EP3564492B1 - Messverfahren zum testen eines bauteils eines luftfahrzeugturbotriebwerks - Google Patents

Messverfahren zum testen eines bauteils eines luftfahrzeugturbotriebwerks Download PDF

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Publication number
EP3564492B1
EP3564492B1 EP19171739.6A EP19171739A EP3564492B1 EP 3564492 B1 EP3564492 B1 EP 3564492B1 EP 19171739 A EP19171739 A EP 19171739A EP 3564492 B1 EP3564492 B1 EP 3564492B1
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Prior art keywords
signals
sensors
iii
time lag
common
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English (en)
French (fr)
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EP3564492A1 (de
Inventor
Nicolas Raimarckers
Frederic Vallino
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • 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
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • 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
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/312—Air pressure
    • 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
    • F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
    • F05D2270/802—Calibration thereof

Definitions

  • the invention relates to a measurement method for a test of a part of an aircraft turbomachine.
  • test measurements are normally carried out.
  • these tests are carried out by means of sensors capable of measuring the same physical quantity and include a step of acquiring and processing output signals from these sensors.
  • EP 1630633 A2 discloses such a measurement method according to the prior art using electronic signals from different sensors to determine the state of health of a turbomachine. The signals are synchronized before their evaluation.
  • An object of the invention is to provide a measurement method for a test of a part of an aircraft turbomachine which is faster to perform.
  • the method according to the invention makes it possible to perform a measurement for a test of a part of an aircraft turbomachine which is particularly quick to perform.
  • step (iii) the output signals of the sensors are generally out of phase in time.
  • the signal synchronization step (iii) makes it possible to replace these signals in the same frame of reference before their processing in step (iv). Consequently, this processing of the signals is facilitated, which allows a significant saving of time in the execution of the measurement for the test.
  • processing unsynchronized analog signals is difficult in view of the prohibitive size of the files which are generated due to the quantity of data to be acquired and to be processed during such a measurement for a test.
  • the synchronization a posteriori of the signals from the pressure sensors is complex to implement by the engineer responsible for such processing. The method according to the invention is therefore faster and simpler to implement.
  • the method according to the invention is all the quicker and more efficient to execute when the signals supplied by the sensors are analogue and when the analogue signals are synchronized in analogue fashion in the preferred sense where they are placed in the same reference frame using the analog electronic signal preprocessing device.
  • measurements by analog signals allow a measurement of a physical quantity, for example a pressure, via another, for example an electric current, in a manner that is both continuous, faithful and of great magnitude. quality.
  • the method according to the invention makes it possible to fully exploit these advantages of the “analog” character of the signals without loss in speed or in efficiency during processing of these signals because they are advantageously synchronized in an analog manner before being processed. .
  • the method according to the invention also makes it possible to start and at least partially carry out processing of the signals in step (iv) without waiting for the end of the measurement for the test, and therefore without waiting for the end of their acquisition.
  • the step of processing a part of the signals is carried out in parallel with a step of acquiring another part of the signals comprising the signals synchronized in step (iii).
  • step (iv) of the method is carried out by means of a very sophisticated acquisition and processing system comprising the electronic processing device.
  • a high quality of the signals is thus obtained.
  • the fact that such signals generate a greater number of data to be managed is not a problem during the execution of the method according to the invention because the synchronization step (iii) allows a saving of time in the processing. of these signals.
  • the method according to the invention makes it possible to carry out a measurement for a test, the implementation of which is also more efficient.
  • an analog electronic device and an electronic processing device are well known to a person skilled in the art and their use allows faster and more efficient execution of the method according to the invention.
  • step (iii) comprises a step of adding a delay to each of the signals to be synchronized, the delay consisting of a positive, negative or zero time delay.
  • a reference signal is chosen in step (iii) and these signals are aligned with this reference signal by means of the addition of a delay.
  • the reference signal is one of the signals, the alignment delay of the reference signal on itself is obviously zero.
  • all the signals are thus synchronized, that is to say considered in the same time frame of reference without phase shift between them, which greatly simplifies their processing in step (iv).
  • the reference signal is the last signal generated. This may or may not be included in the signals to be synchronized.
  • the alignment delay is determined from a point and / or a zone common to the reference signal and to each of the signals to be synchronized.
  • the alignment delay of the reference signal on one of the signals is the delay required to align the point and / or the common area of the reference signal with the point and / or the associated common area of one of the signals.
  • this more preferred embodiment of the method makes it possible to take into account the periodic fluctuation of the output signals. Indeed, when a delay in aligning one of the signals with a reference signal is achieved from an identification of a common area, it may be that other portions of these two signals are not perfectly aligned due to local variations and / or disturbances of these two signals.
  • this more preferred embodiment of the method recommends a periodic evaluation of these variations and / or local disturbances of these two signals.
  • the part comprises at least one blade and / or at least one ferrule of the turbomachine.
  • the method then consists of a measurement method for testing at least one blade and / or at least one ferrule of an aircraft turbomachine.
  • the more preferred embodiment of the method is all the more advantageous as a period of one of the signals is able to be defined as a signal section during the passage of a vane of the turbomachine when in motion.
  • the variations in the alignment delay of one of the signals on a reference signal are particularly small between two consecutive blades, and the delay calculated for one blade can therefore be taken as a reference for the calculation of the next one by means of a optional use of the variation of the delay to update this reference.
