EP0777828B1 - evitement du calage de compresseurs - Google Patents

evitement du calage de compresseurs Download PDF

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Publication number
EP0777828B1
EP0777828B1 EP96920104A EP96920104A EP0777828B1 EP 0777828 B1 EP0777828 B1 EP 0777828B1 EP 96920104 A EP96920104 A EP 96920104A EP 96920104 A EP96920104 A EP 96920104A EP 0777828 B1 EP0777828 B1 EP 0777828B1
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EP
European Patent Office
Prior art keywords
signal
compressor
further characterized
frequency
value
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.)
Expired - Lifetime
Application number
EP96920104A
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German (de)
English (en)
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EP0777828A1 (fr
Inventor
Jeffrey B. Gertz
Om Parkash Sharma
Kevin M. Eveker
Carl N. Nett
Daniel L. Apartment 19332 GYSLING
Matthew R. Feulner
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Raytheon Technologies Corp
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United Technologies Corp
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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
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0223—Control schemes therefor

Definitions

  • This invention relates to techniques for diagnosing and avoiding stall in rotary compressors, such as aircraft jet engines.
  • the flow through the compressor is essentially uniform around the annulus, i.e., it is axisymmetric, and the annulus-averaged flow rate is steady.
  • the compressor is operated too close to the peak pressure rise on the compressor pressure rise versus mass flow, constant speed performance map, disturbances acting on the compressor may cause it to encounter a region on the performance map in which fluid dynamic instabilities develop, known as rotating stall and/or surge. This region is bounded on the compressor performance map by the surge/stall line. The instabilities degrade the performance of the compressor and may lead to permanent damage, and thus they should be avoided.
  • Rotating stall can be viewed as a two-dimensional phenomena that produces a localized region of reduced or reversed flow through the compressor that rotates around the annulus of the flow path.
  • the region is termed a "stall cell” and typically extends axially through the compressor.
  • Rotating stall produces reduced output (as measured in annulus-averaged pressure rise and mass flow) from the compressor.
  • the stall cell rotates around the annulus it loads and unloads the compressor blades and may induce blade fatigue failure.
  • Surge is a one-dimensional.phenomena defined by oscillations in the annulus-averaged flow through the compressor. Under severe surge conditions, reversal of the flow through the compressor may occur. Both types of instabilities should be avoided, particularly in aircraft applications.
  • Stall margin is a measure of the ratio between peak pressure rise, i.e., pressure rise at stall, and the pressure ratio on the operating line of the compressor for the current flow rate. In theory, the greater the stall margin, the larger the disturbance that the compression system can tolerate before entering stall and/or surge. Thus, a compressor design objective is to incorporate enough stall margin to avoid operating in a condition in which an expected disturbance is likely to trigger stall and/or surge. In gas turbine engines used to power aircraft, stall margins of fifteen to thirty percent are common. Since operating the compressor at less than peak pressure rise carries with it a reduction in operating efficiency and performance, there is a trade off between stall margin and performance. Stall margin can be reduced by engine operating conditions, for instance aircraft pitch and yaw and acceleration (conditions that momentarily change increase current pressure) and over time from component wear, for instance enlarged distances between compressor blade tips and the compressor end wall.
  • An object of the present invention is to avoid compressor stall, especially in aircraft jet engines.
  • a method for controlling the acceleration mode of a gas turbine engine is known from European Patent Application EP-A2-0401152.
  • the system allows the engine to accelerate with an adequate stall margin by controlling the flow of fuel to the burner, in response to certain engine operating parameters under acceleration.
  • the present invention provides a controller for a rotary compressor as claimed in claim 1.
  • the invention provides a method for avoiding stall in a rotary compressor as claimed in claim 10.
  • compressor flow is sensed with one or more pressure sensors to produce a signal that passed through a bandpass filter having a lower roll-off between .01 and 1 of N2 (compressor rotational frequency) and an upper roll-off between 1 and 10 of N2.
  • the output from the filter is smoothed and compared with a "design value" for compressor flow unsteadiness, producing an error that is integrated.
  • One or more compressor bleed valves are opened when the integral exceeds a preset threshold.
  • compressor bleed valves are opened for a fixed duration when the threshold is exceeded.
  • the design value is temporarily changed (e.g., reduced) until the bleed valves close.
  • a feature of the invention stemming from the invention's capability of detecting very early signs of rotating stall, is that a stall controller employing the invention can be used to improve operation of a compression (pumping) system having a compressor susceptible to rotating stall under certain circumstances.
  • a feature of the invention is that it can be used in gas turbine engines and cooling systems, such as some air conditioning systems or refrigeration systems.
  • Fig. 1 shows a bypass gas turbine turbofan engine 10 that uses a static pressure sensor 12 to provide a signal PR1 with characteristics of the compressor flow 14 present at a compressor stage location, for example between the eight and ninth compressor stages.
  • the signal PR1 is supplied to a signal processor (SP) 16, which can be assumed to include a central processing unit and associated memory programmed to cyclically perform computation steps using the signal PR1 and the control/transfer functions 20, 22, 24 and 26 in Fig. 2 to produce a signal A con .
  • SP signal processor
  • the signal processor also receives a compressor speed (N2) signal, which represents the compressor rotational speed or frequency (i.e., rotor frequency).
  • N2 compressor speed
  • the signal A con controls the opening of compressor bleed valves 18 using the following control law, which will be explained in more detail using the software function block diagrams in Fig. 2 and Fig. 3:
