EP1647801A2 - Vorrichtung zum Messen der axialen Verschiebung von Turbinenschaufelspitzen auf einem Prüfstand und deren Verwendung - Google Patents

Vorrichtung zum Messen der axialen Verschiebung von Turbinenschaufelspitzen auf einem Prüfstand und deren Verwendung Download PDF

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Publication number
EP1647801A2
EP1647801A2 EP05109335A EP05109335A EP1647801A2 EP 1647801 A2 EP1647801 A2 EP 1647801A2 EP 05109335 A EP05109335 A EP 05109335A EP 05109335 A EP05109335 A EP 05109335A EP 1647801 A2 EP1647801 A2 EP 1647801A2
Authority
EP
European Patent Office
Prior art keywords
blades
camera
images
image
probe
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Withdrawn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
EP05109335A
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English (en)
French (fr)
Inventor
Nadine Harivel
Vincent Leignel
Denis André Jean Lisiecki
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1647801A2 publication Critical patent/EP1647801A2/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • 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
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position

Definitions

  • the invention relates to a device for measuring the axial displacement of the blade tips of a turbomachine for ground tests and a method of using the device.
  • a turbojet engine generally comprises a fan, one or more compressor stages, a combustion chamber, one or more turbine stages and an ejection nozzle.
  • the blower, the compressor and the turbine comprise rotors whose vanes are rotated about the axis of the turbojet engine.
  • the rotating elements of the turbojet engine are subjected, in operation, to numerous mechanical and thermal stresses, which induce expansions and displacements within their structures. It is therefore important, prior to the development of a turbojet engine, to implement ground tests to quantify these displacements and dimension the structure of the turbojet engine accordingly.
  • the invention relates to measuring the axial displacement of the blade tips of a rotor of a turbomachine, in particular a rotor of a turbojet engine.
  • This measurement is generally performed in ground mode in a test bench.
  • a strip of optical fibers is used, housed at the right of the blades in a bore of their retention housing, provided for this purpose.
  • the bar comprises an alignment of juxtaposed optical fibers in which light beams are emitted; the beams are or are not reflected by the top of the blades, according to whether they are at the right of the latter or not.
  • the axial displacement of the blade tips is deduced from the number of fibers whose beam is reflected.
  • This device has various disadvantages.
  • these optical fibers are fragile and have a significant probability of rupture during the introduction of the bar or its transport.
  • the implementation and implementation on the turbojet of such a device is also very restrictive.
  • the aim of the invention is to propose a device that overcomes the disadvantages mentioned above.
  • the invention relates to a device for measuring the axial displacement of the top of the vanes of a rotor of a turbomachine, for ground tests, characterized in that it comprises means for taking pictures and conduction of images arranged to be implanted at the right of the blades and connected to remote means of image acquisition.
  • the invention it is possible to measure the axial displacement of the blade tips by means of a device, whose image taking and image conduction means have easy access to the blades, providing images with a large number of images. good definition thanks to its image acquisition means, remote and therefore placed in a place of little constraint, the device having a longer life than the devices of the prior art.
  • the device comprises means for generating light.
  • the device comprises synchronization means of the light generating means and image acquisition means.
  • the synchronization means are controlled by the rotation frequency of the blades.
  • the device comprises image processing means connected to the image acquisition means.
  • the image-taking and image-conduction means comprise a fiberscope.
  • the image-taking and image-conduction means comprise an endoscope.
  • the invention also relates to a method for measuring the axial displacement of the top of the vanes of a rotor of a turbomachine for ground tests with the device above.
  • the invention is particularly applicable to measuring the axial displacement of the top of the blades of a rotor of a turbojet, but it goes without saying that the applicant does not intend to limit the scope of its protection to this application alone .
  • the invention applies to any turbomachine comprising a rotor with vanes; the term "ground tests” means tests performed on a test bench on the ground as opposed to tests in air operation for a turbojet engine.
  • the tips of the vanes of its rotors can undergo axial displacements on the axis of the turbojet engine, between their position when the engine is stopped. turbojet engine and their operating position. These displacements must be measured, prior to the commissioning of a turbojet, in order to be able to model the behavior of the blades in operation and size the turbojet engine accordingly.
  • one sets up devices for measuring the axial displacements of the top of the blades used during ground tests of the turbojet engine. In the latter, the turbojet engine is placed in a test bench and put into operation.
