EP3548839A1 - Procédé et dispositif de mesurage de dommages d'un composant creux d'avion ou de turbine à gaz - Google Patents

Procédé et dispositif de mesurage de dommages d'un composant creux d'avion ou de turbine à gaz

Info

Publication number
EP3548839A1
EP3548839A1 EP17808072.7A EP17808072A EP3548839A1 EP 3548839 A1 EP3548839 A1 EP 3548839A1 EP 17808072 A EP17808072 A EP 17808072A EP 3548839 A1 EP3548839 A1 EP 3548839A1
Authority
EP
European Patent Office
Prior art keywords
sensor
component
contour
outer contour
damage
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Withdrawn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
EP17808072.7A
Other languages
German (de)
English (en)
Inventor
Christian Schlosser
Felix JAHN
Michael Ernst
David KÜSTNER
Christoph Hess
Daniel ERDELMEIER
Thorsten SCHÜPPSTUHL
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.)
Lufthansa Technik AG
Original Assignee
Lufthansa Technik AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Lufthansa Technik AG filed Critical Lufthansa Technik AG
Publication of EP3548839A1 publication Critical patent/EP3548839A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/02—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness
    • G01B21/04—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness by measuring coordinates of points
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/24—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
    • G01B11/2441—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures using interferometry
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B17/00—Measuring arrangements characterised by the use of infrasonic, sonic or ultrasonic vibrations
    • G01B17/02—Measuring arrangements characterised by the use of infrasonic, sonic or ultrasonic vibrations for measuring thickness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/004—Measuring arrangements characterised by the use of mechanical techniques for measuring coordinates of points
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/004—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring coordinates of points
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G01N29/06—Visualisation of the interior, e.g. acoustic microscopy
    • G01N29/0654—Imaging
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/22—Details, e.g. general constructional or apparatus details
    • G01N29/26—Arrangements for orientation or scanning by relative movement of the head and the sensor
    • G01N29/265—Arrangements for orientation or scanning by relative movement of the head and the sensor by moving the sensor relative to a stationary material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/02—Indexing codes associated with the analysed material
    • G01N2291/028—Material parameters
    • G01N2291/02854—Length, thickness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/26—Scanned objects
    • G01N2291/269—Various geometry objects
    • G01N2291/2693—Rotor or turbine parts
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/26—Scanned objects
    • G01N2291/269—Various geometry objects
    • G01N2291/2694—Wings or other aircraft parts

