• 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 for constituting the end portion of an aircraft aerodynamic profile. The device comprises a profile (1) which comprises, in an assembly adapted to be attached in one piece to said profile to form a trailing edge (BF) a blowing chamber (2) and a nozzle (3) allowing the setting in fluid communication between the blowing chamber (2) and an outer surface of the profile (1). By blowing air through the nozzle or nozzles (3), the aerodynamic disturbances in the wake of the profile are reduced. The device thus allows a compact and easy to implement integration of a blowing device, in the immediate vicinity of the trailing edge (BF). The invention also relates to an assembly comprising such a device. In some embodiments, the profile is provided with a scoop for scooping all or part of the layer on its surface, which can also be disposed very behind the profile.
    公开号:FR3044295A1
    申请号:FR1561433
    申请日:2015-11-26
    公开日:2017-06-02
    发明作者:Jerome Colmagro
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    The invention relates to an aerodynamic profile provided with an air ejection device.
    According to one particular embodiment, the invention applies to a mast or pylon supporting an aircraft propulsion assembly comprising such an aerodynamic profile and to an aircraft comprising such a mast.
    During a trip, any aerodynamic vehicle profile is exposed to the wakes of other profiles of this vehicle, or disruptive phenomena of its boundary layer of air. Aircraft whose propulsion assembly is located on a mast are particularly concerned because the mast generates a wake, regardless of its design.
    This is due to the fact that the height of the boundary layer of the mast profile increases in the downstream direction of the profile.
    Thus, there occurs at the trailing edge of the mast a "speed defect" (or "speed deficit") materialized by a difference between the speed of the free flow of air and the local speed of the air in the downstream area of the profile.
    The zone presenting this speed defect is also the seat of a "mass flow rate defect" (or "mass flow deficit") of air. As a result, air tends to be dragged into the area due to lack of speed, causing turbulence.
    In the case of a mast supporting a propulsion unit, in particular with propellers or unpaved blades, the discontinuity of the speeds and the turbulences of the wake cause, among other things, an increase in the noise generated by the propellers of the turbine of the assembly. propulsion, which can affect the comfort of passengers and the environment, when said propellers pass in the wake of the mast. This is called "masking" effect.
    There is therefore a need to limit this effect of "masking" inducing a pressure variation in the wake of the mast.
    In the specific case of masts supporting propulsion units, there is a need to eliminate the deficit of air flow and thus reduce the speed deficit on their surface.
    One of the solutions to achieve this is to blow air from a high pressure source near the trailing edge of the profile to eliminate the deficit of air flow, and thus reduce the speed deficit.
    For this purpose, the document US 4917336 describes an air ejection device comprising an ejection nozzle sending air, wherein the air escapes through slots made at the extrados and the air outlet. lower surface of a mast supporting an aircraft propulsion unit. Nevertheless, this document presents complex, bulky embodiments, the implementation of which remains imperfect.
    According to the invention, a device comprising a profile is shaped to form an end portion of an aircraft aerodynamic profile and to form a trailing edge of said profile. The device comprises a blowing chamber adapted to be pressurized and an air ejection nozzle allowing the fluidic communication between the blowing chamber and an outer surface of the profile. According to the invention, the profile, the blowing chamber, and the nozzle form an assembly adapted to be attached in one piece to said aerodynamic profile to form a trailing edge (BF). The invention thus provides a compact device incorporating the essential functions of a blower system for aerodynamic profile in order to reduce disturbances in the wake, and this in the immediate vicinity of the trailing edge. By a design allowing an assembly in one piece, the device proposed in the invention is easy to implement, and in particular to mount on a member forming the front part of the airfoil.
    According to one embodiment, the profile, the blowing chamber, and the nozzle form a one-piece assembly.
    According to one embodiment, the outer surface comprises, at an outlet of the nozzle, a recess into which the ejection nozzle opens.
    The nozzle may advantageously be in the form of a slot extending along the profile.
    The device may comprise several nozzles. The device may comprise a first surface intended to form an extrados portion of the aerodynamic profile, and a second surface intended to form a lower section of the aerodynamic profile, comprising at least one nozzle opening at the first surface and a nozzle. opening at the second surface.
    Alternatively, the device may comprise a homogenization plate disposed in the blowing chamber and defining a feed chamber on the one hand, and a blower box on the other.
    In a variant, the blowing chamber may comprise a distributor tube adapted to supply it with air. In particular, the air distributor tube can be arranged in the feed chamber. The invention also relates to an assembly forming an aircraft aerodynamic profile having a leading edge and a trailing edge defining a chord of said profile, the assembly comprising a device as previously described.