  • a device 1 for measuring the axial displacement of the blade tip of a turbojet rotor according to the invention will be described, in connection with the measurement of the axial displacement of the top of the blades 2 of a compressor of a turbojet.
  • These blades 2 extend radially around the axis 3 of the turbojet, around which they are rotatably mounted. They are contained in a casing 4.
  • the function of the device 1 is to measure the axial displacement of the top of the blades 2 during operation of the turbojet engine during ground tests.
  • the device comprises image-taking and image-conduction means 5, which here comprise an optical probe 5, which may in this case be a fiberscope or an endoscope, as will be seen below.
  • the probe 5 is housed in a bore 9 of the compressor casing 4, which is specially drilled for the ground tests. It is placed at the right of the blades 2 to take pictures of their summit.
  • the optical probe 5 is connected to image acquisition means 6, whose function here is to convert the images into a digital video signal, which may comprise, for example, a digital camera or a sensor.
  • image acquisition means 6 whose function here is to convert the images into a digital video signal, which may comprise, for example, a digital camera or a sensor.
  • a digital camera 6 of the CCD type which comprises an electronic shutter that can be opened or closed to make or not the acquisition of images.
  • the probe 5 ensures the taking of pictures at the level of the blades 2 and the conduction of the images towards the camera 6.
  • the camera 6 can either be connected to the probe 5 at its end opposite to that opposite the apex of the 2, or be connected to the probe 5 by additional means of conduction images, for example optical fibers.
  • the camera 6 is connected to means 8 for processing the video signal that it transmits, by appropriate means.
  • the camera 6, as well as the processing means 8, are contained in a computer 7, shown schematically in Figure 1 by a tower and a screen.
  • a device 10 for generating light in this case a strobe 10, is provided, connected to the optical probe 5 by optical fibers 11.
  • the stroboscope 10 and the camera 6 are controlled by a device 12 for synchronizing the flashes of the stroboscope 10 and the electronic shutter of the camera 6.
  • the synchronization device 12 is connected to the stroboscope 10 via means 13 of coupling optical, well known to those skilled in the art.
  • the synchronization device 12 is also connected to the camera 6, which it controls, as well as to the optical probe 5, which allows looping of its servocontrol.
  • the turbojet comprises means for counting the speed motor, that is to say here the frequency of rotation of the compressor blades 2, not shown, connected to a divider 14 which controls the synchronization device 12, to which it is connected by appropriate means.
  • the operation of the device 1 for measuring the axial displacement of the top of the blades 2 of the compressor will now be explained in more detail, in relation to a particular measuring method.
  • the device 1 is used here to measure the axial displacement of the top of the blades 2 of the turbojet compressor, in this case the axial displacement of their leading edge.
  • the method could easily be adapted to measure the axial displacement of their trailing edge.
  • the optical probe 5 is mounted in its receiving bore 9 of the housing 4.
  • the probe 5 may comprise a thread cooperating with a thread of the bore 9 and / or be inserted with a seal.
  • the bore 9 is pierced from outside the housing 4 and opens on its inner wall, near the top of the blades 2.
  • the probe 5 comprises an optical system for taking pictures and conduction images.
  • the probe 5 can be either a fiberscope or an endoscope, which will be described later.
  • a transparent window can be arranged at the internal orifice of the bore 9, in order to ensure the continuity of the gas stream and thus not to disturb the flow of the latter, while allowing images to be taken by the probe 5.
  • the probe 5 also ensuring the tightness of the bore 9. Moreover, the probe 5 itself can ensure, by its end portion, the continuity of the gas stream.
  • the probe 5 is connected to the image acquisition means 6, here the digital camera 6.
  • the camera 6 can be directly connected to the probe 5, if it is not so placed in a too crowded location of the turbojet engine and that it does not suffer from its operating regime in this place. It is well to this extent deported means of shooting.
  • the camera 6 can be deported further still, for example on a structure of the turbojet, connected to the probe by additional means of conduction images, for example optical fibers.
  • the camera 6 is then connected to the image processing means 8 by appropriate means, typically electrical conductors.
  • the camera 6 can also be directly incorporated in the computer 7, as in the case in question, connected to the probe by optical fibers.
  • the computer 7 is here located in a control room of the test bench in which the turbojet engine is disposed, in this case about ten meters from the probe 5. It also comprises the means 8 for processing the images to which the camera 6 is connected.
  • the strobe 10 is here placed on or near the turbojet, and connected to the probe by the optical fibers 11, arranged in a circular arc, closed or not, around the optical probe 5.
