• 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 propulsion system for an aircraft comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a flow (F), characterized in that said member is covered, at least partially of a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a succession of grooves, in contact with the flow of the flow, the grooves extending in the flow direction of the flow, the grooved structure comprising at least one geometrical parameter (h, s, w) configured to adapt as a function of at least one parameter of the flow flow and or an operating point of the propulsion system and / or an engine speed of the propulsion system.
    公开号:FR3050435A1
    申请号:FR1653679
    申请日:2016-04-26
    公开日:2017-10-27
    发明作者:Emilie Goncalves；Nicolas Pierre Lanfant；Robin Mandel
    申请人:Safran SA；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL FIELD The invention relates to a propulsion system comprising a member in contact with a turbulent flow of a flow and at least partially covered with a grooved structure in the fluid flow direction (riblets).
    STATE OF THE ART
    A propulsion system conventionally comprises a nacelle and / or a turbomachine, such as a turbojet engine.
    In connection with FIG. 1, a propulsion system (turbofan) of an aircraft generally comprises, from upstream to downstream in the direction of the gas flow (along the engine axis AA), a streamlined fan 1, a primary flow annulus I and secondary flow annulus II (secondary vein). The primary flow I passes through the low and high pressure compressors 10, the combustion chamber 11 and the high and low pressure turbines 12. The secondary flow II bypasses the hot part; the separation is carried out by the inner hub 3 located behind the streamlined fan 1. Inside the secondary vein are arranged vanes with fixed geometries 4 (in English, "Outiet Guide Vanes", (OGVs)) which make it possible to straighten the flow of the gases circulating therein to align with the motor axis AA, the blower 1 producing a gyratory flow.
    In order to improve the efficiency of the blades, the walls of the inner hub and the outer casing as well as the walls of the blades can be grooved in the fluid flow direction.
    These grooves can have several forms. The shape, the alignment with the flow, the size and in particular the spacing of these grooves have a direct influence on the flow and on the expected efficiency gain of the turbojet engine. One problem is that the grooves will be strongly subjected to erosion but also to fouling.
    In addition, during the flight operation of a turbojet engine, a layer of ice or frost may form on the wings, the air inlets of the engines or the air flow measurement sensors.
    The presence of ice affects the safety and performance of aircraft.
    Icing in flight occurs most often during the landing phase, under certain climatic conditions between 3000 m and 6000 m. The aircraft can then be subjected to the impact of, according to the English terminology, "ice crystals" and / or supercooled water drops (liquid water whose temperature is below 0 ° C) . These droplets of size between 0 and 500 pm strike the cold surface of the aircraft causing the dangerous accumulation of ice.
    The consequences of icing on an engine can be numerous: obstructions of the air inlets which lead to a loss of power, ingestion of ice, icing at the blades and the rotor which causes an alteration of the autorotation capacity even a stop or overconsumption of fuel.
    In addition, the presence of ice causes a change in the aerodynamic profile and therefore a dangerous reduction in lift.
    In order to limit the presence of ice solutions are known consisting of covering parts of the propulsion system that can be subjected to frost of a glaciophobic coating (see the document EP 2 431 276) which can be subjected to vibrations to facilitate detachment of ice (see document FR 2 998 921).
    These solutions do not necessarily make it possible to limit the formation of ice and the setting in vibration is complex to implement and are not compatible with the grooves used to improve the aerodynamic performances. It is necessary to provide two distinct solutions.
    PRESENTATION OF THE INVENTION
    An object of the invention is to improve the aerodynamic performance of an aircraft by the use of grooves while allowing to limit the formation of frost on the bodies of a propulsion system. For this purpose, the invention proposes a propulsion system for an aircraft comprising at least one member in contact with a turbulent flow of a flow, characterized in that said member is covered, at least partially, with a piezoelectric structure such as a piezoelectric film, said structure comprising a grooved structure comprising a succession of grooves in contact with the flow of the flow, the grooves extending in the flow direction of the flow, the grooved structure comprising at least one geometrical parameter configured to adapt to at least one parameter of the flow flow and / or operating point of the propulsion system and / or engine speed of the propulsion system. The invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination: the grooved structure is constituted by a piezoelectric film; the piezoelectric film is of the electroactive polymer type chosen from the following group: PVDF, PVF 2, PVF 2 -TFE, PMMA or a PZT ceramic; the structure further comprises a polarization unit of the film by means of an alternating voltage source and conductive or semiconductive electrodes placed in contact with the film; the height of the grooves is between 10 μΐη and 100 μηι; - a running point of the propulsion system is: parking, shop-visit, cruise, icing episode. The invention also relates to an aircraft comprising a propulsion system according to the invention. More specifically, the invention relates to an aircraft comprising an element exposed to the flow of air.