Definitions

  • the invention relates to a device for damage measurement of a hollow aircraft or gas turbine component with the features of the preamble of claim 1 and a method for damage measurement of a hollow aircraft or gas turbine component with the features of the preamble of claim 7.
  • Aircraft components are exposed to high stress during operation. In addition to components made of composite materials, such as structural components or metallic components, such as suspension components, this can lead to a defective cracking, especially in the components of the aircraft engine. Similar damage patterns are also present in other gas turbines, such as stationary gas turbines. Combustor components are particularly affected by the formation of cracks in gas turbines. For reasons of weight, hollow components are used wherever possible, provided that the strength of the components permits this.
  • Cracks are local material separations within a structure or within a component. Cracking is typically a local event in the microstructure of the surface, which is usually caused by lattice defects in the microstructure or by cyclical operating loads. As a rule, cracks spread perpendicular to the normal stress. This spread is referred to as normal voltage controlled. In the case of gas turbine parts cracks caused by high thermal and mechanical stress. On the one hand, the cracking is caused by the prevailing high temperatures, and on the other hand, the vibrations from the high-pressure compressor and the high-pressure turbine promote crack growth and cracking. In addition, short-term thermal material stresses during starting of the gas turbine and possibly during the starting phase of the aircraft favor the formation of cracks.
  • Solid particles sucked into the gas turbine contribute greatly to the erosion of gas turbine components.
  • the permanent thermal stresses during the operating phase of the gas turbine cause the geometric shape of the gas turbine components to undergo a change. It is often problematic to accurately determine the shape deviation with respect to the original contour after erosion or deformation.
  • the main problem is to detect cracks and changes in geometry (such as erosion) during operation and to repair the components by appropriate measures. Due to the individually different crack or damage characteristics, this is often difficult.
  • Known damage assessment methods include a number of nondestructive testing methods.
  • Presently used methods include, for example, the dye penetration method, the ultrasonic inspection, the eddy current inspection, the X-ray inspection and the magnetic particle inspection. If the damage measurement is carried out manually with the corresponding sensors, the quality of the damage measurement depends very much on the experience and the conscientiousness of the person testing. Furthermore, the results must be logged, which has a very high outlay, particularly in the case of paper-based documentation. Thus, damage measurement requires a high level of training and a very high level of qualification of the examiner.
  • No. 7,921,575 B2 discloses arranging a sensor for measuring the outer contour and an ultrasonic sensor for measuring possible internal damage points of a turbine blade on a measuring head.
  • the determined measurement data are fed to a processing device for further processing and storage of the measured values.
  • a display device connected to the processing device is provided, on which the determined measured values are displayed.
  • a device for damage measurement of a hollow aircraft or gas turbine component with a coordinate measuring arm on which a first sensor device with an outer contour sensor for detecting the outer contour of the component and a second sensor device with an ultrasonic sensor for detecting the contour of Cavity is provided in the component proposed, wherein the basic idea of the invention is to be seen in that a third sensor device with a white light interferometer and / or a laser triangulation sensor is provided on the coordinate measuring arm.
  • the proposed device thus comprises a coordinate measuring arm with three different sensor types.
  • an external contour sensor is provided, for example, in the form of a probe or a contactless contour scanner, by means of which the outer contour of the component is detected.
  • the position of the component in relation to a reference coordinate system can be detected, which is defined by the coordinate measuring arm.
  • the detection of the position and the shape of the leading edge is of particular importance.
  • larger damage locations in the outer surface can already be localized by the outer contour sensor.
  • a second sensor device with an ultrasonic sensor is provided on the coordinate measuring arm, with which the inner contour of the cavity of the component is detected.
  • the inner contour of the cavity of the component is the contour, which is independent of the operating time subject to any wear and thus always corresponds to the contour of the component after production so the new contour.
  • the inner contour can thus be used as reference contour for Evaluation of the wear of the outer contour can be used.
  • a third sensor device with a white light interferometer is provided, which allows a very accurate measurement of the wear points in the range of +/- 10 nanometers.
  • a laser triangulation sensor which likewise permits a very accurate measurement of the wear points with an accuracy of +/- 1 ⁇ m in the depth direction and +/- 7 to 8 ⁇ m in the width.
  • the location of damage localized with the first sensor device can be measured with a very high accuracy.
  • the Koordinatenmessarm can thus be understood as a kind of sensor system with multiple sensor devices, with the location of the damage points to the cavity so the reference contour can be detected in addition to the location of the damaged areas. Furthermore, the geometry of the damaged areas can be measured with a very high accuracy. By knowing the reference contour and the measured outer contour, the thickness profile of the component wall in the circumferential direction, and in particular the thickness in the region of the points of damage, can be measured with a very high degree of accuracy.
  • all sensor devices have a defined position on the coordinate measuring arm.
  • a precisely detectable orientation and position of the sensor devices, in particular the second and third sensor device can be determined at the time of the measurement.
  • This allows a more accurate assignment of measured values of the second and / or third sensor device to a position and orientation on the outer contour, which has a positive effect on the accuracy of the damage measurement.
  • the second and / or third sensor device has a defined position relative to the outer contour sensor of the first sensor device, as a result of which a higher accuracy can be achieved in damage measurement.
  • a processing device for processing the determined measured values and an assistance system with a display device for displaying the further processed measured values can be provided.
  • the determined measured values can be processed further directly and displayed on the display device of the assistance system for assisting the person handling it.
  • the processing device and / or the assistance system may in particular have a memory unit for storing the determined and further processed measured values.
  • the logging can be omitted and the measured values are stored in digital form, so that they can be further used as needed in a processing device for processing the component and in particular for controlling appropriate order and processing machines for re-contouring of the component.
  • component-related parameters and / or repair specifications may be stored in the memory unit according to a further preferred embodiment, wherein on the display device further in dependence on the determined measured values and taking into account the component-related characteristics
