WO2010055263A1 - Method and assembly for determining the wear of the leading edge of a blade - Google Patents
Method and assembly for determining the wear of the leading edge of a blade Download PDFInfo
- Publication number
- WO2010055263A1 WO2010055263A1 PCT/FR2009/052173 FR2009052173W WO2010055263A1 WO 2010055263 A1 WO2010055263 A1 WO 2010055263A1 FR 2009052173 W FR2009052173 W FR 2009052173W WO 2010055263 A1 WO2010055263 A1 WO 2010055263A1
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- Prior art keywords
- blade
- leading edge
- mark
- endoscope
- permanent
- 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.)
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Classifications
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
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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
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- 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
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- 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
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
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- 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
Definitions
- the present invention relates to a method for determining the wear of the leading edge and / or the depth of a mark due to the ingestion of a foreign body (FOD) of at least one rotating blade of an aircraft engine and a wear determination assembly, in particular for implementing said method.
- FOD foreign body
- the European patent application EP 1 494 060 discloses a device for detecting defects in aircraft engine parts by bleeding.
- This device uses an endoscope.
- this invention aims to solve a problem very different from that solved by the present invention.
- An object of the present invention is to provide a method for determining the wear of the leading edge of a rotary blade of an aircraft engine which allows such a control in more acceptable economic conditions and which allows in particular avoid partial dismantling of the engine.
- a method for determining the wear of the leading edge of at least one rotary blade of an aircraft engine, disposed inside an outer casing comprises the following steps: during manufacture of the blade, is made on one of its faces at least one permanent marking having a predetermined position relative to the leading edge of the blade, it is provided in the housing of motor, an orifice in spatial relation with each blade to be controlled, an endoscope is introduced through said orifice to bring its active end opposite the part of the blade comprising said mark and said leading edge in its proximity, and the endoscope is The effective position of said mark with respect to said leading edge is measured by means of taking up use, comparing said raised position with said predetermined position in order to deduce whether there has been wear or not.
- the endoscope inside the motor housing facing the rotor blades to be controlled, it is not necessary to dismantle the motor to have a very serious control of the possible wear of the motor. leading edge of the blades.
- the aircraft engine casings are, at the time of their design, equipped with orifices allowing insertion of the endoscope to the various desirable locations. The implementation of this method does not imply any modification of the aircraft engines.
- the images or data taken using the endoscope for the different blades can maintain a very complete traceability of the aircraft engine status control operations.
- two or more marks can be made on the blade.
- a second object of the invention is to provide a set of determination of the wear of the leading edge of at least one rotary blade of an aircraft engine in particular for the implementation of the method defined above.
- the set of determination is characterized in that it comprises;
- an endoscope capable of being introduced into the casing through said orifice, said mark occupying, with respect to the leading edge of the blade, a predetermined position in such a way that said mark and a part of the leading edge are simultaneously in the field of the endoscope; and means for processing the images delivered by said endoscope in order to deduce the relative position of the leading edge with respect to said mark.
- FIG. 1 is a longitudinal sectional view of a compressor capable of implementing the method according to the invention
- FIG. 2 is a simplified cross-sectional view of the aircraft engine shown in Figure 1, showing the implementation of the method;
- FIG. 3A is a view of a rotary blade provided with a wear marking mark
- Figure 3B is a cross-sectional view of the blade of Figure 3A;
- FIG. 3C is a sectional view according to the thickness of the blade shown in Figure 3A; and - Figure 4 shows a rotary blade provided with marking means according to an alternative embodiment.
- FIG 1 there is shown an aircraft engine or more exactly a part of an aircraft engine that may be applied to the implementation of the invention. It is a helicopter compressor.
- the outer casing 10 of the compressor This consists essentially of an axial compressor 12 and a centrifugal compressor 14. The air enters the axial compressor 12 at its end 16 and leaves the centrifugal compressor 14 via the annular outlet 18.
- the compressor shaft 20 and the blades 22 integral in rotation with the shaft 20 and forming an integral part of the rotor of the compressor.
- the still vanes 24 of the stator of the compressor are further schematically represented.
- the outer casing 10 of the compressor comprises, regularly distributed, orifices not shown in the figure whose diameter is the order of 10 mm. These operating openings of the compressor are of course closed by plug systems.
- an endoscope bearing the general reference 36 is used.
- This endoscope may be of the type described in the European patent application. EP 1 494 060 at least as regards its optical part.
