• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a device (46) for measuring the characteristics of an air flow of a turbomachine annular duct, comprising a rod (44) extending along a first axis (54), carrying means for measuring characteristics of an air flow and engaged in sealing sliding in a first tubular portion (62) extending through a tubular secondary portion (64) sealingly crosswise along the first axis (54) a slider (66) mounted sliding in a slide along a second axis (56) perpendicular to said first axis (54), said rod (44) being engaged with an annular clearance in said second tubular portion (64).
    公开号:FR3079299A1
    申请号:FR1852500
    申请日:2018-03-22
    公开日:2019-09-27
    发明作者:Jean-Luc Verniau；Gilles Polo Filisan；Adnan Sozuan；Simon Paris
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    DEVICE FOR MEASURING THE CHARACTERISTICS OF AN AIRFLOW
    FIELD [001] The present invention relates to a device for measuring the characteristics of an air flow in a turbomachine, in particular in a test turbomachine.
    BACKGROUND Conventionally, a double-flow turbojet engine 10, as illustrated in FIG. 1, consists of a gas turbine 12 of axis of revolution 14 driving a fan wheel 16, which is faired, the latter being generally placed upstream of the turbojet engine. The mass of air drawn in by the engine is divided into a primary air flow (arrow A), which circulates in the gas turbine 12 or primary body, and a secondary air flow (arrow B), which comes from of the fan 16 and which annularly surrounds the primary body, the primary and secondary air flows being concentric and evolving in a primary annular vein 18 and a secondary annular vein 20 respectively
    8.
    In a well known manner, the primary air flow (arrow A) is generally compressed by a low pressure compressor 22 and then by a high pressure compressor 24 each comprising fixed and movable blades 26 arranged alternately in the direction of displacement of the flow. The low pressure compressor shaft is connected to the blower wheel 4 and is rotated by the shaft of a low pressure turbine arranged downstream (not shown). The shaft of the high pressure compressor is rotated by the shaft of a high pressure turbine arranged at the outlet of a combustion chamber and upstream of the low pressure turbine (not shown).
    In such a double body turbojet, usually denoted by fan casing, the outer annular wall 28 surrounding the fan wheel 16 and by intermediate casing 30, a structural element of the turbomachine interposed axially between the compressors, low pressure 22 and, high pressure 24 and which passes through the primary annular 18 and secondary veins 20. This intermediate casing 30 comprises two annular walls radially internal 32 and external 34 delimiting, respectively, internally and externally the annular vein 18 for flow of the flow of primary air, and two radially internal 36 and external 38 annular walls internally and externally delimiting the secondary annular vein 20, respectively.
    In the context of the development of a turbojet engine, it is necessary to test its performance in order to certify it. Development turbomachines are thus provided for this purpose. On these turbomachines, a large number of measurements are made. Are measured, in particular, the characteristics of the aerodynamic flow at different axial positions or planes 40a, 40b, 40c of measurements. In addition, we want to be able to make measurements at several points of a measurement plan.
    To this end, measuring members, commonly called meters, arranged at the level of the measurement planes are commonly used to characterize the aerodynamic flow by measuring in operation parameters such as for example the pressure and the temperature. Such a member 42a, 42b, 42c comprises a rod 44 carrying means for measuring the characteristics of the air flow. It also includes a radially outer end and a radially inner end relative to the axis of rotation 14 of the turbomachine. The radially external end of the member 42a, 42b, 42c is carried by a casing of the turbomachine while the radially internal end arranged inside the vein is free and placed in the air flow of the turbomachine which one wishes to measure the flow characteristics of the air flow.
    More specifically, the radially outer end is connected to a base for fixing to the housing making it possible to support the rod 44 in a given fixed radial direction. When it is desired to carry out measurements at different radial positions, it is necessary to stop the turbomachine, to reposition the rod in its base in a different position and to restart the turbomachine. These steps prove to be long and complicate the testing phases. Also, at the passage of certain speeds of rotation, of the fan, in particular when the rod 44 extends in the annular stream of secondary air, the rod 44 is capable of entering into resonance, which can lead to cracks in the measuring rod 44 and can impact its mechanical integrity. In extreme cases, the formation of cracks or cracks consecutive to vibrations can lead to partial or total dislocation of the rod 44. The debris thus released circulates in the vein and can damage parts of the turbomachine which are arranged downstream.
