 2007-10-24

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011012211A1 (de) * 2011-02-23 2012-08-23 Wilo Se Leistungsoptimiertes Betreiben einer elektromotorisch angetriebenen Pumpe durch Mitkopplung
CN112446159A (zh) * 2020-12-16 2021-03-05 浙江理工大学 基于参数测量法的海水叶片泵状态识别方法
CN112879166A (zh) * 2017-05-25 2021-06-01 通用电气阿维奥有限责任公司 控制涡轮发动机的压缩机

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2102595A (en) * 1981-07-24 1983-02-02 Gen Electric Method and apparatus for promoting a surge condition in a stalled gas turbine engine
GB2316772A (en) * 1993-08-16 1998-03-04 American Standard Inc Control system method for a centrifugal compressor
EP1256726A1 (fr) * 2001-04-17 2002-11-13 General Electric Company Procédé et appareil de prediction continu, de surveillance et contrôle de stabilité d'un compresseur via détection des précurseurs de décollement tournat et du pompage

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2102595A (en) * 1981-07-24 1983-02-02 Gen Electric Method and apparatus for promoting a surge condition in a stalled gas turbine engine
GB2316772A (en) * 1993-08-16 1998-03-04 American Standard Inc Control system method for a centrifugal compressor
EP1256726A1 (fr) * 2001-04-17 2002-11-13 General Electric Company Procédé et appareil de prediction continu, de surveillance et contrôle de stabilité d'un compresseur via détection des précurseurs de décollement tournat et du pompage

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011012211A1 (de) * 2011-02-23 2012-08-23 Wilo Se Leistungsoptimiertes Betreiben einer elektromotorisch angetriebenen Pumpe durch Mitkopplung
DE102011012211A8 (de) * 2011-02-23 2012-12-27 Wilo Se Leistungsoptimiertes Betreiben einer elektromotorisch angetriebenen Pumpe durch Mitkopplung
CN112879166A (zh) * 2017-05-25 2021-06-01 通用电气阿维奥有限责任公司 控制涡轮发动机的压缩机
CN112446159A (zh) * 2020-12-16 2021-03-05 浙江理工大学 基于参数测量法的海水叶片泵状态识别方法
CN112446159B (zh) * 2020-12-16 2024-02-02 浙江理工大学 基于参数测量法的海水叶片泵状态识别方法

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