• 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 present invention relates to a device for measuring aerodynamic quantities (1) intended to be placed transversely in a flow passage (12, 13) of a turbomachine comprising: an upstream body (2) having a generally cylindrical shape profile defining a leading edge (5) - a plurality of sensors (4), the instrumentation lines (45) of the sensors being placed in the body (2), the sensing elements (41) of the sensors extending at the leading edge (5); - A downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6); the downstream fairing (3) comprising, in the longitudinal direction of the upstream body (2), a plurality of sections (35) fixed independently of one another to the body (2), two successive sections (35) being connected by a junction (37) flexible.
    公开号:FR3043775A1
    申请号:FR1560803
    申请日:2015-11-12
    公开日:2017-05-19
    发明作者:Jeremy Giordan；Florian Joseph Bernard Kockenpo
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Device for measuring aerodynamic quantities intended to be placed in a flow vein of a turbomachine
    FIELD OF THE INVENTION
    The present invention relates to the general field of devices for measuring aerodynamic quantities, and in particular pressure and temperature, in a flow vein of a turbomachine.
    STATE OF THE ART
    FIG. 1 schematically represents a turbomachine 10 of the double-flow and double-body type to which the invention applies in particular. Of course, the invention is not limited to this particular type of turbojet engine and applies to other turbojet engine architectures and in particular dual-flow and double-body.
    The turbomachine 10 comprises, from upstream to downstream in the direction of the flow of the gases, a fan 11, one or more stages of compressors 17, a combustion chamber 14, one or more turbine stages 15 and a nozzle. exhaust gas.
    The turbojet also comprises an intermediate casing 20 having, in known manner, a structural function (because the forces are transmitted through it). In particular, the fastening means of the turbojet engine to the structure of the aircraft in the front part are integral with the intermediate casing. The intermediate casing 20 consists of a hub 25, an outer annular shell 24 disposed around the hub concentrically therewith.
    The turbojet engine comprises two coaxial gas flow flow veins, namely a primary flow stream (or hot flow) 12, and a secondary flow flow stream (or cold flow) 13.
    In the context of tests on a turbomachine, it is sometimes necessary to make measurements of the aerodynamic quantities, in particular of pressure and temperature, of the gaseous flow flowing in the flow veins 12 or 13 of a turbomachine.
    With reference to FIGS. 1 and 2, it is known to measure these aerodynamic quantities by means of a device for measuring aerodynamic quantities 1, placed substantially radially in a flow path 13 or 12 of a turbomachine, comprising a cylindrical body 2 and a plurality of sensors 4 of aerodynamic magnitude placed in the cylindrical body 2, the sensitive elements 41 of the sensors extending outside the cylindrical body 2 at a leading edge 5. This measuring device 1 is usually called combs, probes or rakes.
    The aerodynamic losses created by the presence of the measuring device 1 in the flow line 12 or 13 disturb this flow when it enters the turbomachine, which has the consequence of disrupting the operation of the turbomachine 10 and consequently to distort measurements of aerodynamic magnitudes carried out.
    In order to limit the drag of the measuring device 1 in the flow path 12 or 13, it is known to add a fairing 3 attached to the body 2 so as to close its trailing edge sufficiently far downstream to avoid delamination. downstream flow (Figure 2).
    The measuring device 1 in the flow line 12 or 13 is subjected to high vibratory stresses.
    A first vibratory source is for example consecutive residual unbalance rotating sets, that is to say low-pressure rotors and high-pressure. A second vibratory source originates from the alternation of the compression and vacuum phases due to the rotation of a row of moving blades. This second vibratory source is particularly important when the measuring member is arranged immediately downstream of a moving wheel. By way of example, a fan wheel, comprising 30 blades, rotating at a speed of rotation of 2000 revolutions per minute, creates a vibration at a frequency of 1000 Hz. If the first eigenmode of the measuring device is close to 1000 Hz, the organ then has a high risk of resonating.
    A measuring device 1 has eigen frequencies which are fixed and which are a function of its structural and dimensional characteristics. When the vibration frequency of the device 1 approaches its rank 1 resonance frequency or its harmonic eigenfrequencies, for example that of rank 2, the risk of resonance of the device becomes high.
    The resonance phenomena of the measuring device 1 are liable to cause cracks in the measuring device 1 that may impact its mechanical integrity. In extreme cases, the formation of cracks or cracks resulting from the vibrations can lead to the partial or total dislocation of the device. Debris thus released circulates in the vein and can damage parts of the turbomachine arranged downstream. It is understood that the damage caused by such dislocation can be particularly important when the measuring device is mounted in the primary vein 12 since the debris can damage the combustion chamber and the fixed and rotating parts of the high and low pressure turbines.