    PRESENTATION OF THE FIGURES Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings, in which: FIG. overall of a propulsion system of an aircraft; FIG. 2 illustrates a detailed view of FIG. 1; FIG. 3 illustrates a piezoelectric structure according to the invention; FIGS. 4a to 4d illustrate examples of grooves.
    In the set of figures, similar elements bear identical references. DETAILED DESCRIPTION OF THE INVENTION
    FIG. 2 illustrates a detailed view of FIG. 1 comprising a circulation assembly of a flow of a flow in which one or more members may be at least partially covered with a structure of a structure S comprising a grooved structure 5, 6, 7 comprising a succession of grooves in contact with the flow of the flow, the grooves extending longitudinally in the flow direction of the flow.
    The grooved structure 5, 6, 7 is preferably arranged on the faired fan 1 (reference 5) and / or on the outer wall of the inner hub (reference 6) and / or on the variable geometry blade (reference 7).
    FIG. 3 illustrates a structure S comprising a grooved structure traversed by a flow of a flow (arrow in FIG. 3).
    The grooves can take several forms: crenel (Figure 4a), parabolic (Figure 4b), triangular (Figure 4c), trapezoidal (Figure 4d).
    In the case of parabolic-shaped grooves, it is the concave part that is in contact with the flow.
    In the case of trapezoidal grooves, the small base is in contact with the wall of the channel while the large base of the trapezium is removed.
    The grooved structure may advantageously consist of grooves of different shapes.
    The grooved structure is in particular configured to adapt as a function of at least one flow flow parameter and / or an operating point of the propulsion system and / or an engine speed of the propulsion system.
    The structure can thus retract to allow a detachment of ice (anti-icing system). In addition, it makes it possible to limit fouling of the grooves in order to increase the duration of the initial gain (examples: ease of cleaning on the ground and cleaning in flight under the effect of the flow in contact with the structure).
    A geometric parameter is, according to the shape of the groove: the height h, the spacing s between two vertices, the width w intermediate in the case of crenellations (see Figure 4a).
    A flow parameter is the flow pressure, the flow temperature, the flow speed, the flow orientation.
    The grooved structure is preferably constituted by a PZT ceramic film or an electroactive polymer which makes it possible to modulate the depth of the grooves according to an operating point and / or the engine speed. An electroactive polymer is a polymer whose shape and size change when it is stimulated by an electric field. Depending on the electrical pulse sent, the deformation will be larger or smaller. Thus, the roughness will be more or less important depending on the pulse sent.
    To adjust the grooves, the structure S comprises a polarization unit P with an alternating voltage source and conductive or semiconductive electrodes placed in contact with the film. The polarization unit P is optionally coupled to an acquisition unit A configured to acquire flow parameters of the stream. The amplitude of the vibration sent for the voltage source will deform the film longitudinally and / or transversely. Depending on the power sent, the deformation will be more or less important thus giving the depth of the grooves or the desired roughness.
    Thus, depending on the aerodynamic flow to which the wet surface is subjected, it is possible to adjust the shape and depth of the grooves of the structure to obtain the minimum drag and thus the best performance of the propulsion system. The grooves are very sensitive to erosion (sand, rain ...). Erosion damages their structure (for example, the tip of the peak for a triangular shape) resulting in a loss of efficiency (thickness of the laminar flow layer ie the ability to move the layer away). turbulent flow, regularity of vortices between two neighboring grooves, etc.) and therefore a loss of aerodynamic performance. The effectiveness of the grooves is therefore dependent on its shape and thus, it is necessary to use materials that are tolerant to the different aggressions. The use of a piezoelectric film makes it possible to reduce the effect of erosion since one can adjust the shaping of the grooves to certain motor cycles on which the gain is particularly important and no longer systematically over the entire flight time. .
    In addition, the grooves are also very sensitive to fouling. Indeed, they may have V-shaped recesses with acute angles that can quickly be filled with dust, ice or grease. This is especially true in the engine environment. The use of a piezoelectric film then allows to enter the grooves of a flight phase "parking" and "shop-visit" to facilitate the cleaning of surfaces by water jet for example. The grooves could also be retracted during a "cruise" phase of flight in order to let the power of the air flow take away all or some of the clusters.
    The grooves may be between 1 μm and 50 μm in depth h depending on the geometry of the treated surface and the desired aerodynamic performance. For triangular shapes, the angle varies between 15 and 60 ° and for all shapes (crenellations, triangular, U-shaped groove), the peak-to-peak height varies from 20 to 100 μm with a peak height between 10 and 100 pm.
    Advantageously, to prevent the formation of ice or allow its detachment the grooves may be dimensioned so that the structure S has a roughness of between 1 and 2.2 pm. In this case, the grooves will be suitably dimensioned during an icing episode.
    Indeed, during the flight phase of the frost may be deposited in various places: on the air inlets (Gl, G2), and / or on the streamlined fan 1 (G3) and / or on the vanes with fixed geometries 4 ( G4) (see Figures 1 and 2).