  • the strobe flashes light that illuminate, through the optical fibers 11, the space of the turbojet engine located right of the probe 5, the inner side, and therefore a possible blade 2 passing at this point at the time of the flash.
  • a blade 2 is placed at the right of the probe 5 and a first shot is taken, when stopped, which gives the position at the stop of the top of the blades 2.
  • the strobe 10 is lit synchronously with the opening of the electronic shutter of the camera 6, which thus acquires images of the top of the blade 2, transmitted to it by the probe 5 and the optical fibers of conduction images.
  • This first shot also makes it possible to perform optical adjustment of the probe 5 and adjustment of the power of the stroboscope 10 in order to obtain an optimal contrast of the image. It also makes it possible to ensure the synchronization of the emission of a flash by the strobe 10 with the opening of the shutter of the camera 6, so that the camera actually acquires an image when the flash is on, it is ie the top of the dawn 2 lit up.
  • the turbojet engine is operated. When a predetermined speed is reached, shots of the top of a particular blade 2 are taken. Shooting can be done continuously as the speed of the engine changes, the signal emitted by the camera 6 being a video signal.
  • the synchronization device 12 is controlled by the divider 14. The latter is controlled by the engine speed counting device, which serves as a time base for the device.
  • the divider 14 is arranged to send a signal to the synchronization device 12 every "n" turns of the turbojet engine. This signal causes the synchronization device 12 to transmit a signal for sending a flash by the stroboscope 10 and synchronously acquiring an image by the camera 6 by opening its shutter.
  • the blade tip 2 is illuminated by the flash and the shutter of the camera 6 is open to acquire the image of the illuminated blade tip 2.
  • the number "n” is arranged so that the trigger signal always corresponds to the same blade 2.
  • the same blade tip 2 is located at the right of the probe 5 at each emission of a strobe flash and the opening of the shutter of the camera 6.
  • the synchronization device is for this purpose initialized on this particular blade 2, hereinafter referred to as the blade 2, and divides the frequency of rotation or frequency of passage of the blades 2 by "n", so that each image is taken after n turns of the blade 2.
  • the number “n” is arranged to obtain a frequency of the trigger signal which is equal to the desired acquisition frequency for the camera 6.
  • the camera 6 is arranged to capture 50 images per second, "n” being arranged so that the rotation frequency of the blades 2, divided by "n", is equal to 50 Hz or close to 50 Hz.
  • the duration of illumination of the blade tip and the duration of opening of the shutter of the camera 6 are calibrated according to the turbojet engine speed to obtain the most contrasting images possible, but the times are not too low for that the illumination and the acquisition are sufficient, according to the sensitivity of the video sensors of the camera 6.
  • the synchronization of the strobe 10 and the electronic shutter of the camera 6 is done continuously according to the turbojet engine speed . At each image acquisition, the entire synchronization system, which is looped, is synchronized again with respect to the turbojet engine speed.
  • the camera 6 is a camera interlaced frames, each image being acquired in an image of which every other line of all lines is illuminated, alternately every other image.
  • the images are thus acquired at 25 Hz for each of the two sets of lines of a line on two.
  • the images of each line are processed to be interpolated by calculation between two successive taps and assigned to them, for the unlit lines, the value calculated by the interpolation. It goes without saying that the images could be complete as soon as they are acquired.
  • the shutter of the camera 6 can remain open, the flash being lit only during the passage of the blade 2 every "n" turns.
  • the video would then have black periods, or just with ambient light, and illuminated periods.
  • a constant light could illuminate the blades 2, the shutter of the camera 6 being set to be open only every "n" turns of the blade 2.
  • the speed of opening and closing of the shutter of the camera 6 being smaller than that of the ignition and the extinction of the strobe 10, it is better that the capture accuracy of the blade 2 is provided by the strobe 10.
  • the images acquired by the camera 6 are processed in the processing means 8 located in the computer 7. Once the processed images to be complete on all their lines, they are analyzed. It is possible that stray lights, other than the image light from the top of the blade 2, appear on the images. These parasitic lights may in particular come from various reflections in the enclosure containing the blades 2, for example on the walls of the blades 2 or on their feet, reflections related to the coupling between the optical fibers 11 of the strobe 10 and the probe 5. These parasitic lights are filtered in the processing device 8, either by luminous thresholding of the image, or by deleting portions of the image having identifiable parasitic lights, which we know a priori that they can not correspond to the apex of the image. 2.
  • the signal noise is also suppressed using a low-pass filter. This extracts the image from the top of the blade 2 of the image. Next, the closest point to the edge of the image is sought to take account of any misalignments of the probe 5 with the blade 2, for example by scanning the image from the bottom upwards in order to obtain the position of the dawn top 2.