    SUMMARY OF THE INVENTION
    An object of the invention is to provide a device for measuring aerodynamic quantities having a better mechanical strength when placed in a flow vein of a turbomachine.
    This object is achieved within the scope of the present invention by means of a device for measuring aerodynamic quantities intended to be placed transversely in a flow vein of a turbomachine comprising: an upstream body having a profile of generally cylindrical shape defining a leading edge ; a plurality of sensors comprising instrumentation lines and sensitive elements, the instrumentation lines of the sensors being placed in the body, the sensitive elements of the sensors extending at the leading edge; a downstream fairing mounted on the upstream body and defining a trailing edge; the aerodynamic magnitude measuring device being characterized in that said downstream fairing comprises, in the longitudinal direction of the upstream body carrying the sensors, a plurality of downstream fairing sections attached independently of one another to the body, two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections.
    The fact that the downstream fairing is split transversely into several sections, each fixed independently to the upstream body, and linked together by a flexible junction, minimizes the vibratory response of the assembly constituted by the device, when it is subject the vibratory stresses of the stream flow flow, and therefore improve the mechanical strength of the measuring device in the flow vein.
    Indeed, the flexible junction makes it possible to introduce a rupture of stiffness in the structure of the measuring device, which makes it possible to reduce the vibratory response of the device when it is positioned in the flow vein.
    In addition, the position of the flexible junction in the longitudinal direction allows to play on the stiffness of the device and therefore on the resonance frequency thereof, whether the frequency of rank 1 and / or its harmonics. The position of the flexible junction will be chosen so that the resonant frequency of the device does not coincide with the frequencies of vibrations in the flow vein. The invention is advantageously supplemented by the following characteristics, taken individually or in any of their technically possible combinations.
    The downstream fairing consists of two sections.
    The sections have, in the longitudinal direction of the upstream body, a Young's modulus of more than 50GPa.
    The flexible junction has, in the longitudinal direction of the upstream body, a Young's modulus of less than 1GPa.
    The flexible junction is made of elastomer.
    The sections are made of metal. The metal has a lower roughness than the overmolded elastomers, which makes it possible to limit the disturbances induced by the device on the downstream flow.
    The downstream fairing is attached to the upstream body by hooping.
    The downstream fairing is fixed to the upstream body by means of pins. The pins are the only points of connection between the upstream body and the downstream fairing. Their position and their number makes it possible to play on the cantilevered free length and the cantilever mass of the device and therefore on the resonance frequencies thereof. The term "natural frequency" here includes the natural frequency of rank 1 and / or its harmonics. The invention also relates to a method for determining the position of the flexible junction, or, where appropriate, flexible junctions, in the longitudinal direction of a device for measuring aerodynamic quantities intended to be placed in a flow duct. a turbomachine, characterized in that it comprises steps of: determining the vibratory frequencies in the flow vein; determining the position of the flexible junction in the longitudinal direction of the upstream body, so that at least one natural frequency, and preferably at least the first order natural frequency, and preferably all the natural frequencies, of the measuring device aerodynamic magnitudes do not coincide with the vibratory frequencies in the flow vein. The invention also relates to a method for determining the position of the flexible junction or, where appropriate, flexible junctions, and / or the number and / or position of the pins in a device for measuring aerodynamic quantities, characterized in that it comprises steps of: - determination of vibratory frequencies in the flow vein; determination of the position of the flexible junction, and / or the number and / or position of the pins so that at least one natural frequency, and preferably at least the first order natural frequency, and preferably all the natural frequencies, , the device for measuring aerodynamic quantities does not coincide with the vibratory frequencies in the flow vein. The invention also relates to a method for testing a turbomachine, characterized in that it comprises a step during which a device for measuring aerodynamic quantities is placed in a flow vein of the turbomachine.