    In known systems, it has notably been proposed to mount the rod on displacement means with radial sliding and on displacement means in tangential or circumferential direction. However, this type of assembly does not make it possible to achieve an optimal seal against the air flow of the air stream so that the measurement impacts the characteristics of the air flow that it must measure.
    The purpose of the invention is in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
    SUMMARY OF THE INVENTION [010] Thus, the invention provides a device for measuring the characteristics of an air flow from an annular stream of a turbomachine, comprising a rod extending along a given first axis, carrying means for measuring the characteristics of an air flow and engaged in sliding sealingly in a first tubular part extending by a secondary tubular part passing through sealing along the first axis a slide mounted to slide in a sliding along a second axis perpendicular to said first axis, said rod being engaged with an annular clearance in said second tubular part.
    According to the invention, the seal is produced in two different places on two different axes of displacement of the rod, which simplifies the design of the measuring device. In particular, a seal is made with respect to the slide by means of the second tubular part and the seal with the air flowing in the second tubular part is made directly on the rod itself.
    According to another characteristic of the invention, the slide is preferably cylindrical and comprises a first part of slide with telescopic tubes and a second part of slide with telescopic tubes, said first and second parts of slide with telescopic tubes being fixed. sealed by an axial end to said second tubular part.
    The use of a slide with telescopic tubes makes it possible to distribute the pressure of the incoming air well through the annular clearance provided between the rod and the second tubular part on the various tubes constituting the first part of the slide and the second part. slide.
    The first tubular part may comprise a first support plate supporting in rotation about the first axis a first actuator for translational displacement of the rod along said first axis.
    [015] In order to ensure cooling of the first plate, the latter may include a circuit capable of allowing air circulation and intended to be connected to air supply means. The thermal regulation of the first plate thus makes it possible to limit the heating of the parts which are fixed to it. It is understood that the first plate is preferably also tubular, that is to say that it comprises at least one central opening for passage of the rod.
    In a particular configuration, a first tubular part and a second tubular part coaxial with the first axis are mounted around the rod, the first tubular part surrounding the second tubular part and delimiting therewith a circuit capable of allowing circulation a coolant which is intended to be connected to means for supplying coolant. This arrangement allows, in combination with the cooling air circuit, to better regulate the temperature of the device.
    Advantageously, the first tubular part is inserted into an opening of the first plate and is made integral with said first plate.
    To ensure the sealing of the rod and limit the upwelling of hot gases in the first tubular part, the latter can internally house a guide tube in which the rod is mounted with adjusted sliding.
    [019] The guide tube may include an annular flange mounted clamped between an annular shoulder of a first end of the second tubular part and a tightening nut screwed to a second end of said second part.
    Advantageously, a seal can be mounted around the rod and compressed along said first axis between two rings, said two rings and the seal being interposed between said flange of the guide tube and the nut.
    [021] To move the second part and the first part along the second axis, the second tubular part is made integral with a second plate mounted to move along the second axis by means of a rack system .
    [022] A soleplate can be fixed to a face of the slide opposite to that supporting the first tubular part, said soleplate comprising an opening traversed by the rod and a circuit suitable for allowing circulation of a coolant and intended to be connected to means for supplying a cooling fluid.
    [023] Advantageously, the slide comprises a circuit capable of allowing air circulation and connected to means for supplying cooling air.
    The invention also relates to an air flow stream, for a turbomachine, comprising two annular inner and outer coaxial walls, and a device as described above, the slide being fixed to a radially outer face of the outer annular wall and the rod passing through said outer annular wall so that its free end is arranged between said two inner and outer annular walls.
    The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings.