  • the images are in digital format and therefore consist of pixels.
  • the objective of the method of use of the device 1 being the measurement of the axial displacement of the top of the blades 2, the positions of the blades 2 at the various operating speeds of the turbojet engine are compared to their calculated position when stopped; these differences in pixel positions must then be converted into distances.
  • it may be previously carried out the acquisition of images of a control object, of known dimensions, placed at a distance from the probe 5 substantially equal to that at which is placed the top of the blades 2, in order to calculate a conversion factor of pixels in millimeters, for example.
  • the axial displacements of the blades represent, for a blower, 10 to 20 mm, for a high-pressure compressor of a turbofan engine, 5 to 10 mm, for a low-pressure compressor, 1 to 5 mm .
  • the device of the invention and to its method of use, it is therefore possible to measure, in real time, on a turbojet engine operating during ground tests, the axial displacements of the top of the blades by means of acquisition of deported images with respect to the shooting means, to which they are connected by means means of conduction of images.
  • the imaging frequency of the device is adapted in real time to the operating speed of the turbojet engine.
  • the probe of the device 1 is a fiberscope 5a. It comprises a flexible optical conduit 15, comprising a plurality of optical fibers in parallel, in this case numbering 10,000.
  • the optical conduit 15 is bonded to a ferrule 16, housed in a sleeve 17 for coupling to the casing 4 of the compressor.
  • the sleeve 17 comprises a head portion 18 for connecting the fibers 11 connected to the stroboscope 10, in which the ferrule 16 is housed, which is extended by a hollow tubular portion 19 forming with it a bearing shoulder 20 on the housing 4
  • the ferrule 16 may also extend in the tubular portion 19.
  • the latter has an external thread 21, which is screwed into a corresponding bore of the casing 4, thereby sealing the assembly.
  • the ferrule 16 opens into the inner duct of the tubular portion 19, which extends through the bore 9 of the casing 4, and is therefore located at the place of passage of the leading edge of the top of the blades 2, which it takes images.
  • the fibers 11 connected to the stroboscope 10, not shown, here extend in a partial arc around the ferrule 16.
  • the fiberscope 5a is connected directly to the camera 6 by its optical conduit 15.
  • the fiberscope 5a can be mounted in very difficult to access and congested areas.
  • the images obtained are diaphragmed by the circular entrance pupil of the light of the ferrule 16, forming means of shooting.
  • the images are discretized because of the juxtaposition of the optical fibers.
  • the probe of the device 1 is an endoscope 5b. It comprises a rigid optical conduit 22.
  • This conduit 22 typically comprises a metal conduit, in which are arranged in series lenses, spaced apart from each other by their focal length, not shown.
  • the rigid optical conduit 22 is housed in a sleeve 23 of connection to the casing 4 of the compressor.
  • the sleeve 23 comprises a head portion 24, connecting the fibers 11 connected to the stroboscope 10, and a hollow tubular portion 25.
  • the tubular portion 25 has an external thread 26, which is screwed into a corresponding bore of the housing 4, thus ensuring the tightness of the whole.
  • the optical duct 22 opens into the internal duct of the tubular portion 25, which is extended by the bore 9 of the casing 4, and is therefore at the right of the place of passage of the leading edge of the top of the blades 2, which she takes the images.
  • the fibers 11 connected to the stroboscope 10, not shown, here extend in a partial arc around the optical duct 22.
  • the camera 6 can be mounted at the outer end of the optical conduit 22, if space permits, by a connector.
  • the optical conduit 22 thus provides a shooting function, by its internal end, and an image conduction function to the camera 6.
  • the optical conduit 22 can also be connected to other means of conduction images typically optical fibers, in turn connected to the camera 6.
  • the endoscope 5b is slightly more restrictive to mount than the fiberscope 5a.
  • the images that it takes are not discretized as for the fiberscope 5a, the lighting being able to be better, which provides images of better resolution.
  • the field of the filmed object if it is more precise, is on the other hand smaller, because of the magnification by the lenses; this magnification also implies that the apparent speed of the blades in front of the endoscope 5b is all the greater, which requires a better precision in the shooting so that the images are not too fuzzy and do not involve drag or trace too important because of the movement of the blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Length Measuring Devices By Optical Means (AREA)
EP05109335A 2004-10-12 2005-10-07 Vorrichtung zum Messen der axialen Verschiebung von Turbinenschaufelspitzen auf einem Prüfstand und deren Verwendung Withdrawn EP1647801A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0452343A FR2876444B1 (fr) 2004-10-12 2004-10-12 Dispositif de mesure du deplacement axial du sommet des aubes d'une turbomachine pour des essais au sol et procede d'utilisation du dispositif