- the endoscope 36 has an active end 38 and a head 40.
- the outer tube 42 of the endoscope contains both optical guides to transmit to the active end 38 of the endoscope a light beam produced by the optical source 44 and to collect an image of the visible part of the interior of the housing opposite the exit of the endoscope.
- the images taken by the endoscope transmitted by optical fibers or the like disposed in the tube 42 are processed for example digitized by the scanning device 46 connected to the head 40 of the endoscope.
- the scanned image information can be displayed on a screen 48 and is transmitted to a processing unit 50.
- the endoscope tube 42 enters the housing through the orifice such that its active end 38 is placed opposite the portion of the blade 34 near its leading edge 34a. From the images thus taken and processed by the circuit 50, it will be possible to deduce a possible wear of the leading edge by the specific means which will be described below.
- FIGS. 3A to 3C there is shown a rotor blade 34 with its fastening system on the rotor 52.
- a mark 54 is provided whose position relative to the leading edge 34a at the moment of manufacture of the blade is perfectly defined at the distance X.
- the mark 54 is preferably constituted by a hollow in the form of a spherical cap formed in the intrados 34b of the blade 34.
- the depth of the mark 54 is between 0.2 and 0.5mm and its diameter is between 0.8 and 2mm.
- the image or the images taken by the endoscope disposed inside the housing 10 are processed by the circuits 50 which redefine the leading edge 34a possibly used of the blade 34 by taking as reference the mark 54 and the distance X separating the mark 54 from the leading edge in the absence of wear.
- the blade 34 'at the time of its initial manufacture can be provided with two marks 54 and 56. From the image taken by the endoscope which reproduces both the edge of effective attack, that is to say possibly used 34'a and the two marking markings 54 and 56, it is possible to effectively measure the possible wear of the initial leading edge 34a, by comparing the profile raised and comparing it to the initial profile.
- this method of determining the possible wear of the leading edge of a blade has many advantages. On the one hand, it entails no modification of the external structure of the aircraft engine, and in the particular case described of the helicopter compressor, since the orifices 30 allowing the insertion of the endoscope to the rights of each blade to control already exist. In addition and of course, this technique avoids the disassembly of the external parts of the aircraft engine and more particularly in the described case of the compressor while allowing a very precise control of the possible wear of the leading edge of the blade. Finally, the recording of the profile of the leading edge recorded by the endoscope makes it possible to ensure the traceability of the controls carried out on this part of the aircraft engine.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
- Instruments For Viewing The Inside Of Hollow Bodies (AREA)
Abstract
Description
Procédé et ensemble de détermination de l'usure du bord d'attaque d'une pâle Method and assembly for determining the wear of the leading edge of a pale
La présente invention a pour objet un procédé de détermination de l'usure du bord d'attaque et/ou de Ia profondeur d'une marque due à l'ingestion d'un corps étranger (FOD) d'au moins une pale rotative d'un moteur d'aéronef et un ensemble de détermination d'usure notamment pour la mise en œuvre dudit procédé.The present invention relates to a method for determining the wear of the leading edge and / or the depth of a mark due to the ingestion of a foreign body (FOD) of at least one rotating blade of an aircraft engine and a wear determination assembly, in particular for implementing said method.
Dans tous les systèmes propulsifs rotatifs pour aéronef, il est important de pouvoir vérifier périodiquement que les pales du rotor et notamment le bord d'attaque de ces pales n'a pas fait l'objet d'une usure anormale incompatible avec le bon fonctionnement du moteur.In all rotary propulsion systems for aircraft, it is important to be able to check periodically that the rotor blades and in particular the leading edge of these blades has not been subject to abnormal wear incompatible with the proper functioning of the rotor. engine.
La technique utilisée actuellement nécessite un démontage important de ce moteur pour pouvoir examiner individuellement chaque aube. Il en résulte bien sûr un coût important de maintenance et une immobilisation prolongée des appareils équipés de ces moteurs.The technique currently used requires significant disassembly of this engine to be able to individually examine each blade. This of course results in a significant cost of maintenance and prolonged immobilization of devices equipped with these engines.
En particulier, il est nécessaire de procéder au démontage du carter externe de ce moteur et éventuellement au démontage des aubes elles- mêmes.In particular, it is necessary to disassemble the outer casing of this engine and possibly disassembly of the blades themselves.