    DESCRIPTION OF THE FIGURES Other objectives, characteristics and advantages will become apparent from the detailed description which follows with reference to the drawings given by way of non-limiting illustration, among which: FIG. 1, discussed above, is a simplified diagram of a turbomachine on which is located the flow vein of the flow; FIG. 2, discussed above, represents a device for measuring aerodynamic quantities according to the prior art; FIGS. 3 and 4 show a device for measuring aerodynamic quantities arranged in a flow vein, FIG. 3 being a view perpendicular to the plane containing the longitudinal axis of the device and the motor axis, and FIG. view along the longitudinal axis of the device; FIG. 5 is a cross-sectional view of a device for measuring aerodynamic quantities according to the invention; FIG. 6 is a perspective view showing the side of a device for measuring aerodynamic quantities according to the invention; FIG. 7 is a view partially in longitudinal section of a device for measuring aerodynamic quantities according to the invention; FIG. 8 represents the instrumentation wires and the mounting plate of a device for measuring aerodynamic quantities according to the invention; - Figure 9a illustrates a pin protruding from the downstream fairing inserted in a mortise formed in the upstream body; FIG. 9b illustrates a mortise formed in the upstream body; - Figure 9c ilustre a stud protruding from the downstream fairing; FIG. 10 illustrates the adjustment parameters of a device for measuring aerodynamic quantities according to the invention; - Figure 11 shows on the abscissa the distance of the flexible junction at the end of the downstream fairing along the length of the downstream fairing and the ordinate the abatement of eigenfrequencies for the modes 1F (tangential bending) and 1E (axial flexion).
    DETAILED DESCRIPTION OF THE INVENTION
    With reference to FIG. 1, the device for measuring aerodynamic quantities 1 is intended to be placed substantially transversely in the primary flow flow path 12, or in the secondary flow flow path 13.
    With reference to FIGS. 3 and 4, the measurements are characterized by the immersion of the device 1 in the vein, characterized by the distance R from the sensor to the axis of the motor Am, the angle of incidence a of the flow on the device 1 which is the angle between the axis of the engine Am and the longitudinal direction A1 of the device 1 and the angle of wiping β which is the angle between the axis of the engine Am and the direction Ac in which the downstream fairing 3.
    With reference to FIGS. 5 to 7, the device for measuring aerodynamic quantities 1 comprises a hollow upstream body 2, a plurality of sensors 4 of aerodynamic size placed in the upstream body 2, and a downstream fairing 3.
    Upstream body 2
    The upstream body 2 has a generally cylindrical profile.
    The surface of the upstream body 2 is defined by a generatrix keeping a fixed direction which defines the longitudinal direction of the upstream body.
    The upstream body 2 is typically a hollow cylinder. In particular, the upstream body 2 may be a cylinder of circular, oval or C-shaped section. The upstream body 2 is preferably made of metal or rigid plastic (rigid means that having a Young's modulus of more than 50GPa). .
    With reference to FIG. 8, the upstream body 2 is fixed substantially radially in the secondary flow flow channel 13 either to the outer annular shroud 24 or to the hub 25, or both to the outer annular shroud 24 and to the hub 25. In particular, the upstream body 2 can be fixed by a fixing plate 27 on the inner wall of the outer annular shell 24 as illustrated in FIG. 8.
    Sensors 4
    The sensors 4 are pressure and temperature probes. By way of example, the temperature probes may be of the thermocouple sensor type, the sensitive element of the probe consisting of two metals of different resistivity connected together, so as to generate a potential difference which can be connected to the measured temperature.
    Such a temperature probe is well known to those skilled in the art and will not be described in detail here. By way of example, the pressure probes may especially be instrumentation tubes such as Kiel probes. Such pressure sensors are well known to those skilled in the art and will not be described in detail.
    The sensitive elements 41 of the sensors extending outside the upstream body 2 at the leading edge 5.
    The sensors 4 are connected to a computer (not shown in the figures) where the measured data are processed. The sensors 4 are connected to the computer by instrumentation lines 45 (FIG. 8) which are placed in the cylindrical upstream body 2. The computer is typically located outside the engine.
    Downstream fairing 3
    Referring to Figure 5, the downstream fairing 3 has a longitudinal face 31 adapted to be assembled on the upstream body 2. The downstream fairing 3 has two other longitudinal faces 32 which meet in a stop which constitutes the trailing edge 6 when the measuring device is positioned in the flow path 13.
    The face of the upstream body 2 not covered by the downstream fairing and opposite to the downstream fairing 3 forms the leading edge 5 when the measuring device 1 is placed in the flow path 13.
    The distance between the attachment point of the downstream fairing 3 to the cylindrical upstream body 2 and the trailing edge 6 is called the free length L overhang of the device 1. The free length L overhang is typically comprised between 2 and 4cm.
    The downstream fairing 3 is typically of generally cylindrical shape.