Publications (1)

Publication Number Publication Date
EP1647801A2 true EP1647801A2 (de) 2006-04-19

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EP05109335A Withdrawn EP1647801A2 (de) 2004-10-12 2005-10-07 Vorrichtung zum Messen der axialen Verschiebung von Turbinenschaufelspitzen auf einem Prüfstand und deren Verwendung

Country Status (4)

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US (1) US20060088414A1 (de)
EP (1) EP1647801A2 (de)
JP (1) JP2006125393A (de)
FR (1) FR2876444B1 (de)

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CN103323461A (zh) * 2013-06-14 2013-09-25 上海大学 一种非接触式的风力发电机叶片运动在线检测方法
FR3079031A1 (fr) * 2018-03-16 2019-09-20 Safran Aircraft Engines Dispositif ameliore de test d'eprouvette pour turbomachine

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US9488467B2 (en) * 2010-10-28 2016-11-08 General Electric Company System and method for monitoring in real time, a gap between portions in a machine
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US8687206B2 (en) * 2012-05-29 2014-04-01 United Technologies Corporation Optical detection of airfoil axial position with NSMS
FR3094397B1 (fr) 2019-03-25 2021-05-14 Safran Aircraft Engines Dispositif et procédé de contrôle non destructif d’un rotor d’une turbine contrarotative d’une turbomachine d’aéronef
DE102019113154A1 (de) * 2019-05-17 2020-11-19 Schenck Rotec Gmbh Verfahren und Vorrichtung zur Dehnungsmessung an einem fliehkraftbelasteten Körper
CN114563148B (zh) * 2022-03-04 2023-09-22 中国航发沈阳发动机研究所 一种航空发动机进口导叶角度调节机构刚度试验结构

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FR3079031A1 (fr) * 2018-03-16 2019-09-20 Safran Aircraft Engines Dispositif ameliore de test d'eprouvette pour turbomachine

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JP2006125393A (ja) 2006-05-18
FR2876444B1 (fr) 2007-06-22
US20060088414A1 (en) 2006-04-27
FR2876444A1 (fr) 2006-04-14

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