  • the component-related parameters and repair specifications can be used to additionally simplify the measurement recording by using the operating parameter son corresponding instructions are communicated via the display device. For example, it may be necessary to require further measurement of the same site of damage when detecting specific damage locations, which requires special measurements that are only performed in this case.
  • the first and / or second and / or third sensor device can be controlled by the processing device and / or the assistance system.
  • the measurement of the component with the third sensor device with the white light interferometer and / or the laser triangulation sensor can be controlled by the measured values determined by the first sensor device.
  • a clamping device in which the component can be fixed, and a fourth sensor device can be provided which detects the position of the component relative to the clamping device or with respect to a reference point or reference coordinate system.
  • the clamping device fixes the component, and the fourth sensor device detects the basic orientation of the component.
  • the fourth sensor device is assigned to the clamping device, so that it is independent of the coordinate measuring arm.
  • the measured values of the fourth sensor device can then be used to actuate the coordinate measuring arm during the movement into a component-individualized initial position of the measured value recording in the direction of the component.
  • the position or reference position of the component can be determined with the coordinate measuring arm, and a coordinate system are placed in the determined reference position.
  • a method for damage measurement of a hollow aircraft or gas turbine component with a coordinate measuring arm, with a first sensor device with an outer contour sensor and a second sensor device with an ultrasonic sensor is proposed, wherein in particular it is proposed that a third sensor device with a white light interferometer and / or a laser triangulation sensor is provided, and the damage measurement is carried out by a combination of the measured values of the first, second and third sensor device.
  • the damage measurement is accordingly carried out by a combination of the measured values of the three sensor devices, with the individual advantages of the respective sensor devices in particular being used by the combination of the measured values of the sensor devices to improve the measured value recording as a whole.
  • the outer contour can be precisely detected with the outer contour sensor. This can be advantageous for increasing the accuracy in the assignment of measured values of the second and / or third Sensor means are exploited to a position on the outer contour, that the second and / or third sensor means to the outer contour sensor of the first sensor means on the coordinate measuring a defined, ie known and constant, distance or vector with respect to the Koordinatenmessarm have.
  • the position of the sensor devices relative to one another with respect to the coordinate measuring arm is defined in advantageous embodiments and is used to increase the accuracy.
  • the inner contour of the cavity is detected by the ultrasonic sensor as a reference contour, and detects the outer contour of the component by the outer contour sensor, and detects the damage by comparing the detected outer contour to the reference contour.
  • the inner contour of the hollow component is subject to any wear, since the surface of the inner contour is not exposed to any mechanical stress.
  • the inner contour forms an ideal reference surface for measuring the wear of the outer contour.
  • the relative nominal course of the outer contour to the reference contour is preferably stored in a memory unit, and the damage is determined by a comparison of the determined actual course of the outer contour to the reference contour with the relative desired course of the outer contour to the reference contour.
  • the damage is determined according to absolute values.
  • an assistance system with a display device and a memory unit is provided, and in the memory unit a predetermined test sequence is stored, in which the detected measured values are predetermined Limits are compared, the assistance system depending on the falling below or exceeding the predetermined limits by the measured values posersanweisun conditions on the display device to support the test procedure for display brings.
  • the assistance system serves to guide the handling person, so that the measured value can also be carried out by a less experienced person. Furthermore, this can reduce the likelihood of errors due to forgetting test steps.
  • the inner contour of the cavity by the ultrasonic sensor as reference contour de tektiert and detected in a further step, the outer contour of the component by the outer contour sensor, and the Scha detected by a comparison of the detected outer contour to the reference contour.
  • the outer contour is also detected precisely with the outer contour sensor.
  • the ultrasonic sensor and the outer contour sensor on the coordinate measuring arm have a defined, ie. known and constant, distance or vector with respect to the measuring arm, have.
  • a third sensor device with a white light interferometer and / or a laser triangulation sensor wherein the damage measurement is performed by a combination of the measured values of the first, second and third sensor device.
  • the damage measurement is accordingly carried out by a combination of the measured values of the three sensor devices, with the individual advantages of the respective sensor devices in particular being used by the combination of the measured values of the sensor devices to improve the measured value recording as a whole.
  • Fig. 2 shows a device according to the invention with a processing device and an assistance system.
  • FIG. 1 shows an enlarged measuring head 3 of a coordinate measuring arm 2, which can be seen schematically in FIG. 2 as an assembly of a superordinate device.
  • the device shown in FIG. 2 additionally comprises, in addition to the coordinate measuring arm 2, a tensioning device 5, a processing device 1, a memory unit 15 and a display device 4.
  • the memory unit 15 is arranged here in the housing of the processing device 1.
  • the processing device 1 is signal-technically connected to the coordinate measuring arm 2, the display device 4 and the memory unit 15.
  • a plurality of data are stored, such as data. the desired course of the outer contour of a component 6 to be measured, manufacturer-side test specifications and / or limit values, as well as explicit instructions on how to perform certain test steps.
  • the coordinate measuring arm 2 has a base or a corresponding holder, by means of which the coordinate measuring arm 2 is arranged or held in a defined position relative to the clamping device 5 and the component 6 held therein.
  • the coordinate measuring arm 2 as such is known and comprises a device (not shown) for determining the position of the measuring head 3 to be recognized in FIG. 1 in space. In this case, the coordinate measuring arm 2 is calibrated in relation to the clamping device 5 in an initial position.
  • a first sensor device 11 with an outer contour sensor 7 in the form of a probe a second sensor device 12 with an ultrasonic sensor 8 and a third sensor device 13 with a white light interferometer 9 and / or a laser triangulation sensor or a laser line triangulation sensor intended .
  • the measurement of the hollow component 6 takes place according to the following steps.
  • the component 6 is clamped in the clamping device 5 by means of suitable clamping tools 17.
