EP3589843B1 - Verfahren und vorrichtung zum bestimmen eines indikators für eine vorhersage einer instabilität in einem verdichter sowie verwendung - Google Patents

Verfahren und vorrichtung zum bestimmen eines indikators für eine vorhersage einer instabilität in einem verdichter sowie verwendung Download PDF

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Publication number
EP3589843B1
EP3589843B1 EP18713121.4A EP18713121A EP3589843B1 EP 3589843 B1 EP3589843 B1 EP 3589843B1 EP 18713121 A EP18713121 A EP 18713121A EP 3589843 B1 EP3589843 B1 EP 3589843B1
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EP
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Prior art keywords
compressor
operating states
flow
indicator
instability
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EP18713121.4A
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German (de)
English (en)
French (fr)
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EP3589843A1 (de
Inventor
Mario Eck
Dieter Peitsch
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Technische Universitaet Berlin
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Technische Universitaet Berlin
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Priority to PL18713121T priority Critical patent/PL3589843T3/pl
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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
    • F04D27/0261—Surge control by varying driving speed
    • 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
    • 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

Definitions

  • the invention relates to a method and a device for determining an indicator for predicting an instability in a compressor, and to the use.
  • Thermal turbo machines can be designed as axial or radial compressors.
  • axial compressors represent a central component in aircraft engines.
  • the operating behavior of the compressor with this or other designs is difficult to predict.
  • the performance data of newly developed compressors are measured on a test bench and then entered in a map.
  • the so-called surge limit is an important part of the map. If the surge limit is exceeded, instabilities arise in the compressor, which represent an extremely high aerodynamic load on the compressor and can cause considerable structural damage.
  • knowledge of the surge limit is of great importance.
  • the surge limit can only be identified on the test bench if it has already been exceeded. For this reason, costly total failures of the tested compressors are accepted in the prior art when determining the surge limit.
  • a method and an apparatus for predicting the instability of an axial compressor are in the document EP 2 469 098 A1 disclosed.
  • a method for representing the surge line is in the document U.S. 5,908,462 A disclosed.
  • document DE 101 52 026 A1 discloses a method for determining a surge limit warning in a turbo compressor or a warning in the event of blade damage.
  • document US 2009/0312930 A1 discloses a device for stall prediction of an axial compressor having a rotor made of a plurality of rotor blades and a cylindrical housing which covers the outer circumference of the rotor. Furthermore, the device comprises pressure sensors, a unit for calculating key figures for evaluation the stall risk based on time series data from the pressure sensors and a signal processor for stall prediction based on the key figures.
  • the document also belongs to the relevant state of the art JP H02 286899 A .
  • the object of the invention is to specify a method and a device for determining an indicator for predicting instability in a compressor designed as an axial or radial compressor, which reliably allow early warning of the possible occurrence of a compressor instability.
  • a method for determining an indicator for a prediction of instability is created in a compressor which is designed as an axial or radial compressor.
  • a compressor designed as an axial or radial compressor is operated in operating states which differ in terms of different values of a parameter for a flow mass flow of the compressor, whereby the operating states are passed through with decreasing flow mass flows. Values of the characteristic value for the nut mass flow for the operating states are determined.
  • time-resolved pressure measurement values are recorded by means of a pressure sensor, the pressure sensor being arranged in a housing of the compressor upstream adjacent to an entry level of a rotor stage.
  • the skew is determined for the operating states.
  • An indicator for an instability of the compressor (instability indicator) is determined if a change in sign of the curve increase is determined for a curve profile of the skew over the parameter for the mass flow rate for the operating states.
  • the method is used when determining an operating limit of a compressor designed as an axial or radial compressor on a test bench or when monitoring an engine with an axial or radial compressor Executed compressor provided in operation, in particular when used in an aircraft engine or in a turbocharger.
  • a device for determining an indicator for a prediction of instability in a compressor which is designed as an axial or radial compressor.
  • the device has a compressor which is designed as an axial or radial compressor.
  • a measuring device is provided which is set up to determine values of a characteristic value for a flow mass flow of the compressor in operating states when the compressor is operated, the operating states differing in terms of different values of the characteristic variable for the flow mass flow of the compressor and in this case the operating states run through with decreasing flow mass flows become; and to detect time-resolved pressure measurement values when passing through the operating states by means of a pressure sensor which is arranged in a housing of the compressor upstream adjacent to an entry plane of a rotor stage.