La demande de brevet européen EP 1 494 060 décrit un dispositif de détection de défauts de pièces de moteurs d'aéronef par ressuage.The European patent application EP 1 494 060 discloses a device for detecting defects in aircraft engine parts by bleeding.
Ce dispositif utilise un endoscope. Cependant, cette invention vise à résoudre un problème très différent de celui que résout la présente invention.This device uses an endoscope. However, this invention aims to solve a problem very different from that solved by the present invention.
Un objet de la présente invention est de fournir un procédé de détermination de l'usure du bord d'attaque d'une pale rotative d'un moteur d'aéronef qui permette un tel contrôle dans des conditions économiques plus acceptables et qui permette en particulier d'éviter les opérations de démontage partiel du moteur.An object of the present invention is to provide a method for determining the wear of the leading edge of a rotary blade of an aircraft engine which allows such a control in more acceptable economic conditions and which allows in particular avoid partial dismantling of the engine.
Pour atteindre ce but selon l'invention, un procédé de détermination de l'usure du bord d'attaque d'au moins une pale rotative d'un moteur d'aéronef, disposé à l'intérieur d'un carter externe est caractérisé en ce qu'il comporte les étapes suivantes : lors de la fabrication de la pale, on réalise sur une de ses faces au moins un marquage permanent ayant une position prédéterminée par rapport au bord d'attaque de la pale, on fournit dans le carter du moteur, un orifice en relation spatiale avec chaque pale à contrôler, on introduit par ledit orifice un endoscope à l'intérieur du carter pour amener son extrémité active en regard de la partie de la pale comportant ladite marque et ledit bord d'attaque dans sa proximité, on relève à l'aide de l'endoscope et de moyens de prise d'usage la position effective de ladite marque par rapport audit bord d'attaque, on compare ladite position relevée à ladite position prédéterminée pour en déduire s'il y a eu usure ou pas.To achieve this object according to the invention, a method for determining the wear of the leading edge of at least one rotary blade of an aircraft engine, disposed inside an outer casing, is characterized in that it comprises the following steps: during manufacture of the blade, is made on one of its faces at least one permanent marking having a predetermined position relative to the leading edge of the blade, it is provided in the housing of motor, an orifice in spatial relation with each blade to be controlled, an endoscope is introduced through said orifice to bring its active end opposite the part of the blade comprising said mark and said leading edge in its proximity, and the endoscope is The effective position of said mark with respect to said leading edge is measured by means of taking up use, comparing said raised position with said predetermined position in order to deduce whether there has been wear or not.
Grâce à l'introduction de l'endoscope à l'intérieur du carter du moteur en regard des pales de rotor à contrôler, il n'est pas nécessaire de procéder au démontage du moteur pour avoir un contrôle très sérieux de l'usure éventuelle du bord d'attaque des pales. En outre, les carters de moteur d'aéronef sont, au moment de leur conception, équipés d'orifices permettant l'insertion de l'endoscope aux différents emplacements souhaitables. La mise en œuvre de ce procédé n'implique donc aucune modification des moteurs d'aéronefs.Thanks to the introduction of the endoscope inside the motor housing facing the rotor blades to be controlled, it is not necessary to dismantle the motor to have a very serious control of the possible wear of the motor. leading edge of the blades. In addition, the aircraft engine casings are, at the time of their design, equipped with orifices allowing insertion of the endoscope to the various desirable locations. The implementation of this method does not imply any modification of the aircraft engines.
En outre, les images ou données prises à l'aide de l'endoscope relatives aux différentes pales permettent de conserver une traçabilité très complète des opérations de contrôle de l'état du moteur d'aéronef.In addition, the images or data taken using the endoscope for the different blades can maintain a very complete traceability of the aircraft engine status control operations.
En fait, la seule opération spécifique rendue nécessaire par la mise en œuvre du procédé est de réaliser une ou plusieurs marques sur les pales du rotor. Cependant, comme ces pales sont généralement des pièces détachées fixées par tout moyen convenable sur l'arbre du rotor, cette question est d'une incidence économique très mineure.In fact, the only specific operation made necessary by the implementation of the method is to make one or more marks on the rotor blades. However, as these blades are generally spare parts fixed by any suitable means on the rotor shaft, this question has a very minor economic impact.
Avantageusement, deux marques ou plus peuvent être réalisées sur la pale.Advantageously, two or more marks can be made on the blade.
