• 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 rotor cupola (20) comprising a cap (25) extending radially from an axis of rotation in elevation (100) to a periphery (27) and in azimuth over 360 degrees, said cap (25) extending in thickness from a lower face (31) to an upper face (32) in line with said upper face (32). The dome (20) has at least one slot (40) extending between said periphery (27) and said elevational axis of rotation (100), each slot (40) passing right through a thickness of the cap (25). ) extending in elevation from the lower face (31) to the upper face (32).
    公开号:FR3028497A1
    申请号:FR1402562
    申请日:2014-11-14
    公开日:2016-05-20
    发明作者:David Alfano；Damien Desvigne；Raphael Fukari
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a cupola of a lift rotor of a rotorcraft and to a rotorcraft equipped with such a cupola.
    [0002] A rotorcraft conventionally comprises a cell extending from a nose to a tail. This tail may comprise a tail boom carrying a fin and tail. The cell may carry at least one rotor ensuring at least partially lift or propulsion of the rotorcraft. Such a rotor is called "lift rotor" later, and sometimes "main rotor" by the skilled person. In addition, the tail comprises a drift sometimes carrying a rotor for controlling the yaw movement of the rotorcraft. Therefore, this rotor is sometimes called "rear rotor" given its position within the rotorcraft. The cell further comprises hoods arranged under the main rotor. These covers may be movable hoods allowing access to a power plant for example. Such covers are classically called "bonnet".
    [0003] During a flight of translation of the rotorcraft, the air flows along this rotorcraft. The aerodynamic flow of air downstream of the lift rotor and hoods of the cell is generally disturbed. These disturbances can then impact a drift and / or empennage of the tail of the rotorcraft.
    [0004] This disturbed aerodynamic flow is usually referred to as "wake". This term will be retained later for convenience, although this term is misleading. Indeed, a wake corresponds in principle to an area downstream of an obstacle disposed in a fluid in motion, in which the fluid is at rest relative to the obstacle. The impact of the disturbances generated by a lift rotor on the tail of a rotorcraft eventually leads to aerodynamic excitation of one or more tail vibration modes, this excitation being commonly referred to as "tail-shake" in aeronautical technology. This excitation has many disadvantages, in particular: for the comfort of the crew and the passengers, for the fatigue of parts and equipment, and for the operation of certain systems of the rotorcraft. In addition, the air flow can locally take off from the cell downstream of a lift rotor, in particular downstream of engine hoods. This detachment tends to amplify the intensity of the excitations on the tail of the apparatus, increasing the amplitude and enriching the frequency signature of these aerodynamic fluctuations. To reduce these excitations, a dome can be arranged on the head of the lift rotor.
    [0005] A dome is generally in the form of a substantially ellipsoidal shell of revolution. In addition, cavities are formed in a peripheral ring of the cupola in particular not to hinder the movement in flapping and drag blades.
    [0006] Therefore, a dome may comprise an ellipsoidal crown of revolution provided with a cell by blade of the rotor.
    [0007] During a flight in translation, this cupola deflects the air flow downstream of the lift rotor downward. This flow of air is then mainly deflected towards the hoods and the tail boom, and no longer towards the empennage and the drift of the rotorcraft. The effect "tail shake" is then decreased. As a result, a dome tends to deflect downward aerodynamic flow of air downstream of a lift rotor. In addition, the cupola tends to limit the detachment of an aerodynamic flow of air downstream of engine hoods. However, these cupolas are not always optimized. Indeed, a dome is generally sized to fold down an aerodynamic flow of air, and minimize said detachment of this aerodynamic flow of air 15 downstream of the lift rotor equipped with this dome. This dimensioning tends to determine the diameter of the dome. Consequently, the dome leaves no means of action on the frequency signature of the aerodynamic flows of air generated, nor on the forces undergone by the dome. A manufacturer therefore can not act on a dome of given shape to solve problems of interactions between the aerodynamic flow of air and the dome. The present invention therefore aims to provide an alternative dome.
