• 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 in a flow vein (13) of a turbomachine comprising: - an elongate body (2) having at least one longitudinal cylindrical face (21) ; a plurality of sensors (4) of aerodynamic magnitude placed in the body (2), the sensitive elements (41) of the sensors extending outside the body (2) at a leading edge (5); - A fairing (3) partially surrounding the body, having a concave longitudinal face (31) complementary to the cylindrical face of the body (2) and forming trailing edge (6), the face of the body (2) not covered by the fairing and opposed to the fairing (3) forming the leading edge (5); the aerodynamic magnitude measuring device (1) being characterized in that the fairing (3) is mounted for rotation with constrained clearance around the body (2).
    公开号:FR3025885A1
    申请号:FR1458651
    申请日:2014-09-15
    公开日:2016-03-18
    发明作者:Vianney Christophe Marie Maniere；Henri Marie Damevin；Philippe Jacques Pierre Fessou；Mathieu Gaillot；Gilles Pierre-Marie Notarianni
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] 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 the flow vein of a turbomachine.
    [0002] STATE OF THE ART In the context of tests on a turbomachine, it is sometimes necessary to measure the aerodynamic quantities, in particular the pressure and the temperature, of the gaseous flow flowing in the flow path 13 of a turbomachine. (figure 1). With reference to FIGS. 2, 3 and 4, 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 6 of a turbomachine, comprising a 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 body 2 at a leading edge 5. This measuring device generally carries the comb name of probes.
    [0003] The aerodynamic losses created by the presence of the measuring device 1 in the stream flow stream 8 disturb this flow when it enters the high-pressure compressor, which has the consequence of disrupting the operation of the turbomachine 10 and by consequently to distort the measurements of aerodynamic quantities carried out.
    [0004] In order to limit the drag of the measuring device 1 in the flow path 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). This solution effectively limits the drag of the measuring device 1 in the flow path 13, as long as the incidence of the flow with respect to the axis of the measuring device 1 is low (FIG. 3). On the other hand, when this incidence increases, a zone D of major flow recession is created downstream (Figure 4). SUMMARY OF THE INVENTION The invention makes it possible to effectively limit the drag of the measuring device regardless of the impact of the flux with respect to the axis of the measuring device.
    [0005] To this end, the invention proposes a device for measuring aerodynamic quantities intended to be placed in a flow vein of a turbomachine comprising: an elongate body having at least one cylindrical longitudinal face; a plurality of aerodynamic size sensors placed in the body, the sensor sensitive elements extending outside the body at a leading edge; a fairing forming a trailing edge, partially surrounding the body, and having a longitudinal face complementary to the cylindrical longitudinal face of the body, the face of the body not covered by the fairing and opposite to the fairing forming the leading edge; the aerodynamic magnitude measuring device being characterized in that the fairing is rotatably mounted with constrained travel about the body.
    [0006] The invention is advantageously completed by the following characteristics, taken individually or in any of their technically possible combinations: the body is of circular section; The sensitive elements of the sensors extending on the leading edge of the body; - The fairing surrounds the body at an angle between 190 ° to 320 °; the longitudinal face in contact with the body being concave, the curvature of the face being chosen greater than that of the body; The device for measuring aerodynamic quantities further comprises a system for locking the rotation of the fairing around the body; the device for measuring aerodynamic quantities further comprises a control system for locking the rotation of the fairing around the body, the control system being adapted to release the rotation of the fairing around the body during a change of motor operating point and to lock the rotation of the fairing around the body during a measurement of aerodynamic quantities; The fairing is rotatably mounted on the constrained displacement body over an angular range of between -20 and 20 °. The invention also relates to a method for measuring aerodynamic quantities using a device placed in a flow vein of a turbomachine comprising: an elongated body having at least one longitudinal cylindrical face; a plurality of sensors aerodynamic magnitudes placed in the body, the sensing elements of the sensors extending out of the body at a leading edge; - a fairing partially surrounding the body, having a complementary face of the cylindrical longitudinal face of the body and forming trailing edge, the face of the body not covered by the fairing and opposite to the fairing forming the leading edge; The method being characterized in that it comprises a step of measuring the aerodynamic quantities, the fairing being mounted to travel constrained to rotate around the body, so that the trailing edge of the fairing is always placed in the axis of impact of the flow.
