WO2009041851A1 - Procédé de régulation des régimes de fonctionnement d'un compresseur et dispositif de mise en oeuvre correspondant - Google Patents

Procédé de régulation des régimes de fonctionnement d'un compresseur et dispositif de mise en oeuvre correspondant Download PDF

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Publication number
WO2009041851A1
WO2009041851A1 PCT/RU2008/000257 RU2008000257W WO2009041851A1 WO 2009041851 A1 WO2009041851 A1 WO 2009041851A1 RU 2008000257 W RU2008000257 W RU 2008000257W WO 2009041851 A1 WO2009041851 A1 WO 2009041851A1
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WO
WIPO (PCT)
Prior art keywords
compressor
impeller
pressure
pulsations
sensor
Prior art date
Application number
PCT/RU2008/000257
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English (en)
Russian (ru)
Inventor
Nataliya Nikolaevna Ledovskaya
Original Assignee
Central Institute Of Aviation Motors (Ciam)
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 Central Institute Of Aviation Motors (Ciam) filed Critical Central Institute Of Aviation Motors (Ciam)
Publication of WO2009041851A1 publication Critical patent/WO2009041851A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control

Definitions

  • the invention relates to the field of aircraft engine manufacturing, compressor engineering, and the operation of compressor systems, in particular, to their regulation and protection.
  • Pulsation sensors show that, simultaneously with a change in the high-frequency part of the spectrum, which can be manifested in an increase in the amplitudes of the harmonics of the repetition frequency of the blades A n i and its multiple frequencies: A P2 , A n s ... A n i, the pulsation spectrum changes in the frequency band from 0 to the blades repetition rate A n ]. In this case, the standard deviation of the pressure in this frequency region increases.
  • a further decrease in the flow rate leads to a redistribution of the pulsation energy in this frequency band to the low frequency region, which is manifested in a change in the ratio of the amplitudes of rotor harmonics with numbers from Ai to 0.5 A n i.
  • the occurrence of flow destabilization due to a decrease in flow rate, is accompanied by the appearance in the spectrum of harmonics in the frequency band 0 ... Ai at the frequency of the rotating stall, which indicates its (nucleation) occurrence.
  • the development of stalling phenomena with a decrease in flow rate after the initiation of a rotating stall leads to a decrease in the frequency of flow pulsations and the further development of a rotating stall and the occurrence of surging.
  • SUBSTITUTE SHEET (RULE 26) spectral components of pressure pulsations, measured at least at two points along the circumferential direction of the turbocompressor flow path through which a control signal is generated, compared with a threshold value.
  • the frequencies of the spectral components are compared with the rotor speed, after which the amplitude-frequency characteristics, the frequency of which is a multiple of the rotor speed, are used as the first component of the control signal, and the phase shift between the spectral components not multiple of the rotor speed is used as the second signal component control, the received two-component control signal is then compared with a threshold value, which is a function of the rotor speed.
  • TT / V indicates the occurrence of a rotating stall
  • f bases
  • ⁇ Psekund - Shchasovj determine the shift of the mode of occurrence of a rotating stall relative to the base border by the ratio
  • patent RU Na 2246640, F04D 27/02, 07/22/2003 which consists in the fact that they are installed downstream of the throat of the interscapular channel of the straightening apparatus of the last stage of the nozzle compressor to measure the total and bottom pressures, measure the difference between the total and bottom pressures, determine the mathematical expectation of the bottom pressure from the averaging time 0.1–0.2 ⁇ p0c , where ⁇ is the percentage time constant of the controlled transient.
  • control signals are generated after the appearance of signs of the onset of loss of flow stability in the compressor, i.e. the beginning of the formation of a rotating stall in it, manifested in the spectrum in the form of harmonics at a frequency less than and not a multiple of the frequency of rotation of the impeller.
  • the formation of control signals requires a time comparable to the time of occurrence and existence of stall phenomena in the compressor, in particular a rotating stall. This creates the possibility of loss of gas-dynamic stability of the compressor.
  • the objective of the proposed technical solution is to increase the reliability of the compressor, ensuring the maintenance of its stable operation by correcting the operating mode in case of detection of a sign indicating the approach of the occurrence of a rotating stall.
  • a spectral analysis of pressure pulsations is carried out, and harmonic amplitudes are used as a control signal, the frequencies of which are a multiple of the frequency of rotation of the impeller of the compressor and do not exceed 0.5 of the repetition frequency of the blades of the impeller of the compressor.
  • a control signal is generated, it is compared with a threshold value, which prevents the appearance of signs of a rotating stall and surge.
  • the threshold value of the control signal is a function of the impeller speed and the reduced
  • SUBSTITUTE SHEET (RULE 26) axial flow velocity at the inlet, and is determined under conditions of stable operation of the compressor, to ensure recognition of its emergency state.
  • the inventive device for monitoring compressor operating modes comprises a full pressure pulsation sensor and a static pressure pulsation sensor, which are installed in the compressor flow path, a compressor impeller, a compressor impeller speed sensor, a digital recorder, a speed and peripheral speed determiner wheels, spectrum analyzer, determinant of flow parameters, data bank for preliminary tests at different speeds, analyzer, etc. comparing the measured and preliminary data, the shaper of the control signal.
  • a sensor for full pressure and pulsations of full pressure In front of the leading edge of the compressor impeller, a sensor for full pressure and pulsations of full pressure, and a sensor for static pressure and pulsations of static pressure are installed for synchronous, continuous measurement of total and static pressures and pulsations of full and static pressures at different speeds of rotation of the compressor impeller.
  • the outputs of the full pressure sensor and pulsation of the full pressure, the static pressure sensor and pulsation of static pressure, the speed sensor of the impeller of the compressor are connected to a digital recorder, which is connected to an analyzer that compares the measured and preliminary data.
  • the digital recorder Through the determinant of the rotational speed and peripheral speed of the impeller, the digital recorder is connected to a data bank for preliminary tests at different rotational speeds.
  • the digital recorder is connected through a spectrum analyzer and through a flow parameter determiner with a data bank according to preliminary
  • SUBSTITUTE SHEET (RULE 26) torture at different speeds.
  • the database of preliminary tests at different rotational speeds has feedback from the spectrum analyzer to ensure its continuous operation.
  • a digital recorder, a determinant of the rotational speed and peripheral speed of the impeller, a spectrum analyzer, a determinant of flow parameters and a database of preliminary tests at different rotational speeds have a direct connection with the analyzer, which compares the measured and preliminary data and recognizes its pre-disruptive state.