  • a fourth sensor device 14 is provided in the clamping device 5, which detects the basic orientation of the component 6 in the clamping device 5, wherein alternatively the position or reference position of the component can be determined with the Koordina- tenmessarm 2, and a coordinate system in the determined reference position can be placed. If the component 6 can be held exclusively in a single orientation in the clamping tool 17 of the clamping device 5, it would also be conceivable to detect the orientation of the clamping tool 17 relative to the clamping device 5 by the fourth sensor device 14 and thereby indirectly also the orientation of the component. 6 to investigate.
  • the orientation of the component 6 is referenced in a first step.
  • the component 6 is referred to in the concrete application hereinafter as a hollow blade of an aircraft engine or a gas turbine on.
  • the measuring head 3 is then connected to the outside
  • the sensor 7 of the first sensor device 11 is guided to the entry edge of the blade.
  • the operator moves the leading edge of the blade with the outer contour sensor 7, whereby the contour and the position of possible damage points at the leading edge of the blade are detected.
  • the position of the leading edge of the blade can be detected.
  • the data determined by the first sensor device 11 are then supplied to the processing device 1, in which they are processed accordingly for further use.
  • the operator marks potential points of damage with the outer contour sensor 7 in order to make the position known to the system.
  • the operator changes to the second sensor device 12 with the ultrasonic sensor 8 and detects, for example, the transition region from solid material to the hollow region of the blade.
  • the inner contour of the cavity 16 in the blade is measured by the ultrasonic sensor 8, which is then used as a reference contour.
  • an actual thickness profile of the wall thickness of the hollow blade is then calculated from the measured values determined by the first and the second sensor devices 11 and 12, which is compared with a desired thickness profile stored in the memory unit 15. From the difference formation, the existing damage locations can then be localized and also calculated quantitatively. After the measured value recording of the first and the second sensor devices 11 and 12 and the processing of the determined measured values in the processing device 1, a complete damage pattern is available.
  • the guidance of the movement of the measuring head 3 also in dependence on the first and / or second sensor device 11 and 12 measured values can be controlled or simplified by action instructions of the assistance system to the operator.
  • the measured value recording by the third sensor device 13, but also immediately after the measured value recording by the first and second sensor device 11 and 12 during a single movement of the measuring head 3 can be made.
  • the third sensor device 13 can preferably be arranged on the measuring head 3 in such a way that the third sensor device 13 always tracks the respective position of the surface of the sensor during the movement of the coordinate measuring arm 2 and the measured value recording after the first and second sensor devices 11 and 12 Part 6 passes over.
  • the laser line triangulation sensor is activated, and the determined positions of the damaged areas are run over by the measuring head 3 , scanned and measured.
  • the assistance system can suggest and visualize a sequence of the areas to be scanned. This can be achieved both by means of a screen and, for example, by means of a targeted illumination or optical marking of the area to be scanned.
  • the processing device 1 with the memory unit 15 and the display device 4 is formed into an assistance system, which conveys to the handling person instructions on the display device which make it easier to carry out the measurement.
  • the central processing device 1 all process data required for evaluation and calculation are stored.
  • the instructions are generated taking into account the individually determined measured values, the data stored in the memory unit 15, such as the desired thickness profile stored there, or the desired outer contour of the component 6 or manufacturer-specified instructions on how the measurement is to be performed.
  • the processing device 1 can serve as a central data administration and data processing of the inspection process as an interface for data exchange with connected IT systems, while the assistance system for user-friendly and process-reliable control of the overall system and the guidance of the operator through the workflow.
  • the assistance system digitally depicts the entire inspection process.
  • the device is controlled via the assistance system, and the assistance system provides opportunities for collaboration between the operator and additional networks, such as the development or quality department.
  • the measurement of the damaged areas or the outer contour of the component 6 with the third sensor device 13 with the white light interferometer 9 provides the advantage of a highly accurate measurement of the damage points in the range of +/- 10 manometers or when using a laser triangulation sensor with an accuracy of 1 ⁇ in the depth direction and 7 to 8 ⁇ (dot pitch) in the width direction.
  • the measurement of the component 6 can be realized by a semi-automated surveying process with a person assisting the handling assistance system.
  • the measurement and the surface inspection can be objectively reproduced on the basis of the determined measured values, so that the surface inspection can be detected and reconstructed in the event of subsequent damage.
  • the measuring device on the measuring head 3 consists of the three sensor devices 11, 12 and 13, which can perform all measuring functions of the component inspection.
  • the necessary parameters such as the depth of the damaged area and the diameter of the damaged area, are determined automatically or manually by means of the displayed measuring points and made available to the operator via the assistance system.
  • the determination of the residual wall thickness by the integrated ultrasonic sensor 8 as well as the position on the blade can be determined by the tactile outer contour sensor 7.
  • the spatial reference is achieved in all measurements via the coupling of the processing device 1 with the coordinate measuring arm 2.
  • leading-pocket edge is used for the hollow blade, which is also referred to as a fan blade.
  • the leading pocket edge marks the transition between the solid material and the thin-walled portion of the blade at the flow entrance side. Detection takes place by continuous measurement of the wall thickness in the region of the edge by means of the non-collision probe 8 and the outer contour sensor 7, wherein the edge is specifically recognized by the jump of the wall thickness and a consequent characteristic measured value change in the region of the transition from full to hollow region and then over a spline is interpolated along the entire length of the leading edge of the blade.
  • the assistance system prepares inspection decisions by indicating tolerance deviations to the operator and proposing possible repair measures. It also visualizes the operator any error conditions of the measuring device and proposes corrective measures.
  • the process responsibility remains in contrast to a fully automated device aware of the operator, which on the one hand the system complexity and the associated costs can be reduced and on the other hand, the cognitive abilities of the operator in the measurement process can be exploited.
  • the entire device can also be made transportable, so that an on-wing measured value recording in an aircraft engine is possible.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Analytical Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Acoustics & Sound (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Abstract