    The length of the downstream fairing 3, that is to say its dimension in the longitudinal direction, is typically between 1cm and 1m.
    The downstream fairing 3 comprises, in the longitudinal direction of the upstream body 2, several downstream fairing sections 35 fixed independently of each other to the body 2. For this purpose, the downstream fairing 3 is split, in transverse directions, into several sections. 35 mounted on the upstream body 2 side by side so as to be aligned with each other in the longitudinal direction of the upstream body.
    In particular, the downstream fairing 3 can consists of two sections 35.
    The downstream fairing 3 is preferably metallic. In fact, the metal has a lower roughness than the overmolded elastomers, which makes it possible to limit the disturbances induced by the device 1 on the downstream flow. The downstream fairing 3 can be obtained cut into the mass and then split into sections 35.
    The sections 35 are each independently attached to the upstream body 2.
    The transverse sections 35 are typically mounted by hooping on the upstream body 2.
    The longitudinal face 31 of the sections 35 adapted to be assembled on the cylindrical upstream body 2 has, for this purpose, a pin 36 protruding from the longitudinal face 31 and adapted to be inserted into a corresponding mortise 26, made in the upstream body 2 (as shown in Figure 9a). As illustrated in FIG. 9b, the mortise 26 is a cavity made in the upstream body 2, to receive the tenon 36 of the sections 35. As illustrated in FIG. 9c, the post 36 is a cylindrical projection, generally of rectangular section. The mortise 26 is a cylindrical cavity, complementary to the post 36 and generally of rectangular section. The pins 36 are supported in a mortise 26 and not assembled by tight fit.
    The sections 35 may also be held by pins 7, so as to limit their rotation on the upstream body. The pins 7 are inserted into the upstream body 2 so as to pass through the mortise 26 and the tenon 36 without exceeding the upstream body 2.
    The pins 7 are typically cylindrical elements and generally made of metal. They can be grooved with longitudinal grooves causing swelling of the metal by repression; in the assembly, the splines are elastically deformed and ensure adherent assembly without play.
    The pins 7 can also be threaded.
    The sections 35 has a low but non-zero elasticity which allows them to deform elastically under the effect of aerodynamic stresses when the device 1 is disposed in the vein. The sections 35 have, in the longitudinal direction of the upstream body, a Young's modulus typically of more than 50GPa, for example 69GPa for aluminum.
    The sections 35 are mounted to travel constrained relative to each other. For this purpose, two successive sections 35 are interconnected by a junction 37 which in the longitudinal direction of the upstream body 2 is more flexible than the sections 35.
    By more flexible in the longitudinal direction of the upstream body is meant that the junction 37a Young's modulus, in the longitudinal direction of the upstream body, lower than the sections 35. The flexible junction 37 is typically elastomeric. The flexible junction 37 typically has, in the longitudinal direction of the upstream body, a Young's modulus of less than 1GPa.
    The flexible junction 37 extends between the transverse faces of two adjacent sections 35. The flexible junction 37 is preferably attached to each section 35 over the entire transverse face thereof, to maximize the adhesion of the flexible junction 37 to the section 35.
    Flexible junction 37 is typically made by injection molding. The plastic is softened by heating and then injected between the two sections 35, and then cooled.
    The flexible junction 37 may also be made by polymer vulcanization.
    The length of the flexible junction 37 in the longitudinal direction is typically 1mm to 3mm.
    The flexible junction 37 makes it possible to introduce a rupture of stiffness in the structure of the measuring device 1, which makes it possible to reduce the vibratory behavior of the device 1 when it is positioned in the flow channel.
    The fact that the downstream fairing 3 is split into sections 35 linked by a flexible junction 37 allows an adaptation of the eigenfrequencies of the assembly constituted by the device 1.
    With reference to FIG. 10, the location of the flexible junction 37, and / or the number and / or the position of the pins 7, are chosen so as to optimize the vibratory behavior of the device 1 when it is arranged in the vein flow, and this for all engine speeds envisaged (idle speed, cruising speed, etc.).
    The beam theory gives a canonical expression for the eigenfrequencies of a mechanical system whose morphology is similar to device 1:
    With: at2coefficient which depends on the order of the mode ie {1, 2, ...} and conditions of attachment of the device in the vein; L: cantilever free length of device 1, K: stiffness of device 1, M: cantilever mass of device 1,
    The coefficient of stiffness K depends on the positioning of the flexible junction (s) 37 in the longitudinal direction of the upstream body.