Un deuxième objet de l'invention est de fournir un ensemble de détermination de l'usure du bord d'attaque d'au moins une pale rotative d'un moteur d'aéronef notamment pour la mise en œuvre du procédé défini ci-dessus. L'ensemble de détermination se caractérise en ce qu'il comprend ;A second object of the invention is to provide a set of determination of the wear of the leading edge of at least one rotary blade of an aircraft engine in particular for the implementation of the method defined above. The set of determination is characterized in that it comprises;
- au moins une marque en creux réalisée dans la pale lors de sa fabrication ayant une position prédéterminée par rapport au bord d'attaque de la pale ;at least one hollow mark formed in the blade during its manufacture having a predetermined position relative to the leading edge of the blade;
- un endoscope apte à être introduit dans le carter par ledit orifice, ladite marque occupant par rapport au bord d'attaque de Ia pale une position prédéterminée de telle manière que ladite marque et une partie du bord d'attaque soient simultanément dans le champ de l'endoscope; et - des moyens de traitement des images délivrées par ledit endoscope pour en déduire la position relative du bord d'attaque par rapport à ladite marque.an endoscope capable of being introduced into the casing through said orifice, said mark occupying, with respect to the leading edge of the blade, a predetermined position in such a way that said mark and a part of the leading edge are simultaneously in the field of the endoscope; and means for processing the images delivered by said endoscope in order to deduce the relative position of the leading edge with respect to said mark.
D'autres caractéristiques et avantages de l'invention apparaîtront mieux à la lecture de la description qui suit de mode de mise en œuvre préféré du procédé et de réalisation de l'ensemble de détermination de l'usure.Other characteristics and advantages of the invention will appear better on reading the following description of the preferred embodiment of the method and the realization of the wear determination assembly.
La description se réfère aux figures annexées, sur lesquelles :The description refers to the appended figures, in which:
- la figure 1 est une vue en coupe longitudinale d'un compresseur susceptible de permettre la mise en œuvre du procédé selon l'invention ;- Figure 1 is a longitudinal sectional view of a compressor capable of implementing the method according to the invention;
- la figure 2 est une vue en coupe transversale simplifiée du moteur d'aéronef représenté sur la figure 1, montrant la mise en œuvre du procédé ;- Figure 2 is a simplified cross-sectional view of the aircraft engine shown in Figure 1, showing the implementation of the method;
- la figure 3A est une vue d'une pale rotative pourvue d'une marque de repérage d'usure ;FIG. 3A is a view of a rotary blade provided with a wear marking mark;
- la figure 3B est une vue en coupe transversale de la pale de la figure 3A ;Figure 3B is a cross-sectional view of the blade of Figure 3A;
- la figure 3C est une vue en coupe selon l'épaisseur de la pale représentée sur la figure 3A ; et - la figure 4 montre une pale rotative munie de moyens de marquage selon une variante de réalisation.- Figure 3C is a sectional view according to the thickness of the blade shown in Figure 3A; and - Figure 4 shows a rotary blade provided with marking means according to an alternative embodiment.
Sur la figure 1, à titre d'exemple, on a représenté un moteur d'aéronef ou plus exactement une partie d'un moteur d'aéronef susceptible de se voir appliquée la mise en œuvre de l'invention. Il s'agit d'un compresseur pour hélicoptère. Sur cette figure, on a représenté le carter externe 10 du compresseur. Celui-ci est constitué essentiellement par un compresseur axial 12 et par un compresseur centrifuge 14. L'air entre dans le compresseur axial 12 par son extrémité 16 et ressort du compresseur centrifuge 14 par la sortie annulaire 18. Sur cette figure, on a représenté également schématïquement l'arbre du compresseur 20 ainsi que les pales 22 solidaires en rotation de l'arbre 20 et faisant partie intégrante du rotor du compresseur. On a représenté encore schématiquement les aubes fixes 24 du stator du compresseur. Il faut ajouter que le carter externe 10 du compresseur comporte, régulièrement répartis, des orifices non représentés sur Ia figure dont le diamètre est de l'ordre de 10 mm. Ces orifices en fonctionnement du compresseur son bien sûr obturés par des systèmes de bouchon.In Figure 1, for example, there is shown an aircraft engine or more exactly a part of an aircraft engine that may be applied to the implementation of the invention. It is a helicopter compressor. In this figure, there is shown the outer casing 10 of the compressor. This consists essentially of an axial compressor 12 and a centrifugal compressor 14. The air enters the axial compressor 12 at its end 16 and leaves the centrifugal compressor 14 via the annular outlet 18. In this figure, it is shown also schematically the compressor shaft 20 and the blades 22 integral in rotation with the shaft 20 and forming an integral part of the rotor of the compressor. The still vanes 24 of the stator of the compressor are further schematically represented. It should be added that the outer casing 10 of the compressor comprises, regularly distributed, orifices not shown in the figure whose diameter is the order of 10 mm. These operating openings of the compressor are of course closed by plug systems.