    BRIEF DESCRIPTION OF THE FIGURES FIG. 1, already described, is a schematic half-view in axial section of an aircraft turbojet engine of a known type;
    FIG. 2 is a schematic perspective view of a device according to the invention for carrying out measurements of the characteristics of an air flow in an annular air flow stream;
    Fig 3 is a schematic sectional view of the device according to the invention; FIG. 4 is an enlargement of the area delimited in dotted lines in FIG. 4A;
    Figure 5 is a schematic perspective and exploded illustration of a part of the device according to the invention;
    Figure 6 is a schematic perspective view of the rod and the sealing means allowing the sliding thereof in the radial direction;
    Figure 7 is a schematic view illustrating the crushing of a seal for sliding sealing of the rod;
    FIGS. 8A, 8B and 8C are schematic views of the means allowing a displacement in a tangential direction of the measuring rod;
    FIGS. 9A, 9B and 9C are schematic views in longitudinal section of the slide and of the cylindrical slide allowing movement in a tangential direction;
    Figures 10A, 10B, 11A and 11B are schematic sectional views along a plane perpendicular to a radial direction illustrating the interior of the slide;
    FIGS. 12A, 12B and 12C are schematic perspective views and according to different cutting planes in the radial direction of the means for cooling by circulation of a liquid;
    Figure 13 is a schematic perspective view of the cooling means by air circulation of a support plate in radial translation of the measuring rod.
    DETAILED DESCRIPTION [026] FIG. 2 represents a device 46 according to the invention carried by an external casing 48 of the turbomachine and comprising three actuators 50, 52, 54, a first actuator 52 allowing the displacement of the measuring rod 44 according to a first axis 56 extending radially, a second actuator 54 allowing the rod 44 to move in rotation around said first axis 56 and a third actuator 54 allowing the rod 44 to move along a second axis 58 perpendicular to the first axis 56. The second axis 58 extends in a direction perpendicular to the radial direction which is that of the first axis 56 and perpendicular to the longitudinal direction 60 parallel to the axis 14 of rotation of the turbomachine, the air flow flowing in a sense the longitudinal direction. FIG. 3 represents the device 46 of FIG. 3, seen in section on a plane comprising the first axis 56 and the second axis 58. The device 46 comprises a first tubular part 62 extending along the first axis 56 and extending by a second tubular part 64 passing through a cylindrical slide 66 in leaktight manner mounted in a slide 68, the slide 66 being able to move along the second axis 58.
    [028] More specifically, the first tubular part 62 comprises a tubular body 70 formed at the radially internal end of the latter and made integral with a first plate 72 supporting the rod 44 for measuring in translation along the first axis 56 and rotating around the first axis 56 (Figure 4). The first plate 72 comprises an opening centered on the first axis 56 and in which are engaged coaxially with the first axis 56 a first tubular part 74a and a second tubular part 74b, the first tubular part 74a surrounding the second tubular part 74b. As can be seen in FIG. 4, the first tubular part 74a comprises at its radially internal end an annular flange 76 clamped between the tubular body 62 and the first plate 72. Also, the first tubular part 74a has a radial annular shoulder 78 and internal on which is mounted to bear radially inwards the radially internal end or first end of the second tubular part 74b. Likewise, this first end of the second tubular part 74b comprises an annular shoulder 80 on which is mounted in abutment radially inwardly an annular radial rim 82 of a guide tube 84 with sliding guide adjusted from the rod 44 according to the first axis 56 and in which the rod 44 is engaged. As is better visible in FIG. 6, the guide tube 84 is formed in two parts 84a, 84b in order to allow mounting of the guide tube 84 around the rod 44 since it comprises the means for measuring the characteristics of the air flow in its radially internal part intended to be mounted inside the vein. Each part 84a, 84b of tube 84 comprises a semi-cylindrical portion 85a, 85b connected at one end to a flange 82a, 82b radial semiannular. The flanges 82a, 82b together define the directory flange 82 and the semi-cylindrical portions 85a, 85b form a cylindrical portion 87. The second radially external end or end of the second tubular part 74b receives a nut 86 allowing the tightening of a joint 88 interposed between two rings 90a, 90b. Said two rings 90a, 90b, the seal 88 and the nut 86 are obviously coaxial with the first axis 56 and are mounted around the rod 44. The rod 44 is mounted with adjusted slip, that is to say without play in the guide tube 84 which allows it to slide freely but to avoid any rise of hot air from the annular air stream.