  • An analyzer comparing the measured and preliminary data and recognizing its pre-disruptive state is connected to a control signal shaper, where a compressor mode control signal is generated, which ensures its stable operating state.
  • the analyzer, which compares the measured and preliminary data and recognizes its pre-disruptive state has feedback from the spectrum analyzer, which, in the case of stable operation of the compressor, provides a signal to the spectrum analyzer to continue its operation.
  • measurements of the total pressure and pulsations of the total pressure, static pressure and pulsations of the static pressure are performed synchronously and continuously at different frequencies of rotation of the impeller of the compressor, and at the same time they are processed throughout its operation.
  • a spectral analysis of the measurement results is performed, compared with the results of preliminary tests. Based on a sample of harmonics amplitudes at frequencies that are multiple of the impeller rotation frequency, which are rotor harmonics, and do not exceed 0.5
  • the main flow parameters are determined:
  • Recognition of the compressor pre-failure state by the main flow parameters and the sample of rotor harmonic amplitudes provides the ability to fine-tune the inventive device to the parameters of a specific compressor, which increases the accuracy of determining the boundaries of stable operation of the compressor, and extends the compressor operating area with the highest efficiency values.
  • the performance of the claimed device is enhanced by the use of high-frequency sensors and a spectral analysis algorithm with short averaging periods.
  • the claimed device does not allow the occurrence of vibrations that occur in the scapular machine due to inhomogeneities that occur during the formation of a rotating stall.
  • Figure 1 presents a diagram of a device for monitoring the operating modes of the compressor.
  • Figure 2 presents the algorithm for implementing the method of monitoring the operating modes of the compressor according to the claimed device.
  • a device for monitoring compressor operating conditions shown in FIG. 1 comprises:
  • the elements of the device for monitoring the compressor operating modes are interconnected, as shown in figure 2, namely: sensor 1 of the total pressure and pulsations
  • SUBSTITUTE SHEET (RULE 26) full pressure and static pressure sensor 2 and static pressure pulsations are installed in front of the leading edge of the compressor impeller 3 for synchronous and continuous measurement of total and static pressure and their pulsations, while the outputs of sensor I 5 of sensor 2 are connected to a digital recorder 5, which records the measured values full and static pressures and their pulsation and forms temporary implementations.
  • the digital recorder 5 registers the readings of the sensor 4 of the rotational speed of the impeller 3 of the compressor.
  • the obtained temporary realizations from the digital recorder 5 are transferred to the determinant 6 of the rotational speed and peripheral speed of the impeller 3 of the compressor, to the spectrum analyzer 7 and the determinant 8 of the flow parameters.
  • the results of operation of the determinant 6 of the rotational speed and peripheral speed of the impeller of the compressor and the determinant 8 of the flow parameters, as well as the spectrum analyzer 7, which calculates the spectra of pressure pulsations, are transmitted to the input of the data bank 9 on preliminary tests at different rotational speeds.
  • the data bank 9 for preliminary tests at different rotational speeds has feedback with the spectrum analyzer 7, which, after the calculation of the spectra of pressure pulsations and transmission of a signal about it to the data bank 9, receives a command to continue the calculation of the spectra of pressure pulsations.
  • SUBSTITUTE SHEET (RULE 26) plateau of harmonics whose frequencies are a multiple of the rotational speed of the impeller 3 of the compressor and do not exceed 0.5 the repetition frequency of the blades of its impeller. After that, they are compared with the data of preliminary tests. If the threshold value obtained from the data bank 9 on preliminary tests at different speeds of rotation of the impeller of the compressor is exceeded, the signal is transmitted to the shaper 11 of the control signal, where the control signal of the compressor operating mode is generated and it is transferred to a more favorable mode.
  • the inventive device for monitoring the operating modes of the compressor according to the claimed method works as follows.
  • the sensor 1 of the total pressure and pulsations of the total pressure and the sensor 2 of the static pressure and pulsations of the static pressure are placed at the compressor inlet in front of the leading edge of the compressor impeller 3, and the averaged flow and pulsation parameters are measured at different frequencies of rotation of the compressor impeller.
  • the sensor 4 rotational speed of the impeller of the compressor measure the frequency of its rotation.
  • SUBSTITUTE SHEET (RULE 26)
  • the measured parameters P * and (P *) ', converted into electrical signals, are recorded using a digital recorder 5, where temporary realizations are formed, which are transmitted to the inputs of the determiner 6 of the speed and peripheral speed of the compressor impeller 3, a spectrum analyzer 7, and determinant 8 flow parameters.
  • the obtained values of the frequency of its rotation are transmitted to the spectrum analyzer 7 to calculate the spectral composition of the pulsations of static and total pressure.
  • the values of the peripheral speed from the determinant 6 of the speed of rotation and the peripheral speed of the impeller of the compressor are transmitted to the data bank 9 for preliminary tests at different frequencies of rotation of the impeller of the compressor.
  • Databank 9 is a program containing the values of the flow parameters and its pulsations obtained as a result of preliminary tests of the compressor at different speeds under conditions of its stable and unstable operation to select parameter values at the optimal characteristics points and near the stability boundary for the corresponding speed values and peripheral speed.
  • the data bank 9 has feedback with the spectrum analyzer 7, which allows, after transmitting data from the spectrum analyzer 7 to the data bank 9, to resume the operation of the spectrum analyzer 7 for calculating the pressure fluctuation spectra.
  • the spectrum analyzer 7 From the outputs of the determinant 6 of the rotational speed and peripheral speed of the compressor impeller, the spectrum analyzer 7, the determinant 8 of the flow parameters and the data bank 9 for preliminary tests at different rotational speeds of the compressor impeller 3, the data obtained using them are transmitted to the analyzer 10, which
  • SUBSTITUTE SHEET (RULE 26) compares the measured data and the data obtained during preliminary tests at the same impeller speed and reduced inlet flow rate.
  • An analyzer 10 comparing the measured and preliminary data has feedback with a spectrum analyzer 7, which, in the case of stable operation of the compressor, provides a signal to the spectrum analyzer 7 to continue its operation.
  • a control signal is generated in the control signal generator 11, which recognizes the compressor pre-failure state, for the formation of which harmonic amplitudes are used, at frequencies that are a multiple of the frequency of the impeller rotation and do not exceed 0.5 the repetition frequency of the working blades compressor wheels.
  • the inventive method of monitoring the compressor mode and the device for its implementation allow for stable operation of the compressor, since the control signal is generated in conditions of stable operation and does not allow signs of the occurrence of a rotating stall and surge.