    As illustrated in FIG. 11, which represents the abatement of the eigenfrequencies for the modes 1F (tangential bending) and 1E (axial bending), namely the ratio between the natural frequency of a device without flexible junction and the natural frequency of a device with flexible junction, with respect to the position of the flexible junction 37 in the longitudinal direction of the device 1, namely the ratio (distance of a single flexible junction 37 to the end of the downstream fairing 3 / length of the fairing downstream), plus the flexible junction 37 is positioned in the middle of the device 1, plus eigenfrequency frequencies are low, conversely, the more the flexible junction 37 is far from the middle of the device 1, the higher eigenfrequency frequencies are high.
    As can be seen in FIG. 11, the abatement of the eigenfrequencies is particularly important on the domain [0.3; 0.7]
    Moreover, the coefficient of stiffness K, the mass M and the cantilevered free length L depend on the number and the position of the pins 7.
    Indeed, the pins 7 are the only connection points between the upstream body 2 and the downstream fairing 3. Their position allows to play on the free length Cantilever L and mass M cantilever. The longer the cantilevered free length L is, the lower the eigenfrequencies and vice versa.
    The location of the flexible junction 37, and / or the number and / or the position of the pins 7 are chosen so that the eigenfrequencies of the assembly constituted by the device 1 do not coincide with the vibratory frequencies induced by the flow in the flow vein, to prevent the assembly constituted by the device 1 resonates when it is placed in the flow of the flow vein.
    It should be noted that the device 1 makes it possible to adapt the eigenfrequencies of the assembly constituted by the device 1 upwards or downwards, whereas a fully flexible downstream fairing only makes it possible to lower the eigenfrequencies of the device 1. set constituted by the device. Indeed, a stiffness gain K results in an increase of the eigenfrequencies and a gain of mass M results in a decrease of the eigenfrequencies.
    The location of the flexible junction 37, or optionally flexible junctions, and / or the number and / or position of the pins 7 may in particular be determined by a method comprising steps of: - determination of the vibratory frequencies in the vein 12 or 13; determination of the location of the flexible junction 37, and / or the number and / or position of the pins 7 so that at least one natural frequency, and preferably at least the first order natural frequency, and preferably all the eigenfrequencies, the device for measuring aerodynamic quantities 1 does not coincide with the vibratory frequencies in the flow vein 13.
    The determination of vibratory frequencies in the flow vein may be made by calculation or performed experimentally or by any other suitable method.
    The location of the flexible junction 37 and / or the number and / or position of the pins 7 may in particular be determined by an iterative method. Starting with a choice of an initial position of the flexible junction 37, and / or the number and / or the position of the pins 7 considered as a first blank, it is proceeded by iterations during which a succession of approximate solutions is determined. refined which gradually minimize the vibratory response of the assembly constituted by the device 1. Preferably, the location of the flexible junction 37 and / or the number and / or position of the pins 7 are determined by proceeding first to the determining the location of the flexible junction 37 by iterations, then determining the number of pins 7 by iterations, and then determining the position of each pin 7 by iterations.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Device for measuring aerodynamic quantities (1) intended to be placed transversely in a flow passage (12, 13) of a turbomachine comprising: - an upstream body (2) having a generally cylindrical profile defining an edge driver (5) - a plurality of sensors (4) having instrumentation lines (45) and sensitive elements (41), the instrumentation lines (45) of the sensors being placed in the body (2), the sensing elements (41) of the sensors extending at the leading edge (5); - A downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6); the aerodynamic magnitude measuring device (1) being characterized in that said downstream fairing (3) comprises, in the longitudinal direction of the upstream body (2) carrying the sensors, a plurality of downstream fairing sections (35) independently fixed to each other. other to the body (2), two successive sections (35) being connected by a junction (37) which in the longitudinal direction of the upstream body (2) is more flexible than the sections (35).
    [2" id="c-fr-0002]
    2. Device for measuring aerodynamic quantities (1), according to the preceding claim, wherein the downstream fairing (3) consists of two sections (35).
    [3" id="c-fr-0003]
    3. Apparatus for measuring aerodynamic quantities (1), according to one of the preceding claims, wherein the sections (35) have, in the longitudinal direction of the upstream body, a Young's modulus of more than 50GPa.
    [4" id="c-fr-0004]
    4. Apparatus for measuring aerodynamic quantities (1), according to one of the preceding claims, wherein the flexible junction (37) has, in the longitudinal direction of the upstream body, a Young's modulus of less than 1GPa.