  • ⁇ 1 an instantaneous level of unsteadiness in flow properties as manifested in the pressure signal PR1
  • ⁇ k is a stored or"design" value for the instantaneous level of unsteadiness.
  • a so-called “FADEC” or “Full Authority Digital Electronic Control” 28 controls fuel flow to the engine combustors 2 as a function of a power lever advance PLA at a cockpit located power control 4.
  • the fuel control may be assumed to include a signal processor for controlling the fuel flow based on a variety of engine operating parameters and, while a separate signal processor 16 to carry out the special sequences associated with the invention has been shown, it is conceivable that a FADEC can be programmed to perform those operations and produce the A con signal to control the bleed valves 18.
  • a compressor includes a plurality of stages, that the bleed valves 18 are selectively located at certain stages and that the static pressure sensor 12 is ahead of those stages (upstream in the compressor flow), although in some applications the sensor or sensors 12 may be located behind (downstream) from the bleed valves 18.
  • the signal processor 16 is programmed to carry out steps that achieve the functions of blocks 20, 22, 24 and 26.
  • the pressure signal PR1, produced by the sensor 12 will have a time varying characteristic, creating a compressor flow 14 signature, including an indication of the flow unsteadiness along with flow and sensor noise.
  • the pressure signal PR1 is narrowly filtered at block 20, the bandpass frequency ranging from 1N2 to N2 with 2-pole roll-offs at the upper and lower frequencies. An effect is smoothing the signal PR1.
  • the output from the filter function 20, signal PR2, is used in an absolute value 22 function to produce absolute value signal PR2 for the spectrum of information passed through the filter function 20.
  • the output from the block 22 is applied to a low pass filter with a roll off at 1Hz, producing the signal PR3, which in effect is measure of the unsteady flow condition associated with an imminent compressor stall, in other words remaining stall margin.
  • the next block 26 starts the operations shown in Fig. 3.
  • the precursor PR3 is subtracted from a stored value A max (block 32), which is a maximum or design value for the precursor and if exceeded manifests an unstable compressor flow in the value of signal Errorl.
  • a max block 32
  • the output, Error 2 from a second summer 36 would be Error1.
  • the value for Error 2 is integrated at operation 38.
  • the output from the integration step is limited at operation 40 and the output A int (from the limiter 40) is scaled with operation 42, producing the bleed control output signal A con .
  • the bleed valves 18 are commanded to open completely if A con has exceeded a stored threshold; otherwise, the bleed valves 18 remain completely closed.
  • the block 44 should be capable of performing either of the following operations once the bleed valves are opened. It can provide a signal to reduce the value of A max slightly, e.g., by 10 percent while the bleed valves are open and return A max to its full value when the bleed valves close again (the open signal is discontinued).
  • a timer function 44a can be employed to open the bleed valves for a fixed interval when the A con signal is produced.
  • the output from the operation 40 is subtracted from the output from the integrator operation 38 at summer 46, and the error from the summer 46 is scaled with operation 34 and applied to the summer 36, which reduces Error2, preventing the integrator operation from "winding up" beyond the value of A int over time.
  • the bleed valves 18 will rapidly open when the precursor (signal PR1) indicates a flow condition near the stall boundary; that is, the time varying flow characteristics, normally found at the early stages of a rotating stall, are within the bandwidth of filter 20 and last long enough for A con to exceed the threshold.
  • the pressure fluctuations appear hundreds of rotor revolutions prior to an actual stall and/or surge.
  • the X-axis shows the time in seconds before the stall, the stall and/or surge occurring approximately at zero (0) seconds.
  • the Z-axis shows the strength of the pressure disturbance in pounds per square inch squared (psi 2 ) or amplitude squared.
  • the Y-axis indicates the engine order, the frequency of the pressure fluctuation (the value of TP) divided by N2 (the rotational frequency of the rotor disk), the value one (1) being the rotational frequency of the rotor disk and one half (0.5) being one half of the rotational frequency of the rotor disk.
  • N2 pre-stall pressure disturbance at N2 can be detected a few seconds in advance of the stall and/or surge.
  • the value of N2 in this example is approximately one hundred (100) revolutions per second.
  • monitoring the pressure fluctuations at N2 detects the pre-stall condition several hundred rotor revolutions prior to an actual stall.
  • Fig.5 is analogous to Fig.4, but is scaled to show rotating stall disturbances at approximately one half (0.5) or fifty percent (50%) of the rotational frequency of the rotor disk.
  • the preferred embodiment described herein used an unsteady pressure quantity as a form of measurement.
  • Other unsteady flow parameters can be monitored to predict the onset of a stall and/or surge.
  • gas density, velocity, temperature, or any other unsteady flow quantity can be monitored to determine the onset of the stall and/or surge.
  • the velocity can be measured by using hot wire anemometers or a pitot-static tube.
  • the temperature can be measured by using a fine wire thermocouple.
  • the test or diagnostic equipment described and depicted in Fig. 2 is an example of test equipment that can be used to monitor the amplitude of pressure fluctuations according to the invention.
  • Other equipment can be substituted for monitoring the pressure fluctuations within the compressor.
  • the data acquisition system can be either a digital data acquisition system, digital tape, FM analog tape or any other type of a system having capability of recording the pressure disturbances (sensor output) with sufficient frequency bandwidth to resolve the disturbances to rotational frequency of the rotor disk.
  • software packages that can be used in the analysis of the pressure and rotor speed data are MATLAB® program, by The Math Works, Inc. of Natick, Massachusetts, and the SNAP-MASTER® setup program by Hem Data Corporation of Southfield, MI. DAQBOOK® data acquisition hardware made by Iotech of Cleveland, Ohio has been used to produce the outputs with those programs.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Claims (13)