  • the device has an evaluation device which is set up to determine the skewness for the operating states and to determine an indicator for instability of the compressor if a change in sign of the curve increase is determined for a curve profile of the skewness over the parameter for the mass flow rate for the operating states .
  • an indicator can be determined in a reliable manner for thermal turbo working machines, that is to say axial or radial compressors, which indicates the possible future occurrence of an instability of the compressor.
  • measures can be taken to avoid destruction of the compressor when the surge limit is exceeded, be it on a test bench to determine an operating limit of the compressor and / or when using and operating such a compressor, for example in a turbocharger or a Aircraft engine.
  • the compressor When running through the various operating states, the compressor is throttled, i.e. operating states are set one after the other for which the flow mass flow decreases bit by bit.
  • the operation of the compressor when measuring the characteristic value for the flow rate mass flow and the measured pressure values can be carried out at one and the same speed for the rotor or rotors (rotor stages) of the compressor. Alternatively, it can be provided when Determine the indicator of the instability of the compressor using measurements at different speeds.
  • the parameter "skewness" is the third statistical moment, for the determination of which the time-resolved pressure measurement values are used. Methods for determining the skewness are known as such.
  • the acquisition of the time-resolved pressure measurement values can be used to measure the steady-state pressure.
  • the pressure sensor can be arranged in the housing of the compressor on an inner wall of the housing.
  • the pressure sensor can be arranged flush with the surface in the housing of the compressor on the inner wall of the housing of the compressor.
  • a plurality of pressure sensors can also be provided, which are arranged in the housing of the compressor upstream adjacent to the entry plane of the rotor stage, for example spaced circumferentially. Provision can be made to use the time-resolved pressure measurement values acquired with the plurality of pressure sensors to determine the indicator for the instability of the compressor.
  • the pressure sensor can be arranged in the housing of the compressor above blade tips of blades of the rotor stage.
  • pressure fluctuations can be recorded in a time-resolved manner by means of the pressure sensor.
  • the sampling of the time-resolved pressure measurement values can take place at a frequency between approximately and 20 kHz and approximately 100 kHz, so that in the event that pressure fluctuations are measured in a time-resolved manner, they are determined with a frequency of approximately 10 kHz to approximately 50 kHz .
  • the change in sign of the curve rise can indicate that a local maximum has been passed. If the curve of the skewness over the characteristic variable for the flow mass flow runs through from larger to smaller values of the characteristic variable for the flow mass flow, the flow of the local maximum means that the curve rise changes from negative values to positive values.
  • Another indicator for the instability of the compressor can be determined if a further change in sign of the curve increase is determined for the curve shape of the skew over the parameter for the flow mass flow towards lower flow mass flows.
  • the multiple sign changes can be determined as separate indicators of different quality for the possible or expected occurrence of an instability of the compressor, for example with regard to a different distance to the surge limit, which is based on the difference between the value of the parameter for the flow mass flow for the surge limit on the one hand and the value when the sign change on the other hand is determinable.
  • the change in sign of the curve rise can indicate that a local minimum has been passed.
  • the flow coefficient and / or the reduced mass flow for the operating states can be determined as a parameter for the flow mass flow.
  • a warning signal can be generated as an early warning of compressor instability and output via an output device. If the indicator and / or the further indicator are determined from the curve progression, a warning signal assigned in each case indicates to the user optically and / or acoustically that there is a risk of compressor instability in the event of a further reduction in the mass flow rate.
  • the compressor can be operated in operating states that are below a surge limit of the compressor. Provision is made for the throttling of the compressor and the passage through the different operating states caused by this to be interrupted before the surge limit is reached, whereupon instabilities actually occur.
  • damage to the compressor can be avoided, which is why multiple tests are possible.
  • the indicator is determined for a compressor that is in operation or in use, for example as an axial compressor in an aircraft engine, possible damage is avoided, whereby the service life can be extended.
  • the indicator and / or the further indicator indicate a possible occurrence of an instability of the compressor before this actually occurs.
  • Fig. 1 shows a schematic representation of an arrangement for a test stand for measuring or determining an axial compressor.