    [0007] The method for measuring aerodynamic quantities advantageously comprises steps of: - changing the operating point of the motor; - Release the rotation of the fairing around the body until the fairing stabilizes; 15 - locking the rotation of the fairing around the body; - measurement of aerodynamic quantities. DESCRIPTION OF THE FIGURES Other objectives, features and advantages will become apparent from the detailed description which follows with reference to the drawings given by way of nonlimiting illustration, in which: FIG. 1 is a simplified diagram of a turbomachine on which is located the flow vein flow; Figure 1a shows a measuring device according to the invention; FIG. 2 represents a device for measuring aerodynamic quantities according to the prior art; FIGS. 3 and 4 show the aerodynamic recoil zone around a measuring device according to the prior art for different angles of incidence of the flux; FIG. 5 represents a measuring device according to the invention; FIGS. 6 and 7 represent the aerodynamic separation zone around a measuring device according to the invention for different angles of incidence of the flow.
    [0008] DETAILED DESCRIPTION OF THE INVENTION Positioning in the Turbomachine FIG. 1 schematically represents a turbomachine 10 of the double-flow, 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 architectures of turbojets with double flow and double body. The turbomachine 10 comprises, from upstream to downstream in the direction of flow 15 of the gases, a fan 11, one or more stages of compressors 17, a combustion chamber 14, one or more stages of turbines 15 and a nozzle of 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.
    [0009] The turbojet comprises two coaxial gas flow flow veins, namely a primary flow flow (or hot flow) 12, and a secondary flow flow (or cold flow) flow. Aerodynamic magnitudes measurement 1 is intended to be placed substantially radially in the secondary flow stream 13 of the turbomachine 10.
    [0010] With reference to FIGS. 5 to 7, the device for measuring aerodynamic quantities 1 comprises a hollow body 2, a plurality of sensors 4 of aerodynamic size placed in the body 2, and a fairing 3.
    [0011] Cylindrical body 2 The body 2 is elongate and has at least one cylindrical longitudinal face 21. The body 2 is typically a hollow cylinder. In particular, the body 2 may be a cylinder of circular, oval or C-shaped section. Referring to FIG. 1a, the body 2 is fixed radially in the secondary flow stream 13 to the ferrule outer ring 24 is at the hub 25, or both at the outer annular shell 24 and the hub 25.
    [0012] In particular, the body 2 can be fixed by an attachment plate 26 to the inner wall of the outer annular shell 24 as illustrated in FIG. 1a. 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 sensing element of the probe consisting of two different resistivity metals connected together, so as to generate a potential difference which can be connected at 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.
    [0013] The sensitive elements 41 of the sensors extending outside the body 2 at the leading edge 5. The sensitive elements 41 of the sensors 4 extending extending over the leading edge of the body 2 in a direction AT.
    [0014] 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 wires 45 (FIG. 1) which are placed in the cylindrical body 2.
    [0015] Fairing 3 The fairing 3 has a longitudinal face 31 complementary to the longitudinal cylindrical face 21 of the body 2. The longitudinal face 31 of the fairing 3 is in contact with the cylindrical body 2. The fairing 3 has two other longitudinal faces 32 which form together the trailing edge 6 when the measuring device is positioned in the flow path 13. The face 22 of the body 2 not covered by the shroud and opposite to the shroud 3 forms the leading edge 5 when the measuring device 1 The fairing 3 is typically cylindrical in shape. The fairing 3 partially surrounds the cylindrical body 2.
    [0016] The shroud 3 typically surrounds the body 2 at an angle of between 190 ° and 320 °. The shroud 3 is rotatably mounted around the longitudinal axis of the body 2.
    [0017] The shroud 3 is mounted with constrained clearance on the body 2, typically over an angular range of between -20 ° and 20 °. The clearance of the fairing 3 is for example limited by mechanical stops placed on the periphery of the body 2. The device 1 further comprises means for guiding the fairing 3 to rotate relative to the body 2. These rotation guiding means are for example consisting of a circumferential groove formed on the body 2 and a rod 10 extending internally of the shroud 3, adapted to be engaged in the groove, and having at its end a protrusion adapted to not be removable from the throat. The section of the cylindrical body not covered by the fairing forms the leading edge 5 when the measuring device is positioned in the flow path 13. The rotation of the fairing 3 around the body 2 is limited by the friction at the interface between the face 31 of the fairing 3 and the cylindrical body 2.