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

Abstract

L'invention concerne le domaine de la construction de moteurs d'avion et de compresseurs. Le procédé de régulation des régimes de fonctionnement du compresseur consiste à mesurer les paramètres des pulsations de pression, à mesurer la fréquence de rotation de la roue principale, à former un signal de commande du régime de fonctionnement, et à le comparer à une valeur de seuil. Le dispositif comprend un capteur (1) de pression globale des pulsations de pression intégrale, un capteur (2) de pression statique et de pulsations de pression statique, un enregistreur numérique, un capteur (4) de fréquence de rotation de la roue principale (3), un instrument (6) pour déterminer la fréquence de rotation et la vitesse circulaire de la roue principale (3), un analyseur spectral (7), un dispositif (8) pour déterminer les paramètres de flux, une banque de données (9) un analyseur (10) et un formateur de signal de commande (11). L'invention permet d'augmenter la fiabilité du compresseur, d'assurer la stabilité de son fonctionnement par la correction du régime de fonctionnement en cas de détection d'un signe indiquant la proximité d'un arrachage par rotation.
PCT/RU2008/000257 2007-09-24 2008-05-21 Procédé de régulation des régimes de fonctionnement d'un compresseur et dispositif de mise en oeuvre correspondant WO2009041851A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2007135287/06A RU2354851C1 (ru) 2007-09-24 2007-09-24 Способ контроля режимов работы компрессора и устройство для его осуществления
RU2007135287 2007-09-24