    [029] As shown in Figure 7, the seal 88 is substantially plane at rest and comprises two opposite faces substantially planar. The two rings 90a, 90b each include a face 92a, 92b inclined obliquely to the first axis 56, said two faces 92a, 92b inclined in a similar manner, that is to say so that the angle between them is close to zero. This conformation of the rings 90a, 90b makes it possible to ensure optimum crushing of the seal 88 and consequently improve the seal.
    The first plate 72 carries a base 94 rotatably mounted along the first axis 56. This base 94 supports the first actuator 50 carrying the rod 44 and allowing its displacement in translation in the first tubular part 62. The first plate 72 carries the second actuator 52 making it possible to rotate the base 94 around the first axis 56. In this way, it is possible to optimally orient the measuring means of the measuring rod 44 relative to the direction of air flow in the annular air stream.
    [031] The second tubular part 64 comprises a tube 96 mounted in abutment radially outward in a tubular portion 98 of a second plate 100 capable of moving along the second axis 58. This second plate 100 carries the third actuator 54 which allows, via a rack system 102 the movement of the second tubular portion 64 along the second axis 58 (Figures 8 and 9). The rack 102 is here carried by the slide 68.
    The cylindrical slide 66 is mounted in the slide 68 also of cylindrical shape and comprises a first part 104a of the slide and a second part 104b of the slide with telescopic cylindrical tubes, that is to say the tubes 106a, 106b components fit together and slide into each other. Each slide portion 104a, 104b comprises three tubes 106a, 106b nested one inside the other. The two parts 104a, 104b of slide with telescopic tubes are integral at one end with the tube 96 coaxial with the first axis 56 so as to ensure airtightness of the annular vein. As can be seen in FIG. 3, the tube 96 is dimensioned so that the rod 44 is surrounded with play by the tube 44. The use of slides with telescopic tubes has the advantage of better distributing the pressure of the vein annular air and greatly reduce the impact thereof on the sliding movement of the elementary tubes 106a, 106b of each slide portion 104a, 104b relative to each other. In an exemplary embodiment, the tubes 106a, 106b are machined with a clearance of between 8 and 15 μm so as to guarantee sliding and an absence of leakage.
    To limit the heating during operation of the device 46, there is provided a first air cooling circuit (Figures 10A and 10B) and a first cooling circuit with a liquid such as water (Figures 11A and 11 B). Thus, the slide 68 comprises, in its middle part, a first cooling air circuit 108 comprising four channels 108a, 108b, 108c, 108c extending along the second axis 58. The air circuit is in practice formed of two fluidically independent sub-circuits from each other. The first subcircuit includes channels 108a and 108c and the second subcircuit includes channels 108b and 108d. Channels 108a and 108b are connected at one end to means 109 for supplying pressurized air and are respectively connected to channels 108c and 108d, these latter channels being connected to the outside atmosphere by orifices 110 formed in the slide 68 (Figures 10A and 10B). In this way, the slide 68 can be cooled in operation.
    [034] The device 46 according to the invention is fully supported by a sole 112 for fixing to the housing, of which the bolting elements 114 can be seen in FIGS. 11A and 11B. This sole 112 includes a central opening 116 allowing the passage of the instrumented rod 44. The first water cooling circuit 118 comprises four channels 118a, 118b, 118c, 118d formed in the thickness of the sole 112 and extending along the second axis 56. A first channel 118a and a second channel 118b are formed at the same first plane transverse to the first axis 54. A third channel 118c and a fourth channel 118d are formed at the same second plane transverse to the first axis 54. The first plane is located radially outside the second plan. The first channel 118a is connected to means 120 for supplying cooling water to the sole 112, the water then flowing in the third channel 118c then in the fourth channel 118d and finally in the second channel 118b and exits by one end of it. Thus, the sole 112 is cooled in operation, making it possible to facilitate the test phases of the turbomachine.
    Note in Figures 10A, 10B, 11A and 11B that the first air cooling circuit 108 to be used without the first 118 water cooling circuit being used. For this, it is sufficient not to insert the sole 112 between the casing 48 and the first circuit 108. Obviously, the integration of the first water cooling circuit 118 makes it possible to further limit the heating of the device 48 according to the invention due, in particular, to the higher thermal conduction of water compared to air.
