EP2626569A1 - Verfahren zur Vermeidung von Pumpstößen in einem Verdichter - Google Patents

Verfahren zur Vermeidung von Pumpstößen in einem Verdichter Download PDF

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Publication number
EP2626569A1
EP2626569A1 EP12154644.4A EP12154644A EP2626569A1 EP 2626569 A1 EP2626569 A1 EP 2626569A1 EP 12154644 A EP12154644 A EP 12154644A EP 2626569 A1 EP2626569 A1 EP 2626569A1
Authority
EP
European Patent Office
Prior art keywords
compressor
turbomachine
sensors
turbine
parameters
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Withdrawn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
EP12154644.4A
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German (de)
English (en)
French (fr)
Inventor
Claus Grewe
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
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP12154644.4A priority Critical patent/EP2626569A1/de
Priority to JP2014555955A priority patent/JP6005181B2/ja
Priority to EP12806422.7A priority patent/EP2805058B1/de
Priority to PCT/EP2012/075248 priority patent/WO2013117271A1/de
Priority to CN201280069486.3A priority patent/CN104114874B/zh
Priority to US14/376,426 priority patent/US20150044020A1/en
Publication of EP2626569A1 publication Critical patent/EP2626569A1/de
Withdrawn legal-status Critical Current

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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
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring

Definitions

  • the invention relates to a method for avoiding pump surges in a compressor, in which a plurality of characteristics of the compressor is monitored during operation and a setpoint range for the plurality of characteristics is predetermined, wherein when exceeding or falling below a number of parameters from the setpoint range a counteracting the pump surge reaction is triggered. It further relates to a compressor and a turbomachine with a compressor and a control device, which is connected to the data input side with a plurality of sensors, which are designed to detect characteristics during operation.
  • Compressors especially gas turbines, tend to pump under certain operating conditions. If the counter-pressure in the direction of flow becomes too great, then the compressor can no longer convey air and the direction of flow reverses locally or even completely. With local backflow, a portion of the air trapped in the compressor and rotates with the blades with. One speaks of a rotating separation of the flow (rotating stall). In contrast, in the so-called compressor surge (deep surge) the medium completely flows back - it comes to a vehement shock opposite to the thrust direction.
  • the compressor map which typically represents the pressure ratio between inlet and outlet pressures versus flow rate, is divided by the surge line into a stable and an unstable region. Pumping occurs when the operating points of the compressor fall into the unstable range by reducing the flow rate (throughput) or by increasing the final pressure (delivery head).
  • a surge margin is defined in the control electronics or software of a control device of the turbomachine, which is sufficiently far away from the surge limit in operation at design conditions.
  • a surge margin is defined in the control electronics or software of a control device of the turbomachine, which is sufficiently far away from the surge limit in operation at design conditions.
  • real conditions such as. B. with decreasing power frequency, high ambient temperatures and / or air humidity, low calorific values of fuels, but also by aging, contamination or damage to the compressor, it may happen that the surge line reaches the operating characteristic or even falls below. This then leads to immediate pumping of the compressor.
  • a compressor pressure ratio limiting regulator is therefore often used.
  • Such a controller looks at characteristics of the compressor (pressure ratio, line frequency, Vorleitschaufelhorn and ambient conditions such as temperature and humidity) and compares these with allowable values from a compressor-specific Surge limit map. If the current operating point of the surge limit approaches, ie if it exceeds or falls below a predetermined setpoint range, a reaction counteracting the pump surge is triggered.
  • a disadvantage of both mentioned methods is that they do not take into account aging, massive contamination or damage to the compressor and thus can no longer reliably prevent pumping of the compressor as the running time of the turbomachine increases.
  • the invention is therefore based on the object to provide a method for preventing pump surges in a compressor, a compressor or a turbomachine, which reliably prevent pumping of the compressor even at relatively high mileage.
  • the object is achieved according to the invention in that the plurality of parameters comprises a parameter associated with the rotary sound of the compressor.
  • the invention is based on the consideration that for a higher mileage of the turbomachine reliable prevention of pump surges should not be resorted exclusively to predetermined maps and controllable operating variables, but rather current, suitable for preventive detection of impending surge should be used measured variables . Predictive detection would be possible if an approximation to the surge limit in the form of the rotating stall, ie the rotating flow separation, could already be detected by appropriate measurements. It was recognized that such a flow separation generates vibrations in the compressor stages, which lead to increased pressure pulsations and further vibrations. These pressure pulsations and vibrations change the rotational sound of the compressor, so that a change in the rotary sound indicates predictive an imminent pumping. Therefore, a characteristic associated with the rotary sound of the compressor should be used measured and used to avoid pump surges.
  • the measured characteristic assigned to the rotary sound of the compressor is advantageously a vibration amplitude and / or frequency of a component of the turbomachine.
  • the pressure pulsations are also transmitted to the components of the turbomachine.
  • the suitable sensors and encoders are less sensitive to the operating conditions mentioned and thus more durable.
  • the shaft and / or the housing of the turbine and / or the compressor is the shaft and / or the housing of the turbine and / or the compressor.
  • the rotary sound can be determined particularly well with regard to an imminent approach to the surge line particularly well.
  • the characteristics used further include the shaft speed, the compressor discharge pressure and / or the Vorleitschaufel too.
  • the predictive recognition of the pumping can be further improved since the rotary sound can be determined particularly well with the aid of these additional parameters, for example in a computer provided with special evaluation algorithms specifically for the measurement.
  • the counteracting the pump surge reaction comprises a reduction of the target value of the turbine outlet temperature and / or a reduction of the fuel mass flow.
  • a reduction of the setpoint value of the turbine outlet temperature results in the fact that the adjustable pilot vanes of the compressor are opened. This increases the distance to the surge line.
  • the compressor discharge pressure and thus the compressor pressure ratio are reduced as quickly as possible.
  • z. B. through the anti-icing valve of the compressor at the compressor end air are removed. Improving then the air removal via the anti-icing valve can be re-introduced at the compressor inlet. This also reduces the compressor pressure ratio.
  • a turbomachine with a compressor and a control device for carrying out the method described is formed.
  • the object is achieved by one of the sensors for detecting a characteristic assigned to the rotary sound of the compressor is trained.
  • the respective sensor is a vibration sensor.
  • This is advantageously designed as a vibrometer.
  • vibrometers which measure accelerations on a piezoelectric basis, such as, for example, the piezoelectric accelerometer CA 901 from Meggitt. This is particularly durable and robust against high temperatures, soiling and compressor washes.
  • the respective sensor of the shaft and / or the housing of the turbine and / or the compressor is assigned.
  • corresponding sensors are advantageously mounted at several points on the circumference of the compressor, ideally in Klingelbohrungen outside, d. H. not in the flow path.
  • a power plant advantageously comprises a turbomachine described.
  • the advantages achieved by the invention are in particular that can be seen by the targeted measurement of the rotational sound of the compressor of a turbomachine approach to the surge line or a rotating stall before an actual pumping occurs.
  • This can be achieved particularly easily by means of corresponding vibration sensors which measure pressure changes of rotating compressor rotor blades of one stage.
  • Other donors shaft speed, compressor discharge, Vorleitschaufel too
  • B. determine a computer with special evaluation algorithms. This also makes it possible to detect foreign objects that can damage the compressor flow path and its parts. Namely, such foreign bodies also lead to a change in the rotary sound. Subsequent damage to components downstream of the compressor can thus be avoided.
  • FIG. 1 shows schematically a section through the upper half of a compressor of a gas turbine.
  • the turbomachine 1 which is shown in detail in FIG. 1, is designed as a gas turbine. From the gas turbine, only the compressor 2 is shown.
  • the compressor 2 comprises guide vanes 6 fixed to a housing 4 and thus fixed, which are located in a flow channel 8 between the compressor inlet 10 and the compressor outlet 12.
  • In the Flow direction of the air first vane 6 is configured as an adjustable Vorleitschaufel 14. As a result, the air supply can be regulated and throttled in the flow channel 8.
  • blades 18 are each arranged on a shaft.
  • the blades 18 and the guide vanes 6, 14 are each arranged in a star shape in rings in the flow channel 8.
  • a ring of guide vanes 6, 14 together with the following in the flow direction ring of blades 18 each one stage of the compressor. 2
  • vibration sensors 20 are mounted in each 90 ° angularly mounted bell holes that detect mechanical vibrations and thus allow an image of the rotational sound of the compressor 2.
  • the rotary sound is determined by means of an evaluation algorithm 22, which as software on a control device, not shown, for. B. a computer is implemented.
  • an evaluation algorithm 22 which as software on a control device, not shown, for. B. a computer is implemented.
  • the data of further corresponding sensors or sensors are included in the evaluation algorithm. These include the shaft speed, the compressor pressure ratio between compressor inlet 10 and compressor outlet 12, the vane position, the shaft vibration, and the housing vibration at the compressor and turbine.
  • the computer sends signals (binary or analog) to perform appropriate responses to prevent pumping.
  • the reactions include opening the anti-icing valve 24, lowering the turbine exit temperature 26 and reducing the amount of fuel 28. Other measures may also be provided.
  • the reactions can be triggered as needed as a function of the results determined by the evaluation algorithm 22. Thus, for example, only a few of the reactions mentioned can take place or else a majority. Furthermore, messages can be sent to operating personnel 30.
  • Foreign object impacts also trigger messages to the operations control system or to the operating personnel 30. The operations control or personnel can then decide on the measures to be taken, for. B. Shutdown and Diagnosis of the Compressor 2 or the Turbomachine 1.
  • Foreign object impacts that can lead to secondary damage or damage to compressor components can - if they do not occur spontaneously - be detected and reported. On the other hand, spontaneous, severe damage leads to automatic measures in the case of FOD 32 (Foreign Object Detection), such as the shutdown of the gas turbine.
  • FOD 32 Form Object Detection