  • this common zone consists of a top and / or a trough and / or a trough. or a rising edge and / or a falling edge of a curve representing each of the signals to be synchronized.
  • step (iii) consists in synchronizing the signals.
  • the signals synchronized in step (iii) consist of all the analog output signals.
  • the latter comprises a step of recording the signals processed in step (iv).
  • This step is preferably carried out using very sophisticated data acquisition, storage and recording techniques.
  • a high quality of the signals is thus obtained. Since the phenomena sought during these measurements for tests have very short characteristic times, they are thus advantageously better detected by means of these high quality signals.
  • the latter comprises a step of detecting at least one fault in the part on the basis of the signals processed in step (iv).
  • step (iii) is preceded by a step of setting the turbomachine in motion.
  • step (i) comprises a step of supplying pressure sensors.
  • the sensors are pressure sensors.
  • the pressure sensors are well known to a person skilled in the art and their use allows the detection of a class of phenomena corresponding to faults in the blades and / or the shrouds of the turbomachine when the latter is in motion.
  • the sensors are preferably pressure sensors.
  • a simple and efficient execution of the method according to the invention is then obtained.
  • step (i) comprises a step of supplying at least one device comprising at least three sensors positioned and oriented in a distinct manner
  • step (ii) comprises a step of positioning of at least one device near the part.
  • the use of a pressure sensor or of such a device provided with at least three sensors is particularly advantageous because it allows a particular embodiment of the invention consisting of a method of measuring an angle of an air flow for a test at the level of the at least one blade and / or a ferrule of an aircraft turbomachine.
  • the figure 1 illustrates a device 4 comprising three sensors 11, 12, 13, preferably pressure sensors, which are able to be used during an execution of the method according to one embodiment of the invention.
  • the sensors 11, 12, 13 are positioned and oriented in three distinct directions, these first two and the latter two respectively considered forming a clockwise oriented angle of between 60 to 75 degrees.
  • a large number of good quality analog signals are generated, synchronized, acquired and processed by executing the method according to the invention.
  • step (ii) of the method according to the invention is thus simplified and accelerated.
  • the figure 2 illustrates a positioning of the device 4 after an execution of step (ii) of the method according to the invention.
  • the positioning is shown in a schematic sectional plan view of a section 5 of a turbomachine comprising vanes 6, 7 and shrouds.
  • the turbomachine is preferably set in a rotational movement about the Z axis with a view to performing step (iii).
  • the device 4 comprising the sensors 11, 12 and 13 for its part remains fixed during the rotational movement of the turbomachine.
  • the positioning of the device 4 allows it to be in the path of the flows generated by the turbomachine, which advantageously makes it possible to process signals encoding air flow measurement information for a test of the blades 6, 7 and / or of the blades.
  • the sensors 11, 12, 13 are pressure sensors. Indeed, the sensors 11, 12, 13 make it possible to measure pressures in several directions in the same neighborhood, these pressures being due to air flows at the level of the turbomachine, and to deduce therefrom an angle of incidence thereof as a function of the position of the device 4 with respect to the blades 6, 7 and the turbomachine shrouds. This air flow angle measurement is particularly useful during a development test of turbomachine parts.
  • the sensors 11, 12, 13 are able to emit analog output signals which can be represented by pressure curves, portions of which 61, 62, 63, 71, 72, 73 are illustrated in figure 3 .
  • the references 61 and 71 designate portions of the curve representing a first output signal -1 from a first sensor 11, the references 62 and 72 designate portions of the curve representing a second output signal -2 from a second sensor 12, and the references 63 and 73 denote portions of the curve representing a third output signal -3 from a third sensor 13.
  • Each of the signals -1, -2, -3 can be broken down into periods comprising the periods 61 and 71 for the signal -1, periods 62 and 72 for signal -2, and periods 63 and 73 for signal -3.
  • the periods common to the three signals are 61, 62 and 63 on the one hand, defining the period 6 *, and 71, 72 and 73 on the other hand, defining the period 7 *.
  • the periods 6 * and 7 * correspond to the signals generated by the sensors during the passage of the blades 6 and 7 respectively.
  • the shift 8 between two consecutive blades 6, 7 is of the order of approximately 100 ⁇ s
  • the delay 612 or 613 between two signals -1 and -2, or -1 and -3 over the same period 6 * or 7 * is of the order of a few ⁇ s.
  • the delays 612 and 613 are due to the phase shifts between the signals -1, -2, -3 resulting from the different location and orientation of the sensors 11, 12 and 13.
  • the delays 612 and 613 are able to be determined over the period 6 * as being the time delays separating a top of the portion 61 from a top of the portion 62 and of the portion 63 respectively.
  • Another common area of signals -1, -2 and -3 over this period 6 * could have been used to determine these periods 612 and 613 without departing from the scope of the invention.
  • This common zone could be, for example, a hollow, an increasing or decreasing flank of the portions 61, 62 and 63.
  • step (iii) of the method signals -2 and -3 are synchronized with signal -1 by shifting them by delays 612 and 613 respectively.
  • the signals are brought back to the same time frame of reference, which simplifies their processing in step (iv) with a view to deducing test measurement information from the part.
  • the present invention relates to a measurement method for a test of a part of an aircraft turbomachine on the basis of analog output signals from sensors 11, 12, 13, the method comprising a step of synchronization by a device. analog of at least some of these signals 61, 71, 62, 72, 63, 73 preceding a step of processing by an electronic device of the synchronized signals.
  • the terms “first”, “second”, “third” and “fourth” are used only to differentiate the various elements and do not imply order between these elements.
  • the use of the verbs “to understand”, “to include”, “to include”, or any other variant, as well as their conjugations, can in no way exclude the presence of elements other than those mentioned.
  • the use of the indefinite article “a”, “a”, or of the definite article “the”, “the” or “the”, to introduce an element does not exclude the presence of a plurality of these elements.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Fluid Pressure (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Claims (13)