    The device 46 also comprises a second air cooling circuit 122 and a second cooling circuit with a liquid 124 such as water. The second water cooling circuit 124 is formed at the level of the first 74a and second 74b tubular parts as can be seen in FIGS. 12A, 12B and 12C. The first tubular part 74a comprises a lateral tip 126 for entering the coolant connected to means 128 for supplying coolant and a lateral tip 130 for leaving the coolant. The inlet nozzle 126 is placed below the outlet nozzle 128 so as to allow a flow of liquid from the bottom to the top. As can be seen in FIG. 12C, the second tubular piece 74b comprises a lower annular groove 132a and an upper annular groove 132b connected to each other by axial grooves 132c. These grooves 132a, 132b and grooves 132c define, with an internal face of the first tubular part 74a, the circuit in which the coolant is able to circulate. Thus, the coolant flows from the inlet nozzle 126 into the lower annular groove 132a, then through the grooves 132c and then flows through the upper annular groove 132b to exit through the upper nozzle 130.
    [037] Figure 13 shows the first plate 72 along a section plane perpendicular to the first axis 54. As can be seen, the first plate 72 carries a first nozzle 134 for air inlet and a second nozzle 136 for inlet air extending from opposite edges of the first plate 72 and each connected to air supply means 137. The first air inlet nozzle 134 communicates with a channel 138 for junction with an annular groove 142 fluidly connecting holes 140 formed in the thickness of the wall of the first tubular part 74a and opening along the first axis 54 and towards the top in the annular space between the base 94 and the rod 44. The second air inlet nozzle 136 communicates with axial channels 144a, 144b, 144c, 144d connected to each other and together forming a square pattern . Holes 146 are formed in the thickness of the first plate 72 and open in a first direction from the first axis 54 on the underside of the first plate 72 and in a second direction in the channels 144a, 144b, 144c, 144d. Thus, the air entering through the second nozzle 136 circulates in the channels 144a, 144b, 144c, 144d and cools the first plate 72 and exits through the holes 146.
    [038] In a particular embodiment of the device described above, it could comprise only one or at least one of the first air cooling circuit 108, the first liquid cooling circuit 118 , of the second air cooling circuit 122, of the second liquid cooling circuit 124.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1. Device (46) for measuring the characteristics of an air flow from an annular stream of a turbomachine, comprising a rod (44) extending along a given first axis (56), carrying means for measuring characteristics of a flow of air and engaged in sliding with sealing in a first tubular part (62) extending by a secondary tubular part (64) passing through with sealing along the first axis (56) a slide (66) mounted for sliding in a slide along a second axis (58) perpendicular to said first axis (56), said rod (44) being engaged with an annular clearance in said second tubular part (64).
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the slide (66), preferably cylindrical, comprises a first part (104a) of telescopic tube slide and a second part (104b) of telescopic tube slide, said first (104a) and second (104b) slide parts with telescopic tubes being sealingly secured by an axial end to said second tubular part (64).
    [3" id="c-fr-0003]
    3. Device according to claim 1 or 2, wherein the first tubular part (62) comprises a first support plate (72) supporting in rotation about the first axis (54) a first actuator (50) for translational displacement of the rod (44) along said first axis (54).
    [4" id="c-fr-0004]
    4. Device according to claim 3, wherein the first plate (72) comprises a circuit (122) adapted to allow air circulation and intended to be connected to means (137) of air supply.
    [5" id="c-fr-0005]
    5. Device according to claim 3 or 4, wherein a first tubular part (74a) and a second tubular part (74b) are mounted coaxially with the first axis (54) around the rod (44), the first tubular part (74a ) surrounding the second tubular part (74b) and delimiting with it a circuit (124) capable of allowing a circulation of a coolant which is intended to be connected to means (128) for supplying coolant .
    [6" id="c-fr-0006]
    6. Device according to claims 4 and 5, wherein the first tubular part (74a) is inserted into an opening of the first plate (72) and is made integral with said first plate (72).
    [7" id="c-fr-0007]
    7. Device according to one of claims 1 to 6, in which the first tubular part (62) internally houses a guide tube (84) in which the rod (44) is mounted with adjusted slip.