En se réfèrent maintenant à la figure 2, on va expliquer en quoi consiste l'invention. Sur cette figure, on a représenté de façon simplifiée le carter externe 10 du moteur d'aéronef et un des orifices 30 mentionnés précédemment. Cette figure montre également l'arbre 20 du moteur avec son rotor 32 et une pale rotative référencée 34 sur cette figure.Referring now to Figure 2, we will explain what the invention is. In this figure, there is shown in a simplified manner the outer casing 10 of the aircraft engine and one of the orifices 30 mentioned above. This figure also shows the shaft 20 of the motor with its rotor 32 and a rotary blade referenced 34 in this figure.
Comme on l'a déjà expliqué pour procéder au contrôle de l'usure du bord d'attaque 34a de la pale rotative 34, on utilise un endoscope portant la référence générale 36. Cet endoscope peut être du type décrit dans la demande de brevet européen EP 1 494 060 du moins pour ce qui concerne sa partie optique. L'endoscope 36 comporte une extrémité active 38 et une tête 40. Le tube externe 42 de l'endoscope contient à la fois des guides optiques pour transmettre à l'extrémité active 38 de l'endoscope un faisceau lumineux produit par la source optique 44 et pour recueillir une image de la partie visible de l'intérieur du carter en regard la sortie de l'endoscope.As has already been explained in order to check the wear of the leading edge 34a of the rotary blade 34, an endoscope bearing the general reference 36 is used. This endoscope may be of the type described in the European patent application. EP 1 494 060 at least as regards its optical part. The endoscope 36 has an active end 38 and a head 40. The outer tube 42 of the endoscope contains both optical guides to transmit to the active end 38 of the endoscope a light beam produced by the optical source 44 and to collect an image of the visible part of the interior of the housing opposite the exit of the endoscope.
Comme cela est bien connu, les images prises par l'endoscope transmise par des fibres optiques ou analogues disposées dans le tube 42 sont traitées par exemple numérisées par le dispositif de numérisation 46 relié à la tête 40 de l'endoscope. Les informations d'images numérisées peuvent être affichées sur un écran 48 et sont transmises à une ensemble de traitement 50. Comme on le voit sur cette figure, le tube 42 de l'endoscope pénètre à l'intérieur du carter de par l'orifice tel que 30 de telle manière que son extrémité active 38 soit placée en regard de la partie de la pale 34 à proximité de son bord d'attaque 34a. A partir des images ainsi prises et traitées par le circuit 50, on pourra en déduire une éventuelle usure du bord d'attaque grâce aux moyens spécifiques qui vont être décrits ci- après.As is well known, the images taken by the endoscope transmitted by optical fibers or the like disposed in the tube 42 are processed for example digitized by the scanning device 46 connected to the head 40 of the endoscope. The scanned image information can be displayed on a screen 48 and is transmitted to a processing unit 50. As seen in this figure, the endoscope tube 42 enters the housing through the orifice such that its active end 38 is placed opposite the portion of the blade 34 near its leading edge 34a. From the images thus taken and processed by the circuit 50, it will be possible to deduce a possible wear of the leading edge by the specific means which will be described below.
Sur les figures 3A à 3C, on a représenté une pale de rotor 34 avec son système de fixation sur le rotor 52. Pour permettre la détection de l'usure du bord d'attaque 34a, au moment de la fabrication de la pale 34, on prévoit une marque 54 dont la position par rapport au bord d'attaque 34a au moment de la fabrication de la pale est parfaitement définie à la distance X. Comme le montre mieux Ia figure 3B, la marque 54 est de préférence constituée par un creux en forme de calotte sphérique réalisé dans l'intrados 34b de la pale 34. Par exemple, la profondeur de la marque 54 est comprise entre 0,2 et 0,5mm et son diamètre est compris entre 0,8 et 2mm.In FIGS. 3A to 3C, there is shown a rotor blade 34 with its fastening system on the rotor 52. To enable the detection of the wear of the leading edge 34a, at the time of manufacture of the blade 34, a mark 54 is provided whose position relative to the leading edge 34a at the moment of manufacture of the blade is perfectly defined at the distance X. As best shown in FIG. 3B, the mark 54 is preferably constituted by a hollow in the form of a spherical cap formed in the intrados 34b of the blade 34. For example, the depth of the mark 54 is between 0.2 and 0.5mm and its diameter is between 0.8 and 2mm.