    [0018] The interface between the face 31 of the fairing 3 and the body 2 has a coefficient of friction chosen so that the resisting torque between the body 2 and the shroud 31 is greater than or equal to the maximum aerodynamic force due to the unsteady fluctuations of pressure on the fairing 3, the maximum amplitude of these fluctuations being of the order of 3000 Pa. Thus the fairing is wedged in the direction of the flow without being sensitive to unsteady pressure fluctuations. For example, the longitudinal face 31 is concave and the curvature of the face 31 is chosen to be greater than that of the body 2 so that the interface between the face 31 of the fairing 3 and the body 2 has the desired coefficient of friction. .
    [0019] The coating of the face 31 and that of the body 2 can also be chosen so that the interface between the face 31 of the fairing 3 and the body 2 has the desired coefficient of friction. Operation The force exerted by the flow on the fairing 3 rotates the fairing 3 relative to the body 2 so as to align the fairing 3 with the axis of incidence of the flow. With reference to FIGS. 6 and 7, the fairing 3 thus extends in the axis F of incidence of the flow whatever the incidence of the flow. In particular, when the flow is oriented in the axis A in which the sensitive elements 41 extend (FIG. 6), the shroud 3 extends in the axis A. The aerodynamic detachment zone D downstream of the device measurement 1 is limited. When the angle of incidence F of the flow deviates from the axis A (FIG. 7), the fairing 3 moves away from the axis A so as to be positioned in the axis F of the incidence of the flow. The aerodynamic detachment zone D downstream of the measuring device 1 is thus also limited. Locking system 7 of the rotation of the shroud 3 around the cylindrical body 25 In a particular embodiment, the measuring device 1 further comprises a locking system 7 of the rotation of the shroud 3 around the body 2. The locking system 7 makes it possible to block the rotation of the fairing 3 around the body 2. The locking system 7 consists for example of an electromagnet.
    [0020] The measuring device 1 may further comprise a control system 8 of the locking system 7.
    [0021] The control system 8 is adapted to release the rotation of the fairing 3 around the body 2 during a change of motor operating point and to block the rotation of the fairing 3 around the body 2 during a measurement of aerodynamic quantities. An engine operating point change may for example be a change in engine speed or the opening or closing of the output section. To perform a series of aerodynamic measurements in a flow path 13 of a turbomachine 10 for different engine speeds, the measuring device 1 is positioned in the flow path of the turbomachine 10, and the following is carried out: control of a motor operating point; releasing the rotation of the fairing 3 around the body 2 until the position of the fairing 3 is stabilized; - Locking the rotation of the fairing 3 around the body 2; - measurement of aerodynamic quantities; the above steps are repeated for each engine operating point. 20
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device for measuring aerodynamic quantities (1) intended to be placed in a flow vein (13) of a turbomachine comprising: - an elongated body (2) having at least one longitudinal cylindrical face (21); a plurality of sensors (4) of aerodynamic magnitude placed in the body (2), the sensitive elements (41) of the sensors extending outside the body (2) at a leading edge (5); - a fairing (3) forming a trailing edge (6), partially surrounding the body, and having a longitudinal face (31) complementary to the longitudinal cylindrical face (21) of the body (2), the face of the body (2) no covered by the fairing and opposed to the fairing (3) forming the leading edge (5); the aerodynamic magnitude measuring device (1) being characterized in that the fairing (3) is mounted for rotation with constrained clearance around the body (2).
    [0002]
    2. Apparatus for measuring aerodynamic quantities (1), according to the preceding claim, wherein the body (2) is of circular section.
    [0003]
    3. A device for measuring aerodynamic quantities (1), according to one of the preceding claims, characterized in that the sensitive elements (41) of the sensors (4) extending on the leading edge of the body (2).
    [0004]
    4. Apparatus for measuring aerodynamic quantities (1) according to one of the preceding claims, wherein the shroud (3) surrounds the body (2) at an angle between 190 ° to 320 °.
    [0005]
    5. Apparatus for measuring aerodynamic quantities (1), according to one of the preceding claims, the longitudinal face (31) in contact with the 3025885 12 body (2) being concave, the curvature of the face (31) being chosen superior to that of the body (2).