Landscapes

  • 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)
  • Control Of Positive-Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP12154644.4A 2012-02-09 2012-02-09 Verfahren zur Vermeidung von Pumpstößen in einem Verdichter Withdrawn EP2626569A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP12154644.4A EP2626569A1 (de) 2012-02-09 2012-02-09 Verfahren zur Vermeidung von Pumpstößen in einem Verdichter
JP2014555955A JP6005181B2 (ja) 2012-02-09 2012-12-12 圧縮機におけるポンプサージングの防止方法
EP12806422.7A EP2805058B1 (de) 2012-02-09 2012-12-12 VERFAHREN ZUR VERMEIDUNG VON PUMPSTÖßEN IN EINEM VERDICHTER
PCT/EP2012/075248 WO2013117271A1 (de) 2012-02-09 2012-12-12 VERFAHREN ZUR VERMEIDUNG VON PUMPSTÖßEN IN EINEM VERDICHTER
CN201280069486.3A CN104114874B (zh) 2012-02-09 2012-12-12 用于避免压缩机中的泵喘振的方法
US14/376,426 US20150044020A1 (en) 2012-02-09 2012-12-12 Method for avoiding pump surges in a compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12154644.4A EP2626569A1 (de) 2012-02-09 2012-02-09 Verfahren zur Vermeidung von Pumpstößen in einem Verdichter

Publications (1)

Publication Number Publication Date
EP2626569A1 true EP2626569A1 (de) 2013-08-14

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EP12154644.4A Withdrawn EP2626569A1 (de) 2012-02-09 2012-02-09 Verfahren zur Vermeidung von Pumpstößen in einem Verdichter
EP12806422.7A Active EP2805058B1 (de) 2012-02-09 2012-12-12 VERFAHREN ZUR VERMEIDUNG VON PUMPSTÖßEN IN EINEM VERDICHTER

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EP12806422.7A Active EP2805058B1 (de) 2012-02-09 2012-12-12 VERFAHREN ZUR VERMEIDUNG VON PUMPSTÖßEN IN EINEM VERDICHTER

Country Status (5)

Country Link
US (1) US20150044020A1 (ja)
EP (2) EP2626569A1 (ja)
JP (1) JP6005181B2 (ja)
CN (1) CN104114874B (ja)
WO (1) WO2013117271A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3045676A1 (de) * 2015-01-13 2016-07-20 Siemens Aktiengesellschaft Verfahren zur Vermeidung eines rotierenden Strömungsabrisses