    Advantageously, the ejection nozzle can lead to at least 70% of the chord of the profile, and preferably about 95% of the chord of the profile. The assembly according to the invention may further comprise a scoop shaped to scoop all or part of the boundary layer formed during an air flow along said aerodynamic profile. The device may comprise a plurality of scoops. In particular, scoops may be distributed between the upper and lower surfaces of the aerodynamic profile. The scoop can be positioned between 50% and 90% of the chord of the profile, and preferably about 80% of the chord of the profile. Such an earlier positioning of the scoop (or scoops) is made possible by the implementation in the assembly of a trailing edge device according to the invention. When the assembly comprises an ejection nozzle and a scoop, the scoop is advantageously further away from the trailing edge than the nozzle. The scoop may comprise a slot substantially parallel to the leading edge of the airfoil. The invention finally relates to a mast supporting an aircraft propulsion assembly comprising an assembly as previously described. In such a mast, the blowing chamber can be supplied with air by the propulsion unit. Other features and advantages of the invention will become apparent in the description below.
    In the accompanying drawings, given as non-limiting examples: FIG. 1 illustrates, in a three-dimensional diagrammatic view, an aircraft fuselage 1 comprising a propulsion system; - Figure 2 shows a schematic three-dimensional view of an aircraft propulsion assembly mast in its immediate environment; - Figure 3 shows schematically in section in side view a device according to one embodiment of the invention; - Figure 4 shows schematically in a three-dimensional view of a device according to the embodiment of Figure 3; - Figure 5 shows schematically in a three-dimensional view an assembly comprising the device of Figure 4; FIG. 6 schematically represents a part of an assembly according to a particular embodiment of the invention; - Figure 7 schematically shows an aerodynamic profile according to a particular embodiment of the invention; - Figure 8 schematically shows a mast carrying an aircraft propulsion unit and comprising a device according to one embodiment of the invention.
    FIG. 1 illustrates an aircraft fuselage F equipped with two propulsion units, which comprise an engine (in this case a turbine) contained in an n-boat and one or more thrust propellers each comprising blades. A propulsion unit GP and its nacelle N form an aircraft propulsion unit.
    This nacelle N is supported and connected to the fuselage F by a mast P. A mast P constitutes a structural and functional connection piece between a propulsion unit GP of an aircraft and the structure (for example the fuselage F) of the aircraft. In particular, a mast comprises an aerodynamic fairing including a structure supporting the propulsion assembly and the devices that can be connected thereto. These are not represented.
    As explained above, during the flight, the mast P causes eddies in its wake and turbulence shown in Figure 2.
    Figure 2 shows in more detail a propulsion mast P of an aircraft in its immediate environment. In order to limit the aerodynamic drag, the mast has a suitable aerodynamic profile imparted by its fairing. Such an aerodynamic profile comprises a leading edge BA and a trailing edge BF. The mast is commonly made of several parts, the trailing edge may be constituted by a profile 1 reported to the rest of the mast. By profile means a fixed or variable section piece, which is an extreme portion of the aerodynamic profile. . In the embodiment shown here, the profile has a substantially triangular variable section along said profile.
    The passage in the wake of the mast P of the blades of a propeller, for example a turboprop as a propellant, can generate a significant noise, the blades undergoing aerodynamic disturbances and the effect of "masking" it generates.
    Although the aircraft propulsion assembly masts constitute a preferential application of the invention, a similar phenomenon can occur in many other elements of an aircraft, and the solution proposed in the invention can generally be applied to them. .
    FIG. 3 shows in particular, in a sectional view, a device according to one embodiment of the invention. The device essentially comprises a section 1 intended to constitute an end portion of an aircraft aerodynamic profile. In particular, the section 1 is shaped to form the trailing edge BF of an aerodynamic profile, in this case the trailing edge of a mast fairing for an aircraft propulsion unit.
    The section 1 is at least partially hollow. According to the invention, it comprises a blowing chamber 2 (also called "blowing box" in English terminology) and a nozzle 3 for air ejection. The section 1, the blowing chamber 2 and the nozzle 3 form an assembly adapted to be reported integrally to said airfoil to form a trailing edge (BF). The blowing chamber 2 and the nozzle 3 may in particular be formed directly in the profile 1, so that the profile 1, the blowing chamber 2, and the air ejection nozzle are formed in one piece. In other words, they are in this case monoblock. A one-piece constitution of the main elements of a device according to the invention reduces the number of operations required to obtain it and its complexity
    In the exemplary embodiment shown here, the device further comprises a homogenizer plate 4 which separates the blowing chamber into a feed chamber 21 on the one hand, and a blower box 22 on the other hand .