L'image ou les images prises par l'endoscope disposé à l'intérieur du carter 10 sont traitées par les circuits 50 qui redéfinissent le bord d'attaque 34a éventuellement usé de la pale 34 en prenant comme référence la marque 54 et la distance X séparant la marque 54 du bord d'attaque en l'absence d'usure.The image or the images taken by the endoscope disposed inside the housing 10 are processed by the circuits 50 which redefine the leading edge 34a possibly used of the blade 34 by taking as reference the mark 54 and the distance X separating the mark 54 from the leading edge in the absence of wear.
Dans une variante de réalisation illustrée par la figure 4, la pale 34' au moment de sa fabrication initiale peut être munie de deux marques 54 et 56. A partir de l'image prise par l'endoscope qui reproduit à la fois le bord d'attaque effectif, c'est-à-dire éventuellement usé 34'a et les deux marquages de repérage 54 et 56, il est possible de mesurer effectivement l'usure éventuelle du bord d'attaque initial 34a, en comparant le profil relevé et en le comparant au profil initial.In an alternative embodiment illustrated in Figure 4, the blade 34 'at the time of its initial manufacture can be provided with two marks 54 and 56. From the image taken by the endoscope which reproduces both the edge of effective attack, that is to say possibly used 34'a and the two marking markings 54 and 56, it is possible to effectively measure the possible wear of the initial leading edge 34a, by comparing the profile raised and comparing it to the initial profile.
On comprend que ce procédé de détermination de l'usure éventuelle du bord d'attaque d'une pale présente de nombreux avantages. D'une part, il n'entraîne aucune modification de la structure externe du moteur d'aéronef, et dans le cas particulier décrit du compresseur pour hélicoptère, puisque les orifices 30 permettant l'insertion de l'endoscope aux droits de chaque pale à contrôler existent déjà. En outre et bien entendu, cette technique évite le démontage des parties externes du moteur d'aéronef et plus particulièrement dans le cas décrit du compresseur tout en permettant un contrôle très précis de l'usure éventuelle du bord d'attaque de la pale. Enfin, l'enregistrement du profil du bord d'attaque relevé par l'endoscope permet d'assurer la traçabilité des contrôles réalisés sur cette partie du moteur d'aéronef. It is understood that this method of determining the possible wear of the leading edge of a blade has many advantages. On the one hand, it entails no modification of the external structure of the aircraft engine, and in the particular case described of the helicopter compressor, since the orifices 30 allowing the insertion of the endoscope to the rights of each blade to control already exist. In addition and of course, this technique avoids the disassembly of the external parts of the aircraft engine and more particularly in the described case of the compressor while allowing a very precise control of the possible wear of the leading edge of the blade. Finally, the recording of the profile of the leading edge recorded by the endoscope makes it possible to ensure the traceability of the controls carried out on this part of the aircraft engine.