  • a rotor 2 with blades 3 and a drive device 4 for rotating the rotor 2 are arranged in a flow pipe 1.
  • Stator blades are installed downstream of the rotor 2.
  • Fig. 1 also shows a front view.
  • a Prandtl tube 5 and a pressure sensor 6 are provided, which are arranged on a tube wall 7 in such a way that, in relation to an inlet plane of the rotor 2 upstream adjacent to the inlet plane on the inside of the tube wall 7, pressure measurement values can be recorded in a time-resolved manner .
  • the Prandtl tube 5 is used to measure the dynamic pressure in the flow tube 1.
  • the pressure sensor 6 is used to measure the static, unsteady pressure.
  • the pressure measurement is carried out in a time-resolved manner, with pressure fluctuations, for example, being measurable with a high time resolution in a frequency range from approximately 10 kHz to approximately 50 kHz.
  • a further pressure sensor 6a is provided with which time-resolved pressure measurement values comparable to the measurement with the pressure sensor 6 can be recorded and which can alternatively be omitted.
  • a pressure measuring device 9 is provided in order to measure the static pressure at a compressor outlet. In combination with the pressure measurement data from the Prandtl tube 5, a pressure ratio generated by the compressor can be determined.
  • Fig. 2 shows a schematic representation of an axial compressor 20 in which, for example, several stage packages 20.1,..., 20.5 are arranged one behind the other and each have a vane rotor and a vane stator, which are arranged in a compressor housing 21.
  • the pressure sensor 6 is comparable to the illustration in FIG Fig. 1 , arranged adjacent to the entry level of the first stage package 20.1. Alternatively, the pressure sensor 6 can also be arranged adjacent to the entry level of one of the later stage packages 20.2,..., 20.5 in order to acquire the measured values for the time-resolved pressure measurement.
  • Fig. 3 shows a schematic representation of a radial compressor 30 with rotor 31 and stator 32, the pressure sensor being arranged in a comparable position.
  • Different operating states can be set for the compressor, for example with a constant speed of the rotor 2.
  • these are characterized by an increasingly lower flow mass flow.
  • the mass flow rate for the respective operating state and associated pressure measurement values recorded in a time-resolved manner are measured with the aid of the pressure sensor 6.
  • the skewness (third static moment) can be determined as an integral parameter from the measured values for the static unsteady pressure, as is known as such.
  • the recorded measured values can be evaluated with the help of an evaluation device (not shown), for example by means of a computer, which has a processor and a memory having.
  • the evaluation device can be connected to the various elements of the measuring device in order to exchange electronic data and signals.
  • An output for outputting optical and / or acoustic signals can be connected to the evaluation device, in particular for outputting one or more warning signals.
  • Fig. 4 shows a schematic representation for a curve 40 that results when running through the various operating states with decreasing flow mass flow when the skew is plotted over a parameter for the flow mass flow, with FIG Fig. 4 the flow coefficient ⁇ is specified.
  • Fig. 5 and 6th show graphical representations for experimental values at speeds of 5500 and 9000 revolutions per minute, the skewness being plotted against the flow coefficient ⁇ .
  • the characteristic curve is shown as it is for Fig. 4 was explained.
  • the compressor With the aid of the drive device 4, the compressor is operated at a certain speed. While the speed remains constant, the outlet opening of the compressor is successively reduced, as a result of which the mass flow is reduced and the pressure built up increases. The so-called throttling of the compressor can only be carried out until the operating limit is reached. This means that at every speed there is a maximum possible pressure build-up from which the stable aerodynamics inside the compressor collapse - the compressor starts to "pump".
  • the flow parameter plotted on the x-axis represents a similarity parameter for comparing different compressor mass flows and is determined during the test.
  • the "reduced mass flow” can also be determined at each operating point.
  • the choice between the two similarity parameters has no influence on the evaluation.
  • For the parameter to be plotted on the y-axis a high-resolution pressure fluctuation over time is measured at each operating point at the blade tips.
  • the pressure signal of any length can be reduced to an integral parameter, the third statistical moment - skewness.
  • the pair of values, consisting of the flow coefficient (reduced mass flow) and the skew is shown in the diagram in Fig. 3 transfer. The process is repeated for all subsequent operating points.
  • the proposed method can use pairs of values for two consecutive operating points in the various configurations for the early detection of compressor pumps in order to determine a local curve slope .
  • this event is interpreted as a preliminary stage for compressor pumping. If there is another sign change in the following (cf., local maximum 43 in Fig. 3 ), the last operating point set characterizes the last stable operating point before reaching the surge limit 42.
  • the method provides for the issuing of a corresponding recommendation to abort the throttling process in order to prevent the surge limit from being exceeded.