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106321465A (zh) * 2016-08-22 2017-01-11 江苏大学 一种离心泵叶轮旋转失速的动力学表征方法
CN113482960A (zh) * 2021-06-23 2021-10-08 中国航发沈阳发动机研究所 一种航空燃气涡轮发动机喘振判断方法
CN114033736A (zh) * 2021-12-23 2022-02-11 国家能源集团泰州发电有限公司 一种基于气压脉动信号风机故障监测系统
CN114169178A (zh) * 2021-12-14 2022-03-11 中国水利水电科学研究院 基于emd的暂态过程压力脉动数值处理系统及其方法
CN114033736B (zh) * 2021-12-23 2024-05-31 国家能源集团泰州发电有限公司 一种基于气压脉动信号风机故障监测系统

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2962500B1 (fr) * 2010-07-08 2012-09-14 Snecma Procede et dispositif de detection d'un decollement tournant affectant un compresseur de turbomachine
FR3089263B1 (fr) * 2018-12-03 2020-12-11 Safran Aircraft Engines Procédé et dispositif de détection d’un décollement tournant affectant un compresseur d’un turboréacteur

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DE4202226A1 (de) * 1991-10-01 1993-04-08 Atlas Copco Energas Verfahren zur ueberwachung der pumpgrenze von mehrstufigen, zwischengekuehlten turboverdichtern
RU2098669C1 (ru) * 1995-08-21 1997-12-10 Открытое акционерное общество "Кировский завод" Способ стабилизации запаса газодинамической устойчивости турбокомпрессора
US6558113B2 (en) * 2000-01-14 2003-05-06 Man Turbomaschinen Ag Ghh Borsig Process and device for regulating a turbocompressor to prevent surge
RU2230939C2 (ru) * 2002-04-24 2004-06-20 Закрытое акционерное общество "Завод "КИРОВ-ЭНЕРГОМАШ" Способ регулирования режимов работы компрессора
RU2246640C1 (ru) * 2003-07-22 2005-02-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Способ контроля режимов работы компрессорной системы и устройство для его реализации
RU2295654C1 (ru) * 2005-07-19 2007-03-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Способ защиты газотурбинного двигателя и устройство для его осуществления (варианты)

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4202226A1 (de) * 1991-10-01 1993-04-08 Atlas Copco Energas Verfahren zur ueberwachung der pumpgrenze von mehrstufigen, zwischengekuehlten turboverdichtern
RU2098669C1 (ru) * 1995-08-21 1997-12-10 Открытое акционерное общество "Кировский завод" Способ стабилизации запаса газодинамической устойчивости турбокомпрессора
US6558113B2 (en) * 2000-01-14 2003-05-06 Man Turbomaschinen Ag Ghh Borsig Process and device for regulating a turbocompressor to prevent surge
RU2230939C2 (ru) * 2002-04-24 2004-06-20 Закрытое акционерное общество "Завод "КИРОВ-ЭНЕРГОМАШ" Способ регулирования режимов работы компрессора
RU2246640C1 (ru) * 2003-07-22 2005-02-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Способ контроля режимов работы компрессорной системы и устройство для его реализации
RU2295654C1 (ru) * 2005-07-19 2007-03-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Способ защиты газотурбинного двигателя и устройство для его осуществления (варианты)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106321465A (zh) * 2016-08-22 2017-01-11 江苏大学 一种离心泵叶轮旋转失速的动力学表征方法
CN113482960A (zh) * 2021-06-23 2021-10-08 中国航发沈阳发动机研究所 一种航空燃气涡轮发动机喘振判断方法
CN113482960B (zh) * 2021-06-23 2022-08-30 中国航发沈阳发动机研究所 一种航空燃气涡轮发动机喘振判断方法
CN114169178A (zh) * 2021-12-14 2022-03-11 中国水利水电科学研究院 基于emd的暂态过程压力脉动数值处理系统及其方法
CN114169178B (zh) * 2021-12-14 2024-03-22 中国水利水电科学研究院 基于emd的暂态过程压力脉动数值处理系统及其方法
CN114033736A (zh) * 2021-12-23 2022-02-11 国家能源集团泰州发电有限公司 一种基于气压脉动信号风机故障监测系统
CN114033736B (zh) * 2021-12-23 2024-05-31 国家能源集团泰州发电有限公司 一种基于气压脉动信号风机故障监测系统

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