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109458324A (zh) * 2018-10-31 2019-03-12 重庆美的通用制冷设备有限公司 压缩机喘振识别方法、装置及系统
CN111120360A (zh) * 2019-12-22 2020-05-08 云南瑞斯德机械有限公司 一种减少离心式压缩机喘振现象且自动调节流量的结构及方法
TWI773107B (zh) * 2021-01-29 2022-08-01 復盛股份有限公司 喘振偵測方法及壓縮裝置
CN113945029B (zh) * 2021-10-19 2023-04-25 青岛海尔空调电子有限公司 用于控制冷媒循环系统的方法、装置及冷媒循环系统
CN114754020B (zh) * 2022-04-18 2024-02-02 合肥通用机械研究院有限公司 基于进气噪声特性的压缩机喘振监控系统和监控方法

Citations (7)

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GB822443A (en) * 1955-03-24 1959-10-28 United Aircraft Corp Fuel control systems for gas turbine engines
US4399548A (en) * 1981-04-13 1983-08-16 Castleberry Kimberly N Compressor surge counter
WO2003038282A1 (de) * 2001-10-23 2003-05-08 Mtu Aero Engines Gmbh Warnung vor pumgrenze oder schaufelschaden bei einer turbomaschine
WO2007086755A1 (en) * 2006-01-26 2007-08-02 Dynatrend As A method and device for determining the occurence of rotating stall in a compressor's turbine blade ii
DE102008044433A1 (de) * 2007-08-17 2009-02-19 General Electric Co. Vorrichtung und Verfahren zum Überwachen eines Verdichterspalts und zur Steuerung einer Gasturbine
US20090055071A1 (en) * 2007-08-22 2009-02-26 Cleveland Electric Laboratories Active surge control
EP2375081A2 (en) * 2010-04-08 2011-10-12 General Electric Company System and method for monitoring a compressor

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AU4637293A (en) * 1992-08-10 1994-03-03 Dow Deutschland Inc. Process and device for monitoring and for controlling of a compressor
US6092029A (en) * 1998-02-19 2000-07-18 Bently Nevada Corporation Method and apparatus for diagnosing and controlling rotating stall and surge in rotating machinery
JP4705732B2 (ja) * 2000-05-25 2011-06-22 本田技研工業株式会社 航空機用ガスタービン・エンジンのサージ検出装置
US7003426B2 (en) * 2002-10-04 2006-02-21 General Electric Company Method and system for detecting precursors to compressor stall and surge
US7282873B2 (en) * 2004-11-16 2007-10-16 Lenovo (Singapore) Pte. Ltd. Mutual active cancellation of fan noise and vibration
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US7905702B2 (en) * 2007-03-23 2011-03-15 Johnson Controls Technology Company Method for detecting rotating stall in a compressor
CN201575861U (zh) * 2009-02-18 2010-09-08 长沙全程数字机电科技有限公司 一体化振动监测仪
US8074499B2 (en) * 2009-12-22 2011-12-13 General Electric Company Method and system for detecting a crack on a turbomachine blade

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB822443A (en) * 1955-03-24 1959-10-28 United Aircraft Corp Fuel control systems for gas turbine engines
US4399548A (en) * 1981-04-13 1983-08-16 Castleberry Kimberly N Compressor surge counter
WO2003038282A1 (de) * 2001-10-23 2003-05-08 Mtu Aero Engines Gmbh Warnung vor pumgrenze oder schaufelschaden bei einer turbomaschine
WO2007086755A1 (en) * 2006-01-26 2007-08-02 Dynatrend As A method and device for determining the occurence of rotating stall in a compressor's turbine blade ii
DE102008044433A1 (de) * 2007-08-17 2009-02-19 General Electric Co. Vorrichtung und Verfahren zum Überwachen eines Verdichterspalts und zur Steuerung einer Gasturbine
US20090055071A1 (en) * 2007-08-22 2009-02-26 Cleveland Electric Laboratories Active surge control
EP2375081A2 (en) * 2010-04-08 2011-10-12 General Electric Company System and method for monitoring a compressor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3045676A1 (de) * 2015-01-13 2016-07-20 Siemens Aktiengesellschaft Verfahren zur Vermeidung eines rotierenden Strömungsabrisses

Also Published As

Publication number Publication date
CN104114874B (zh) 2016-08-31
JP6005181B2 (ja) 2016-10-12
WO2013117271A1 (de) 2013-08-15
CN104114874A (zh) 2014-10-22
US20150044020A1 (en) 2015-02-12
EP2805058B1 (de) 2016-06-29
JP2015511288A (ja) 2015-04-16
EP2805058A1 (de) 2014-11-26

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