  1. Messverfahren zum Testen eines Bauteils einer Luftfahrzeugturbomaschine, umfassend die folgenden Schritte:
    (i) Bereitstellen:
    - des Bauteils;
    - von Sensoren (11; 12; 13), um eine gleiche physikalische Größe zu messen, und geeignet, analoge Signale bereitzustellen, die der gleichen physikalischen Größe entsprechen;
    - eine analoge elektronische Vorverarbeitungsvorrichtung, die mit den Sensoren (11; 12; 13) gekoppelt ist, um aus den Sensoren (11; 12; 13) stammende Signale vorab zu verarbeiten; und
    - eine elektronische Verarbeitungsvorrichtung, die mit der elektronischen Vorverarbeitungsvorrichtung gekoppelt ist, um mindestens eine Information abzuleiten, die sich auf die physikalische Größe bezieht;
    (ii) Positionieren der Sensoren (11; 12; 13) an separaten Stellen, um eine gleiche physikalische Größe, die mindestens teilweise durch das Bauteil beeinflusst wird, an diesen unterschiedlichen Stellen zu messen;
    (iii) Synchronisieren, auf analoge Weise und mithilfe der analogen elektronischen Vorverarbeitungsvorrichtung, der aus den Sensoren (11; 12; 13) stammenden analogen Signale (61, 71; 62, 72; 63, 73), sodass diese Signale (61, 71; 62, 72; 63, 73) in einem gleichen Bezugssystem neu platziert werden;
    (iv) Verarbeiten der im vorgegangenen Schritt synchronisierten Signale (61, 71; 62, 72; 63, 73) mithilfe der elektronischen Verarbeitungsvorrichtung, um mindestens eine Information, die sich auf die physikalische Größe bezieht, und eine Testinformation des Bauteils abzuleiten.
  2. Verfahren nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass der Schritt (iii) einen Schritt des Hinzufügens einer Verzögerung (612; 613) zu jedem der Signale (61, 71; 62, 72; 63, 73) umfasst, wobei die Verzögerung (612; 613) aus einer positiven, negativen oder Zeitverzögerung von null besteht.
  3. Verfahren nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass der Schritt (iii) die folgenden Unterschritte umfasst:
    - Auswählen eines Bezugssignals (61, 71) aus den Signalen (61, 71; 62, 72; 63, 73);
    - Identifizieren eines gemeinsamen Bereichs für jedes der Signale (61, 71; 62, 72; 63, 73);
    - Bestimmen der Verzögerung (612; 613), die jedem der Signale (61, 71; 62, 72; 63, 73) hinzuzufügen ist, wobei die Verzögerung (612; 613) eine Verzögerung ist, die die gemeinsamen Bereiche des Bezugssignals (61, 71) und jedes der Signale (61, 71; 62, 72; 63, 73) trennt.
  4. Verfahren nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass der Schritt (iii) die folgenden Unterschritte umfasst:
    - Zerlegen jedes der Signale (61, 71; 62, 72; 63, 73) in eine Sammlung von Zeiträumen (61; 62; 63; 71; 72; 73);
    - Identifizieren gemeinsamer Zeiträume (61, 62, 63; 71, 72, 73) für jedes der Signale (61, 71; 62, 72; 63, 73);
    - Bestimmen einer Schwankung für jeden der gemeinsamen Zeiträume (61, 62, 63; 71, 72, 73) jedes der Signale (61, 71; 62, 72; 63, 73), wobei die Schwankung aus einer positiven, negativen oder Zeitschwankung von null der Verzögerung (612; 613) besteht, die jedem der Signale (61, 71; 62, 72; 63, 73) hinzugefügt wird;
    - Hinzufügen der Schwankung zu jedem der gemeinsamen Zeiträume (61, 62, 63; 71, 72, 73) jedes der Signale (61, 71; 62, 72; 63, 73).