La présente invention concerne un dispositif de mesurage de dommages d'un composant (6) creux d'avion ou de turbine à gaz avec un bras de mesure de coordonnées (2) sur lequel sont installés un premier dispositif capteur (11) avec un capteur de contour extérieur (7) pour la détection du contour extérieur du composant (6) et/ou pour la détermination de position d'une zone endommagée et un deuxième dispositif capteur (12) avec un capteur à ultrasons (8) pour la détection du contour d'un espace creux (16) dans le comportant (6) et/ou pour l'évaluation d'une épaisseur de paroi de la zone endommagée et/ou pour l'évaluation de l'épaisseur de paroi après une réparation de la zone endommagée, un troisième dispositif capteur (13) avec un interféromètre à lumière blanche (9) et/ou un capteur de triangulation laser étant installé sur le bras de mesure de coordonnées (2).
EP17808072.7A 2016-12-02 2017-12-01 Procédé et dispositif de mesurage de dommages d'un composant creux d'avion ou de turbine à gaz Withdrawn EP3548839A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016224049.8A DE102016224049A1 (de) 2016-12-02 2016-12-02 Verfahren und Einrichtung zur Schadensvermessung eines hohlen Flugzeug- oder Gasturbinen-Bauteils
PCT/EP2017/081165 WO2018100144A1 (fr) 2016-12-02 2017-12-01 Procédé et dispositif de mesurage de dommages d'un composant creux d'avion ou de turbine à gaz

Publications (1)

Publication Number Publication Date
EP3548839A1 true EP3548839A1 (fr) 2019-10-09

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17808072.7A Withdrawn EP3548839A1 (fr) 2016-12-02 2017-12-01 Procédé et dispositif de mesurage de dommages d'un composant creux d'avion ou de turbine à gaz

Country Status (3)

Country Link
EP (1) EP3548839A1 (fr)
DE (1) DE102016224049A1 (fr)
WO (1) WO2018100144A1 (fr)

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CN114322830B (zh) * 2021-12-29 2023-11-17 北方工业大学 复杂空心涡轮叶片在机检测装置及数据处理方法

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