    The homogenization plate makes it possible to homogenize the air by stirring. The homogenizing plate may for example comprise a plate having a multitude of holes through which the air passes to reach the blowing box 22. In the exemplary embodiment shown, the homogenizing plate has a structural role in the constituting the device object of the invention. In particular, the device may comprise two plates joined to form the desired angle of the profile at the trailing edge, said plates being joined by the homogenization plate. According to a variant, said plates can form with the homogenization plate an isosceles triangle, variable or not along the profile.
    The device may comprise, in the length of the profile, a curved plate 8, typically C or in a closed curve, forming a wall of the blower box 22, and allowing with at least one other wall of the blower box to provide slots forming nozzle in the extension of the curvature of the curved plate 8. Alternatively, the device may comprise a solid end forming trailing edge, or provided with openings and / or cavities. The curved plate 8, linked to the plates forming the angle of the trailing edge, can also make it possible to stiffen the structure mechanically, in particular at its end. The structure thus obtained is hollow, therefore light, while having a high rigidity. The curved plate 8 is preferably positioned in the immediate vicinity of the homogenizing plate 4, in order to direct the air at the outlet of the homogenization plate towards the nozzle or nozzles 3.
    The nozzle allows an air passage between the blowing chamber 2, and more particularly the blower box 22, and an outer surface of the profile 1. In particular, the nozzle has an outlet oriented so that the air expelled by the nozzle is expelled substantially in the same direction as the flow of air flowing along the airfoil when the aircraft is in flight.
    In the embodiment shown here, two nozzles are present on both sides of the device. In particular, a nozzle opens on a first surface 11 intended to form the extreme portion of the extrados EX of an aerodynamic profile, and another nozzle opens on a second surface 12 intended to form the end portion of the intrados IN of the profile.
    As is well shown in FIG. 4, the external surface of the device comprises, at an outlet of the nozzle 3, a recess 13 into which the nozzle 3 opens. In the example represented here, the nozzle 3 is in the form of a slot extending along the section 1. The slot forming the outlet of the nozzle may have a width of the order of 1 millimeter. In particular, the slot-shaped nozzle extends to the bottom of the recess 13. In the variant shown here, ribs 14 serve to stiffen the profile 1 and to avoid a mechanical weakening which would be caused by the presence of the nozzle 3 .
    The profile can be machined in two stages. In a first step, a raw section is obtained by molding. In a second step, the nozzle or nozzles are machined, typically by mechanical machining (for example by drilling and / or milling) or by electroerosion.
    FIG. 5 diagrammatically represents an assembly comprising the device of FIG. 3 after assembly on an anterior element of an aircraft propulsion unit mast or on another part defining an aerodynamic profile. In the example shown here, the front element comprises an intermediate part 52 and the device of Figure 3 is assembled on the intermediate part 52. The assembly can be achieved by various modes of attachment. As clearly visible in Figure 5, the profile does not have a constant section. In addition, in the example shown, the trailing edge BF formed by the section 1 is not rectilinear. On either side of the section 1 can be reported, especially in the case of the constitution of a mast supporting an assembly or aircraft propulsion unit, fuselage F connection fairings of the aircraft of a on the other hand, and the nacelle N of the powertrain GP on the other hand. In the context of larger aircraft elements, several sections incorporating one or more blowing nozzles 3 may be implemented, end to end or separated by fairing portions forming the continuation of the trailing edge and devoid of blowing system.
    FIG. 6 schematically represents a part of an assembly according to a particular embodiment of the invention, comprising a section 1 assembled on a part such as an element former of an aircraft propulsion group mast at the level of FIG. An assembly part 51. In the example shown here, the assembly part 51 forms a wall of the blowing chamber 2, which is thus closed. In the embodiment shown in Figure 6, the blowing chamber is supplied with air under pressure by an optional dispensing tube 6. The dispensing tube 6 is a tube passing through the profile 1 in the blowing chamber 2, and more particularly, where appropriate, in the feed chamber 21. The dispensing tube is pierced with a multitude of orifices providing a distribution, for example homogeneous, air in the blowing chamber. The dispensing tube may be supplied with pressurized air (that is to say at a pressure greater than atmospheric pressure, or in any case greater than the pressure at the outlet of the nozzle 3) by a propulsion unit. 'aircraft. It may be in particular the propulsion unit supported by the mast equipped with the device according to the invention.