    The electroactive film must therefore have erosion resistance properties but also hydrophobic properties to improve the anti-adhesion of the ice on contact.
    Also, it is preferably a PVDF-type hydrophobic polymer or PVF2, PVF2-TFE, PM MA, all with hydrophobicity properties or on a ceramic PZT (titanium lead zirconate) of chemical formula Pb (Zrx , Tii-x) C> 3 which is in thin film or polymerized gel. Several compositions are possible by varying the Zr / Ti ratio.
    The grooved structure is advantageously obtained by grooving a wall of the member subjected to a turbulent flow. The grooves may be obtained by surface texturing on metal or polymer or ceramic with a laser or by deposition of metal layers or by using a mask to print the pattern on the polymer or ceramic.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    A propulsion system for an aircraft comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a flow (F), characterized in that said member is covered, at least partially with a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a succession of grooves, in contact with the flow of the flow, the grooves extending in the flow direction of the flow, the grooved structure comprising at least one geometrical parameter (h, s, w) configured to adapt as a function of at least one parameter of the flow flow and / or an operating point of the propulsion system and / or an engine speed of the propulsion system.
    [2" id="c-fr-0002]
    2. propulsion system according to claim 1, wherein the grooved structure is constituted by a piezoelectric film.
    [3" id="c-fr-0003]
    The propulsion system of claim 2, wherein the piezoelectric film is of the electroactive polymer type selected from the following group: PVDF, PVF2, PVF2-TFE, PMMA or a PZT ceramic.
    [4" id="c-fr-0004]
    4. Propulsion system according to one of claims 2 to 3, wherein the structure further comprises a unit (P) of polarization of the film by means of an AC voltage source and conductive or semiconductor electrodes placed in contact with the film.
    [5" id="c-fr-0005]
    5. Propulsion system according to one of claims 1 to 4, wherein the height (h) of the grooves is between 10 μίτι and 100 μίτι.
    [6" id="c-fr-0006]
    6. propulsion system according to one of claims 1 to 5, wherein a running point of the propulsion system is: parking, shop-visit, cruise, icing episode.
    [7" id="c-fr-0007]
    7. Aircraft comprising a propulsion system according to one of claims 1 to 6.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20190152585A1|2019-05-23|
    FR3050435B1|2018-04-20|
    US11148787B2|2021-10-19|
    WO2017187073A1|2017-11-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4732351A|1985-03-21|1988-03-22|Larry Bird|Anti-icing and deicing device|
    FR2667256A1|1990-10-02|1992-04-03|Thomson Csf|Device for removing the icing formed on the surface of a wall, especially of an optical or radio frequency window|
    GB2472053A|2009-07-23|2011-01-26|Rolls Royce Plc|Aircraft and engine deicing apparatus|
    WO2014209665A1|2013-06-28|2014-12-31|General Electric Company|Flow surface|
    US20130299637A1|2012-05-08|2013-11-14|The Boeing Company|Ice protection for aircraft using electroactive polymer surfaces|
    EP2816200B1|2013-06-18|2017-02-01|General Electric Technology GmbH|Method and device for suppressing the formation of ice on structures at the air intake of a turbomachine|
    GB201716178D0|2017-10-04|2017-11-15|Rolls Royce Plc|Blade or vane for a gas turbine engine|US20190309652A1|2018-04-09|2019-10-10|Gulfstream Aerospace Corporation|Ice shedding aircraft engine|
    US20220001432A1|2018-08-08|2022-01-06|Northwestern University|Serrated surfaces for anti-icing applications|
    DE102018130298A1|2018-11-29|2020-06-04|Rolls-Royce Deutschland Ltd & Co Kg|Assembly with an output stator for a turbofan engine and turbofan engine with such an assembly|
    CN112282856B|2020-10-26|2021-09-24|上海交通大学|Turbine blade for suppressing channel vortex|
    法律状态:
    2017-04-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-27| PLSC| Publication of the preliminary search report|Effective date: 20171027 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1653679A|FR3050435B1|2016-04-26|2016-04-26|SYSTEM FOR PROPULSION OF AN AIRCRAFT COMPRISING AN ORGAN COVERED WITH A GROOVE STRUCTURE|
    FR1653679|2016-04-26|FR1653679A| FR3050435B1|2016-04-26|2016-04-26|SYSTEM FOR PROPULSION OF AN AIRCRAFT COMPRISING AN ORGAN COVERED WITH A GROOVE STRUCTURE|
    US16/096,496| US11148787B2|2016-04-26|2017-04-24|Aircraft propulsion system comprising a member covered with a grooved structure|
    PCT/FR2017/050967| WO2017187073A1|2016-04-26|2017-04-24|Aircraft propulsion system comprising a member covered with a grooved structure|
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