  1. Dispositif de commande d'un compresseur rotatif comportant une soupape de soutirage de compresseur (18), caractérisé par :
    un premier moyen (12) destiné à délivrer un premier signal variant dans le temps (PR1) indiquant l'écoulement de compresseur ;
    un deuxième moyen (20) destiné à délivrer un deuxième signal (PR2) indiquant l'amplitude dudit premier signal entre une première fréquence qui est inférieure à la vitesse de rotation du compresseur et une deuxième fréquence qui est supérieure ou égale à ladite vitesse de rotation de compresseur ; et
    un moyen de traitement de signal (24, 26) destiné à délivrer un premier signal traité à partir dudit deuxième signal qui indique une différence entre l'amplitude dudit deuxième signal et une valeur mise en mémoire (32) dudit deuxième signal, à intégrer ladite différence pour produire un signal de commande et à produire un signal de soutirage (ACON) pour ouvrir la soupape de soutirage de compresseur (18) si ledit signal de commande dépasse la valeur de seuil.
  2. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que ledit premier moyen comprend un capteur de pression statique (12) situé dans un étage de compresseur.
  3. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que :
    ledit moyen de traitement de signal (24, 26) comprend un moyen destiné à produire ledit signal de soutirage (ACON) pendant un intervalle de temps choisi.
  4. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que ledit deuxième moyen (20) possède des coupures bipolaires auxdites première et deuxième fréquences.
  5. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que ladite première fréquence est égale à 0,1 fois la vitesse de rotation du compresseur.
  6. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que ladite première fréquence est située entre 0,01 et 1 fois ladite fréquence de rotation et ladite deuxième fréquence est située entre 1 et 10 fois ladite fréquence de rotation.
  7. Dispositif de commande selon la revendication 6,
    caractérisé en outre en ce que ledit moyen de traitement de signal (24, 26) comprend un moyen (44a) destiné à produire ledit signal de soutirage (ACON) pendant un intervalle de temps fixe.
  8. Dispositif de commande selon la revendication 1, caractérisé en outre en ce que ledit moyen de traitement de signal (24, 26) comprend un moyen (44) destiné à modifier l'amplitude de ladite valeur mise en mémoire (32) en une valeur temporaire lors de la production dudit signal de soutirage (ACON) .
  9. Dispositif de commande selon la revendication 8, caractérisé en outre en ce que ladite valeur temporaire est inférieure à l'amplitude de ladite valeur mise en mémoire (32) lors de la production dudit signal de soutirage.
  10. Procédé destiné à éviter tout calage dans un compresseur rotatif, caractérisé par les étapes consistant à :
    détecter l'amplitude (PR3) des caractéristiques variant dans le temps de l'écoulement de compresseur à une largeur de bande entourant la fréquence de rotation du compresseur ;
    produire une valeur intégrale (38) en intégrant la différence entre ladite amplitude (PR3) et une valeur de calcul (32) de ladite amplitude ; et
    augmenter le débit massique de compresseur lorsque ladite valeur intégrale (38) dépasse une valeur de seuil.
  11. Procédé selon la revendication 10, caractérisé en outre par l'étape consistant à augmenter le débit massique pendant une durée fixe.
  12. Procédé selon la revendication 10, caractérisé en outre par l'étape consistant à réduire ladite valeur de calcul (32) pendant la production de ladite valeur intégrale (38).
  13. Procédé selon la revendication 10, caractérisé en outre en ce que ladite largeur de bande possède une fréquence de coupure inférieure comprise entre 0,01 et 1 fois ladite fréquence de rotation et une fréquence de coupure supérieure comprise entre 1 et 10 fois ladite fréquence de rotation.
EP96920104A 1995-04-24 1996-04-17 evitement du calage de compresseurs Expired - Lifetime EP0777828B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US42733495A 1995-04-24 1995-04-24
US427334 1995-04-24
US1318796P 1996-03-12 1996-03-12
US13187 1996-03-12
PCT/US1996/005309 WO1996034207A1 (fr) 1995-04-24 1996-04-17 Diagnostic et evitement du calage de compresseurs