  5. Verfahren nach einem der Ansprüche 3 oder 4, dadurch gekennzeichnet, dass der für jedes der Signale (61, 71; 62, 72; 63, 73) identifizierte gemeinsame Bereich aus einem Scheitelpunkt und/oder einem Tiefpunkt und/oder einer steigenden Flanke und/oder einer fallenden Flanke einer Kurve besteht, die jedes der Signale (61, 71; 62, 72; 63, 73) darstellt.
  6. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Schritt (iii) aus einer Synchronisierung der analogen Ausgangssignale besteht.
  7. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass es einen Schritt der Aufzeichnung der im Schritt (iv) verarbeiteten Signale umfasst.
  8. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass es einen Schritt des Erfassens mindestens eines Defekts des Bauteils auf Grundlage der im Schritt (iv) verarbeiteten Signale umfasst.
  9. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass dem Schritt (iii) ein Schritt des In-Bewegung-Setzens der Turbomaschine vorangeht.
  10. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Schritt (i) einen Schritt des Bereitstellens von Drucksensoren (11, 12, 13) umfasst.
  11. Verfahren nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Schritt (i) einen Schritt des Bereitstellens mindestens einer Vorrichtung (4) umfasst, die mindestens drei Sensoren (11, 12, 13) umfasst, die auf separate Weise positioniert und ausgerichtet sind, und dadurch, dass der Schritt (ii) einen Schritt der Positionierung der mindestens einen Vorrichtung (4) in der Nähe des Bauteils umfasst.
  12. Messverfahren zum Testen mindestens einer Schaufel und/oder einer Halterung (6, 7) einer Luftfahrzeugturbomaschine nach einem der vorstehenden Ansprüche.
  13. Messverfahren eines Winkels eines Luftstroms zum Testen in Bezug auf mindestens eine Schaufel und/oder eine Halterung (6, 7) einer Luftfahrzeugturbomaschine nach einem der Ansprüche 10 oder 11.
EP19171739.6A 2018-05-02 2019-04-30 Messverfahren zum testen eines bauteils eines luftfahrzeugturbotriebwerks Active EP3564492B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE201805281A BE1026251B1 (fr) 2018-05-02 2018-05-02 Méthode de mesure pour un test d'une pièce d'une turbomachine d'aéronef

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EP3564492A1 EP3564492A1 (de) 2019-11-06
EP3564492B1 true EP3564492B1 (de) 2021-04-21

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Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4896537A (en) * 1988-06-02 1990-01-30 Westinghouse Electric Corp. Shrouded turbine blade vibration monitor
US7769507B2 (en) * 2004-08-26 2010-08-03 United Technologies Corporation System for gas turbine health monitoring data fusion
US8482434B2 (en) * 2010-09-17 2013-07-09 United Technologies Corporation Wireless sensor for an aircraft propulsion system
FR2996302B1 (fr) * 2012-10-01 2014-10-17 Snecma Procede et systeme de mesure a capteurs multiples

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* Cited by examiner, † Cited by third party
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BE1026251B1 (fr) 2019-12-02
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