    [5" id="c-fr-0005]
    5. A device for measuring aerodynamic quantities (1), according to one of the preceding claims, wherein the flexible junction (37) is elastomeric.
    [6" id="c-fr-0006]
    6. Apparatus for measuring aerodynamic quantities (1), according to one of the preceding claims, wherein the sections (35) are metal.
    [7" id="c-fr-0007]
    7. Apparatus for measuring aerodynamic quantities (1) according to one of the preceding claims, wherein the downstream fairing (3) is fixed to the upstream body (2) by hooping.
    [8" id="c-fr-0008]
    8. Apparatus for measuring aerodynamic quantities (1) according to one of the preceding claims, wherein the downstream fairing (3) is fixed to the upstream body (2) by means of pins (7).
    [9" id="c-fr-0009]
    9. A method for determining the position of at least one flexible junction (37) of a device for measuring aerodynamic quantities (1) according to one of the preceding claims, characterized in that it comprises steps of: - determining vibratory frequencies in the flow vein (13); determination of the position of at least one flexible junction (37) in the longitudinal direction of the upstream body, so that at least one natural frequency of the device for measuring aerodynamic quantities (1) does not coincide with the vibratory frequencies in the flow vein (13).
    [10" id="c-fr-0010]
    Method for determining the position of at least one flexible junction (37) of a device for measuring aerodynamic quantities (1), and / or the number and / or position of the pins (7) in a device aerodynamic magnitudes measurement (1), according to claim 8, characterized in that it comprises steps of: - determination of vibratory frequencies in the flow vein (13); determining the position of the flexible junction (37) in the longitudinal direction of the upstream body, and / or the number and / or position of the pins (7) so that at least one natural frequency of the device measurement of aerodynamic quantities (1) does not coincide with the vibratory frequencies in the flow vein (13).
    [11" id="c-fr-0011]
    11. A method of testing a turbomachine (10), characterized in that it comprises a step during which is placed a device for measuring aerodynamic quantities (1), according to one of claims 1 to 8, in a flow vein (12, 13) of the turbomachine (10).
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    FR3072169B1|2017-10-09|2019-10-11|Safran Aircraft Engines|DEVICE FOR MEASURING AT LEAST ONE PARAMETER OF AERODYNAMIC FLOW OF A TURBOMACHINE EQUIPPED WITH A VIBRATION DAMPING MEANS AND TURBOMACHINE VEIN EQUIPPED WITH SUCH A DEVICE|
    US10598041B2|2017-10-20|2020-03-24|United Technologies Corporation|Inlet performance measurement system for gas turbine engine|
    FR3079613B1|2018-03-30|2021-07-30|Safran Aircraft Engines|MODULAR MEASURING DEVICE OF PARAMETERS OF AN AERODYNAMIC FLOW OF A TURBOMACHINE AND TURBOMACHINE EQUIPPED WITH SUCH A DEVICE|
    US10684183B2|2018-04-24|2020-06-16|The Boeing Company|Powered total pressure measurement rake with telemetry|
    US11193854B2|2018-06-20|2021-12-07|Rolls-Royce Plc|Estimating fluid parameter|
    US10704413B2|2018-09-06|2020-07-07|Raytheon Technologies Corporation|Systems and methods for variable alignment aerodynamic probes|
    FR3087266B1|2018-10-16|2021-02-12|Safran Aircraft Engines|DEVICE FOR MEASURING PARAMETERS OF A SEGMENTED AERODYNAMIC FLOW, TURBOMACHINE VEIN EQUIPPED WITH SUCH MEASURING DEVICE AND TURBOMACHINE INCLUDING SUCH A DEVICE OR A VEIN|
    FR3112807A1|2020-07-24|2022-01-28|Safran Aircraft Engines|Support device for means for visualizing a flow in an aircraft engine|
    法律状态:
    2016-11-08| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-19| PLSC| Publication of the preliminary search report|Effective date: 20170519 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1560803A|FR3043775B1|2015-11-12|2015-11-12|DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE|FR1560803A| FR3043775B1|2015-11-12|2015-11-12|DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE|
    EP16198037.0A| EP3168586B1|2015-11-12|2016-11-09|Device for measuring aerodynamic variables intended for being placed in an air stream of a turbine engine|
    US15/348,824| US10138754B2|2015-11-12|2016-11-10|Device for measuring aerodynamic magnitudes intended to be placed in a flow passage of a turbine engine|
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