    [0006]
    6. A device for measuring aerodynamic quantities (1), according to one of the preceding claims, further comprising a locking system (7) of the rotation of the shroud (3) around the body (2).
    [0007]
    7. Apparatus for measuring aerodynamic quantities (1), according to the preceding claim, further comprising a control system (8) of the locking system (7) of the rotation of the shroud (3) around the body (2), the control system (8) being adapted to release the rotation of the fairing (3) around the body (2) during a motor operating point change and to lock the rotation of the fairing (3) around the body (2) during a measurement of aerodynamic quantities. 15
    [0008]
    8. Apparatus for measuring aerodynamic quantities (1), according to one of the preceding claims, characterized in that the shroud (3) is rotatably mounted on the body (2) with constrained clearance on an angular range between - 20 and 20 °. 20
    [0009]
    9. A method for measuring aerodynamic quantities (1) using a device placed in a flow vein (13) of a turbomachine comprising: - an elongated body (2) having at least one cylindrical longitudinal face 25 (21); a plurality of sensors (4) of aerodynamic magnitude placed in the body (2), the sensitive elements (41) of the sensors extending outside the body (2) at a leading edge (5); a fairing (3) partially surrounding the body (2), having a complementary face (31) of the longitudinal cylindrical face (21) of the body (2) and forming a trailing edge (6), the face of the body (2) ) no 3025885 13 covered by the fairing and opposite to the fairing forming the leading edge (5); the method being characterized in that it comprises a step of measuring the aerodynamic quantities, the fairing (3) being mounted to travel 5 constrained to rotate around the body (2), so that the trailing edge (6) of the fairing (3) is always placed in the axis (F) of incidence of the flow.
    [0010]
    10. A method for measuring aerodynamic quantities according to the preceding claim, characterized in that it comprises steps of: 10 - change of motor operating point; - Release of the rotation of the shroud (3) around the body (2) until the shroud (3) stabilizes; - Locking the rotation of the fairing (3) around the body (2); - measurement of aerodynamic quantities. 15
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    同族专利:
    公开号 | 公开日
    FR3025885B1|2017-11-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2041104A|1979-02-01|1980-09-03|Gen Electric|Instrumentation probe|
    DE3524834A1|1984-07-13|1986-01-16|Institutul de Cercetare Stiintifica si Inginerie Tehnologica pentru Industria Electrotehnica, Bukarest/Bucuresti|Measuring device for pneumatically conveyed substances|
    DE19606794A1|1996-02-23|1997-08-28|Mtu Muenchen Gmbh|Device for positioning a measuring probe|
    EP1615002A1|2004-07-09|2006-01-11|General Electric Company|Vane assembly and method for measuring a physical property of an air flow|
    EP2492441A2|2011-02-25|2012-08-29|General Electric Company|System for measuring parameters of fluid flow in turbomachinery|
    US8397565B1|2011-04-15|2013-03-19|Florida Turbine Technologies, Inc.|High response air angle probe|WO2017187108A1|2016-04-28|2017-11-02|Safran Aircraft Engines|Device for measuring aerodynamic quantities intended for being placed in a flow section of a turbine engine|
    FR3053786A1|2016-07-05|2018-01-12|Safran Aircraft Engines|DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE|
    FR3065527A1|2017-04-21|2018-10-26|Safran Aircraft Engines|DEVICE FOR MEASURING PARAMETERS OF AERODYNAMIC FLOW OF A TURBOMACHINE, INSTRUMENTAL AUB AREA EQUIPPED WITH SUCH A MEASURING DEVICE AND METHOD FOR MANUFACTURING SUCH A DEVICE|
    US10126208B2|2015-10-22|2018-11-13|Rolls-Royce Plc|Sensor system having a sensor supported by a mast for use within fluid flows|
    WO2020095006A1|2018-11-09|2020-05-14|Safran|Stator blade|
    法律状态:
    2015-09-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-18| PLSC| Publication of the preliminary search report|Effective date: 20160318 |
    2016-09-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458651A|FR3025885B1|2014-09-15|2014-09-15|DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE|FR1458651A| FR3025885B1|2014-09-15|2014-09-15|DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE|
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