    [8" id="c-fr-0008]
    8. Device according to claim 7 in combination with claim 5, wherein the guide tube (84) comprises an annular flange (82) mounted clamped between an annular shoulder (80) of a first end of the second tubular part ( 74a) and a tightening nut (86) screwed to a second end of said second tubular part (74b).
    [9" id="c-fr-0009]
    9. Device according to claim 8, wherein a seal (88) is mounted around the rod (44) and compressed along said first axis (54) between two rings (90a, 90b), said two rings (90a , 90b) and the seal (88) being interposed between said annular flange (82) of the guide tube (84) and the nut (86).
    [10" id="c-fr-0010]
    10. Device according to one of claims 1 to 9, in which the second tubular part (64) is integral with a second plate (100) mounted to move along the second axis (56) via a system rack and pinion.
    [11" id="c-fr-0011]
    11. Device according to one of claims 1 to 10, comprising a sole (112) fixed to a face of the slide (68) opposite to that supporting the first tubular part (62), said sole (112) comprising a through opening by the rod (44) and a circuit (118) adapted to allow a circulation of a coolant and intended to be connected to means (120) for supplying a coolant.
    [12" id="c-fr-0012]
    12. Device according to one of claims 1 to 11, wherein the slide (68) comprises a circuit (108) adapted to allow air circulation and connected to means (109) for supplying cooling air.
    [13" id="c-fr-0013]
    13. Air flow stream, for a turbomachine, comprising two annular inner and outer coaxial walls, and a device (46) according to one of claims 1 to 12, in which the slide (68) is fixed on one face radially outer of the outer annular wall 5 (48) and the rod (44) passing through said outer annular wall (48) so that its free end is arranged between said two inner and outer annular walls.
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    同族专利:
    公开号 | 公开日
    EP3769067A2|2021-01-27|
    CN111954798A|2020-11-17|
    WO2019180383A2|2019-09-26|
    US20210033492A1|2021-02-04|
    FR3079299B1|2020-06-05|
    WO2019180383A3|2020-03-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5076108A|1990-08-23|1991-12-31|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administrator|Probe insertion apparatus with inflatable seal|
    FR3036735A1|2015-05-26|2016-12-02|Snecma|INSTRUMED VEIN OF TURBOMACHINE|
    FR3043203A1|2015-11-04|2017-05-05|Snecma|DEVICE FOR MEASURING PARAMETERS OF AERODYNAMIC FLOW OF A TURBOMACHINE, TURBOMACHINE EQUIPPED WITH SUCH A DEVICE AND METHOD FOR MANUFACTURING A SEAL FOR SEALING SUCH A DEVICE|
    FR3043464A1|2015-11-06|2017-05-12|Snecma|MEASURING DEVICE FOR A GAS FLOWING VEIN OF A TURBOMACHINE|
    FR3051908A1|2016-05-24|2017-12-01|Snecma|ANTI-BENDING DEVICE FOR TURBOMACHINE PROBE|
    US11215117B2|2019-11-08|2022-01-04|Raytheon Technologies Corporation|Gas turbine engine having electric motor applying power to the high pressure spool shaft and method for operating same|
    FR3112190A1|2020-07-02|2022-01-07|Safran|Turbomachine probe support|
    法律状态:
    2019-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2019-09-27| PLSC| Publication of the preliminary search report|Effective date: 20190927 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-02-18| PLFP| Fee payment|Year of fee payment: 4 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1852500A|FR3079299B1|2018-03-22|2018-03-22|DEVICE FOR MEASURING THE CHARACTERISTICS OF AN AIR FLOW|
    FR1852500|2018-03-22|FR1852500A| FR3079299B1|2018-03-22|2018-03-22|DEVICE FOR MEASURING THE CHARACTERISTICS OF AN AIR FLOW|
    EP19718902.0A| EP3769067A2|2018-03-22|2019-03-20|Device for measuring the characteristics of an air flow|
    CN201980019575.9A| CN111954798A|2018-03-22|2019-03-20|Apparatus for measuring gas flow characteristics|
    US16/981,815| US20210033492A1|2018-03-22|2019-03-20|Device for measuring the characteristics of an air flow|
    PCT/FR2019/050641| WO2019180383A2|2018-03-22|2019-03-20|Device for measuring the characteristics of an air flow|
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