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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)
EP18713121.4A 2017-03-02 2018-03-01 Verfahren und vorrichtung zum bestimmen eines indikators für eine vorhersage einer instabilität in einem verdichter sowie verwendung Active EP3589843B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL18713121T PL3589843T3 (pl) 2017-03-02 2018-03-01 Sposób i urządzenie do oznaczania wskaźnika prognozowania niestabilności w sprężarce oraz zastosowanie

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017104414.0A DE102017104414B3 (de) 2017-03-02 2017-03-02 Verfahren und Vorrichtung zum Bestimmen eines Indikators für eine Vorhersage einer Instabilität in einem Verdichter sowie Verwendung
PCT/DE2018/100180 WO2018157889A1 (de) 2017-03-02 2018-03-01 Verfahren und vorrichtung zum bestimmen eines indikators für eine vorhersage einer instabilität in einem verdichter sowie verwendung

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Publication Number Publication Date
EP3589843A1 EP3589843A1 (de) 2020-01-08
EP3589843B1 true EP3589843B1 (de) 2021-04-28

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EP18713121.4A Active EP3589843B1 (de) 2017-03-02 2018-03-01 Verfahren und vorrichtung zum bestimmen eines indikators für eine vorhersage einer instabilität in einem verdichter sowie verwendung

Country Status (6)

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US (1) US11353034B2 (pl)
EP (1) EP3589843B1 (pl)
CN (1) CN110382878B (pl)
DE (1) DE102017104414B3 (pl)
PL (1) PL3589843T3 (pl)
WO (1) WO2018157889A1 (pl)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019216712A1 (de) * 2019-10-30 2021-05-06 Robert Bosch Gmbh Verfahren zum Betreiben und zum Auslegen eines Brennstoffzellensystems
CN113297705B (zh) * 2021-04-22 2023-02-14 西北工业大学 一种根据设计指标预测压气机特性的方法
CN115306754B (zh) * 2022-10-12 2023-02-17 中国航发四川燃气涡轮研究院 基于声阵列的轴流风扇气动失稳辨识方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177649A (en) * 1977-11-01 1979-12-11 Borg-Warner Corporation Surge suppression apparatus for compressor-driven system
JPS54119103A (en) * 1978-03-08 1979-09-14 Hitachi Ltd Pump operating method and system
JPH02286899A (ja) 1989-04-28 1990-11-27 Masahiro Inoue ターボ機械の旋回失速を回避するための旋回失速予知装置
CA2149576A1 (en) * 1994-05-19 1995-11-20 Hideomi Harada Surge detection device and turbomachinery therewith
US5908462A (en) 1996-12-06 1999-06-01 Compressor Controls Corporation Method and apparatus for antisurge control of turbocompressors having surge limit lines with small slopes
US6098010A (en) * 1997-11-20 2000-08-01 The Regents Of The University Of California Method and apparatus for predicting and stabilizing compressor stall
DE10152026A1 (de) 2001-10-23 2004-02-19 Mtu Aero Engines Gmbh Warnung vor Pumpgrenze oder Schaufelschaden bei einer Turbomaschine
JP4890095B2 (ja) 2006-05-19 2012-03-07 株式会社Ｉｈｉ ストール予兆検知装置及び方法、並びにエンジン制御システム
US20120141251A1 (en) 2009-08-21 2012-06-07 Universidad Politécnica de Madrid Method and device for predicting the instability of an axial compressor
CN103198193B (zh) * 2013-04-12 2015-12-02 北京大学 基于一阶模态幅值斜率的压气机旋转失速预测方法及系统

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PL3589843T3 (pl) 2021-10-25
DE102017104414B3 (de) 2018-07-19
EP3589843A1 (de) 2020-01-08
US11353034B2 (en) 2022-06-07
WO2018157889A1 (de) 2018-09-07
US20190383297A1 (en) 2019-12-19
CN110382878B (zh) 2020-12-08
CN110382878A (zh) 2019-10-25

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