Publications (2)

Publication Number Publication Date
EP0777828A1 EP0777828A1 (fr) 1997-06-11
EP0777828B1 true EP0777828B1 (fr) 2002-08-21

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EP96920104A Expired - Lifetime EP0777828B1 (fr) 1995-04-24 1996-04-17 evitement du calage de compresseurs

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EP (1) EP0777828B1 (fr)
AU (1) AU5850796A (fr)
DE (1) DE69623098T2 (fr)
WO (1) WO1996034207A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2804732B1 (fr) 2000-02-03 2002-04-12 Snecma Procede de detection precoce des instabilites aerodynamiques dans un compresseur de turbomachine
EP2193400B1 (fr) 2007-09-17 2014-12-10 Danmarks Tekniske Universitet Convertisseur de faisceau electromagnetique
EP2971700B1 (fr) 2013-03-14 2019-12-25 United Technologies Corporation Filtre de bruit de capteur de pression avant une détection de surtension pour une turbine à gaz
BR102013021427B1 (pt) 2013-08-16 2022-04-05 Luis Antonio Waack Bambace Turbomáquinas axiais de carcaça rotativa e elemento central fixo
US10037026B2 (en) 2014-09-25 2018-07-31 General Electric Company Systems and methods for fault analysis
WO2016087393A1 (fr) 2014-12-01 2016-06-09 Danmarks Tekniske Universitet Système et procédé de contraste de phase généralisé à longueurs d'onde multiples
CN110608187B (zh) * 2019-10-30 2024-08-06 江西理工大学 基于频率特征变化的轴流压气机失速喘振预测装置
CN114962305B (zh) * 2021-02-25 2023-09-26 中国航发商用航空发动机有限责任公司 压气机失稳在线检测方法、装置、系统、设备及介质
US20240255070A1 (en) * 2023-01-30 2024-08-01 The Boeing Company System, method, and valve assembly for surge protection

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4137710A (en) * 1977-01-26 1979-02-06 United Technologies Corporation Surge detector for gas turbine engines
IL94506A (en) * 1989-05-30 1993-07-08 United Technologies Corp Acceleration control for a gas turbine engine with duct pressure loss compensation
US5275528A (en) * 1990-08-28 1994-01-04 Rolls-Royce Plc Flow control method and means
JPH06147189A (ja) * 1992-11-11 1994-05-27 Hitachi Ltd 圧縮機の旋回失速防止装置
US5448881A (en) * 1993-06-09 1995-09-12 United Technologies Corporation Gas turbine engine control based on inlet pressure distortion

Also Published As

Publication number Publication date
DE69623098T2 (de) 2002-12-19
DE69623098D1 (de) 2002-09-26
EP0777828A1 (fr) 1997-06-11
WO1996034207A1 (fr) 1996-10-31
AU5850796A (en) 1996-11-18

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