    According to other variants of the invention, the blast chamber 2 or the supply chamber 21 of the blast chamber 2 can be directly supplied with pressurized air, for example by an aircraft propulsion unit, without the use of a blower. a distribution tube.
    Whatever the embodiment of the invention, other air supply means under pressure are possible, such as an electric or mechanical compressor.
    Figure 7 schematically shows an aerodynamic profile according to a particular variant of the invention. As previously explained, the turbulence in the wake of an aerodynamic profile is related to the increase in the thickness (height) of the boundary layer in the downstream direction of the profile. Turbulence problems can be solved totally or partially by the previously detailed blow molding. Alternatively or in addition to this blowing, it is also possible to reduce the thickness of the boundary layer by scooping all or part of this boundary layer. By reducing the thickness of the boundary layer, it acts directly on the origin of the aerodynamic disturbances. To this end, the aerodynamic profile may be provided with one or more scoops 7. Typically, a scoop may be present at the extrados EX of the aerodynamic profile, and a scoop may be present at the intrados IN of the aerodynamic profile. The use of a device according to the invention allows to position the blowing nozzle or nozzles in the immediate vicinity of the trailing edge BF of the airfoil. Typically, the outlet (s) of the nozzles may be disposed at more than 90% of the aerodynamic profile cord, and preferably at approximately 95% of said chord of the profile. Remarkably, the blowing chamber being integrated in the profile forming the trailing edge, the entire system for blowing is compact and integrated into the rear end of the airfoil. This frees the volume prior to said blowing system for the combined adoption of scoops may themselves be located very behind the profile, typically beyond 60% of its rope, and preferably around 80% of its rope. Thus disposed, the scoops are highly efficient because they are located in an area in which the boundary layer is highly thickened, and sufficiently close to the leading edge to avoid significant resurfacing of the boundary layer downstream of said scoops.
    The scoops may be in the form of slots, typically flush with the aerodynamic profile. They may have a width that may for example be between 1 and 30 mm. The ecoped air can be conducted in the blowing chamber of the profile used in the invention. Thus, the air from the scoops, pressurized, can be used to feed at least partly a blowing system implementing a device according to the invention to form the trailing edge of an aircraft aerodynamic profile. The supply of the pressurized air blowing chamber may be supplemented by air coming from an aircraft power unit, or by a dedicated mechanical or electrical compressor.
    FIG. 8 schematically shows a mast P carrying a propulsion group GP of an aircraft and comprising a device according to one embodiment of the invention. The mast P connects, structurally and functionally, the fuselage F of an aircraft to the nacelle N GP powertrain. The mast P forms an aerodynamic profile, and comprises a profile 1 forming its trailing edge, and an anterior member 5 to which the trailing edge is bound. The front element 5 may comprise an intermediate piece 52 and an anterior section 53 forming its leading edge.
    The device developed in the invention therefore offers many advantages vis-à-vis the blowing systems existing in the invention. In particular, it allows integration into a very small volume of all the means necessary for blowing, and this in the immediate vicinity of the trailing edge, that is to say where blowing is most effective against the aerodynamic disturbances generated in the wake of an aerodynamic profile. In addition, the device proposed in the invention limits integration constraints and avoids the complex assembly of known devices, especially when it is constituted essentially integrally. Finally, thanks to a disposition very behind the aerodynamic profile, the device can be combined with one or more scoops making it possible to scoop all or part of the boundary layer, on the underside and / or on the extrados of the profile, the scoops can themselves be arranged very behind the profile in an area where their efficiency is very good.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1. Device comprising a profile (1) shaped to form an end portion of an aircraft aerodynamic profile, characterized in that it comprises a blowing chamber (2) adapted to be pressurized and a nozzle (3) air ejection device for fluidic communication between the blowing chamber (2) and an outer surface of the profile (1); the profile (1), the blowing chamber (2), and the nozzle (3) forming an assembly adapted to be attached integrally to said aerodynamic profile to form a trailing edge (BF).
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the section (1), the blowing chamber (2), and the nozzle (3) constitute a one-piece assembly.
    [3" id="c-fr-0003]
    3. Device according to claim 1 or claim 2, wherein the outer surface comprises, at an outlet of the nozzle (3), a recess (13) in which opens the nozzle (3) ejection.
    [4" id="c-fr-0004]
    4. Device according to one of claims 1 to 3, wherein the nozzle (3) is in the form of a slot extending along the profile (1).