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0857731 | 2008-11-14 | ||
| FR0857731A FR2938651B1 (en) | 2008-11-14 | 2008-11-14 | METHOD AND ASSEMBLY FOR DETERMINING THE WEAR OF THE LEADING EDGE OF A BLADE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2010055263A1 true WO2010055263A1 (en) | 2010-05-20 |
Family
ID=40759014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/FR2009/052173 Ceased WO2010055263A1 (en) | 2008-11-14 | 2009-11-12 | Method and assembly for determining the wear of the leading edge of a blade |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR2938651B1 (en) |
| WO (1) | WO2010055263A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120285226A1 (en) * | 2011-05-09 | 2012-11-15 | Kurt Neal Laurer | Wear-Indicating System For Use With Turbine Engines and Methods Of Inspecting Same |
| FR2975771A1 (en) * | 2011-05-27 | 2012-11-30 | Snecma | DEVICE FOR MEASURING A PIECE IN A TURBOMACHINE |
| CN103857919A (en) * | 2011-10-07 | 2014-06-11 | 涡轮梅坎公司 | Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker |
| CN110998189A (en) * | 2017-08-21 | 2020-04-10 | 赛峰飞机发动机公司 | Combustor module for an aircraft turbine engine including markings to aid identification during endoscopy of the combustor |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3006013B1 (en) * | 2013-05-21 | 2017-10-13 | Turbomeca | TURBOMACHINE COMPRISING A WEAR OF THE CARTER |
Citations (6)
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|---|---|---|---|---|
| FR2051345A5 (en) * | 1969-06-30 | 1971-04-02 | Gen Electric | |
| US6341936B1 (en) * | 2000-04-21 | 2002-01-29 | General Electric Company | FOD inspection of laser shock peened gas turbine engine airfoils |
| US20040054256A1 (en) * | 2002-07-01 | 2004-03-18 | Olympus Optical Co., Ltd. | Measurement endoscope system |
| US20040148793A1 (en) * | 2003-01-30 | 2004-08-05 | Lockheed Martin Corporation | Apparatus and method for inspecting and marking repair areas on a blade |
| EP1494060A1 (en) | 2003-07-04 | 2005-01-05 | Snecma Moteurs | Apparatus for searching and detecting flaws in parts by endoscopy |
| US20080158556A1 (en) * | 2006-12-28 | 2008-07-03 | Bendall Clark A | Method for measuring missing corner dimensions |
-
2008
- 2008-11-14 FR FR0857731A patent/FR2938651B1/en active Active
-
2009
- 2009-11-12 WO PCT/FR2009/052173 patent/WO2010055263A1/en not_active Ceased
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2051345A5 (en) * | 1969-06-30 | 1971-04-02 | Gen Electric | |
| US6341936B1 (en) * | 2000-04-21 | 2002-01-29 | General Electric Company | FOD inspection of laser shock peened gas turbine engine airfoils |
| US20040054256A1 (en) * | 2002-07-01 | 2004-03-18 | Olympus Optical Co., Ltd. | Measurement endoscope system |
| US20040148793A1 (en) * | 2003-01-30 | 2004-08-05 | Lockheed Martin Corporation | Apparatus and method for inspecting and marking repair areas on a blade |
| EP1494060A1 (en) | 2003-07-04 | 2005-01-05 | Snecma Moteurs | Apparatus for searching and detecting flaws in parts by endoscopy |
| US20080158556A1 (en) * | 2006-12-28 | 2008-07-03 | Bendall Clark A | Method for measuring missing corner dimensions |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120285226A1 (en) * | 2011-05-09 | 2012-11-15 | Kurt Neal Laurer | Wear-Indicating System For Use With Turbine Engines and Methods Of Inspecting Same |
| US8695445B2 (en) * | 2011-05-09 | 2014-04-15 | General Electric Company | Wear-indicating system for use with turbine engines and methods of inspecting same |
| FR2975771A1 (en) * | 2011-05-27 | 2012-11-30 | Snecma | DEVICE FOR MEASURING A PIECE IN A TURBOMACHINE |
| WO2012164192A1 (en) * | 2011-05-27 | 2012-12-06 | Snecma | Method and device for measuring a part in a turbine engine |
| US8973428B2 (en) | 2011-05-27 | 2015-03-10 | Snecma | Method and device for measuring a part in a turbine engine |
| RU2598906C2 (en) * | 2011-05-27 | 2016-10-10 | Снекма | Method and device for measuring component in turbo machine |
| CN103857919A (en) * | 2011-10-07 | 2014-06-11 | 涡轮梅坎公司 | Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker |
| US9829005B2 (en) * | 2011-10-07 | 2017-11-28 | Turbomeca | Centrifugal compressor provided with a marker for measuring wear and a method of monitoring wear using said marker |
| CN110998189A (en) * | 2017-08-21 | 2020-04-10 | 赛峰飞机发动机公司 | Combustor module for an aircraft turbine engine including markings to aid identification during endoscopy of the combustor |
| CN110998189B (en) * | 2017-08-21 | 2021-02-26 | 赛峰飞机发动机公司 | Combustor module for an aircraft turbine engine including markings to aid identification during endoscopy of the combustor |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2938651A1 (en) | 2010-05-21 |
| FR2938651B1 (en) | 2011-03-04 |
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