    [5" id="c-fr-0005]
    5. Device according to one of claims 1 to 4, characterized in that it comprises a first surface (11) for forming an extrados portion (EX) of the airfoil, and a second surface (12) for forming a portion of intrados (IN) of the aerodynamic profile, having a nozzle (3) opening at the first surface and a nozzle (3) opening at the second surface.
    [6" id="c-fr-0006]
    6. Device according to one of claims 1 to 5, further comprising a homogenizer plate disposed in the blowing chamber (2) and defining a feed chamber (21) on the one hand, and a blower box (22) secondly.
    [7" id="c-fr-0007]
    7. Device according to one of claims 1 to 6, wherein the blowing chamber (2) comprises a distributor tube (6) adapted to supply air.
    [8" id="c-fr-0008]
    8. Device according to claims 6 and 7, wherein the air distributor tube is disposed in the feed chamber (21).
    [9" id="c-fr-0009]
    9. An assembly forming an aircraft aerodynamic profile having a leading edge and a trailing edge (BF) defining a rope of said profile, the assembly comprising a device according to one of claims 1 to 7.
    [10" id="c-fr-0010]
    10. The assembly of claim 9, wherein the ejection nozzle (3) opens at least 70% of the string of the profile, and preferably about 95% of the chord of the profile.
    [11" id="c-fr-0011]
    11. The assembly of claim 9 or claim 10, further comprising a scoop (7) shaped to scoop all or part of the boundary layer formed during an air flow along said airfoil.
    [12" id="c-fr-0012]
    12. The assembly of claim 11, wherein the scoop is positioned between 50% and 90% of the chord of the profile, and preferably about 80% of the chord of the profile.
    [13" id="c-fr-0013]
    13. The assembly of claim 11 or claim 12, wherein the scoop (7) has a slot substantially parallel to the leading edge of the airfoil.
    [14" id="c-fr-0014]
    14. Mast supporting an aircraft propulsion unit comprising an assembly according to one of claims 9 to 13.
    [15" id="c-fr-0015]
    15. Mast according to claim 14, wherein the blowing chamber (2) is supplied with air by the propulsion assembly.
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    同族专利:
    公开号 | 公开日
    CN107054612A|2017-08-18|
    GB2546594A|2017-07-26|
    GB201619868D0|2017-01-11|
    FR3044295B1|2018-12-07|
    US20170152024A1|2017-06-01|
    引用文献:
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    GB2473651A|2009-09-21|2011-03-23|Rolls Royce Plc|Oil cooling arrangement for gas turbine aircraft engines and operation thereof|
    US20120273609A1|2011-04-28|2012-11-01|Airbus Operations |Streamlined profile reducing the speed deficit in its wake|
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    CN104029816B|2014-06-20|2016-04-27|西北工业大学|The screw propeller that a kind of trailing edge is jet|FR3050781A1|2016-04-27|2017-11-03|Airbus Operations Sas|DEVICE FOR REDUCING AERODYNAMIC DISTURBANCES IN THE WAKE OF AN AERODYNAMIC BLOW PROFILE WITH VARIABLE DISTRIBUTION TO EXTRADOS AND INTRADOS|
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    US20190061905A1|2017-08-30|2019-02-28|David Victor Bosse, JR.|Airfoil|
    CN112093029A|2019-06-18|2020-12-18|成都飞机工业（集团）有限责任公司|Aircraft airfoil trailing edge|
    FR3107308A1|2020-02-13|2021-08-20|Safran|Blowing system for aircraft propulsion system|
    法律状态:
    2016-11-18| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-02| PLSC| Publication of the preliminary search report|Effective date: 20170602 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 3 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1561433A|FR3044295B1|2015-11-26|2015-11-26|DEVICE FORMING A LEFT EDGE OF AERODYNAMIC PROFILE AND COMPRISING A BLOWING SYSTEM|
    FR1561433|2015-11-26|FR1561433A| FR3044295B1|2015-11-26|2015-11-26|DEVICE FORMING A LEFT EDGE OF AERODYNAMIC PROFILE AND COMPRISING A BLOWING SYSTEM|
    US15/359,146| US20170152024A1|2015-11-26|2016-11-22|Device forming a trailing edge of an aerodynamic profile and comprising a blowing system|
    GB1619868.1A| GB2546594A|2015-11-26|2016-11-24|Device forming a trailing edge of an aerodynamic profile and comprising a blowing system|
    CN201611052504.3A| CN107054612A|2015-11-26|2016-11-25|Form the trailing edge of aerodynamics airfoil and the device including blower system|
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