    [0008] According to the invention, a dome is intended for a rotor of a rotorcraft, this dome comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness 3028497 4 of a lower face intended to be opposite a hub of the rotor to an upper face in line with this upper face. This cupola comprises at least one slot extending between the periphery and the axis of rotation in elevation of the cupola, each slot passing right through a thickness of the cap extending in elevation from the underside to the upper face, the dome comprising in azimuth along at least one inner circle a succession of solid surfaces represented by the upper face and openings represented by each slot with respect to an incident air flow so that said flow incident air impacts successively a solid surface and an opening during a rotation of said dome around the axis of rotation in elevation. The periphery of the dome may delimit cells that are dimensioned to allow in particular the flapping of a blade without interference with the dome. Each slot of the dome is not a cell and does not allow the beat of a blade. Each slot is thus formed within a dome between its periphery and the axis 20 of rotation in elevation of the dome. For example, the invention applies to an existing dome. An operator then open the dome to spare the required slots. The slots of a dome according to the invention are therefore to be distinguished from any cells.
    [0009] This cupola makes it possible to modify the air flow by generating geometrical variations of the cap. Indeed, each slot introduces geometric variations of the discontinuous cupola radially and azimutally in a decoupled manner.
    [0010] The presence of slits makes it possible to generate a pulsed flow. Indeed, this flow impacts successively the upper face and an opening formed by a slot due to the rotation made by the dome. Thus, the incident air flow 5 impacting the cap will successively enter or exit a slot. The irregular shape of the dome in azimuth according to at least one radius has the effect of disturbing the flow of incident air at the frequency of successive passage of the irregularity introduced by the slot.
    [0011] For convenience, the upper and lower faces are termed "irregular" because of the presence of slits. Conversely, the upper face and the lower face of a conventional dome-shaped spherical cap are called "regular".
    [0012] The cupola according to the invention then generates vortex flow structures, generally smaller in size than the structures naturally emitted by a dome provided with regular faces. This wake interacts with the "natural" wake of the dome, and can potentially alter its frequency content because of the highly non-linear nature of this type of interaction. As a result, the wake generated by the dome of the invention is pulsed. This spectral redistribution of the overall wake of the cupola potentially leads to a reduction in the intensity of the dynamic behavior of the wake. Indeed, a large part of the swirls emitted are smaller than in the case of a standard dome with regular faces. These swirls dissipate naturally naturally faster. The pulsed wake of the cupola of the invention also makes it possible to act on the possible detachments of the air flow at the level of the engine hoods at frequencies greater than the frequency of passage of the blades, which can reduce the intensity of the generated wakes. In addition, the magnitude of the forces and moments exerted on the fastening means of the dome to a rotor tend to be reduced.
    [0013] These frequencies can be adjusted by adapting the number and shape of the slots, and therefore without changing the overall size of the dome. Therefore, the invention can be implemented in place of an existing dome.
    [0014] In addition, each slot is also likely to drive stagnant flows under the dome, thus avoiding the presence of dead zones of flow. The direct consequence is a decrease in overall drag of the dome. The dome according to the invention may further comprise one or more of the following features. Thus, the periphery being possibly not circular but crenellated to define a succession of crenellations and cells, each cell allowing the flapping of a blade, the number of cells is different from the number of slots.
    [0015] The number of slots may be equal to the number of cells. Each slot can then in this case be arranged in the extension or mid-distance of these cells. However, the number of slots may be different from the number of cells. This characteristic makes it possible to act on the generated wake by introducing disturbances appearing at a natural frequency different from the frequency of the passage of the openings and the blades.
    [0016] As a result, the number of cells and the number of slots are favorably prime between them. Moreover, at least one slot extends along a radius of said dome.
    [0017] According to a first embodiment, all the slots extend in the cupola along a radius of this dome. These domes are thus obtained by making days in the cap along the rays. The slots may be distributed on the surface of the dome 10 in a regular arrangement being equidistributed angularly, or in an irregular arrangement. However, not all slots may extend radially. According to a variant, at least one slot does not therefore extend along a radius of the dome. According to a second embodiment, no slot extends into the cupola along a radius of this cupola These cupolas are obtained by making days in the cap either along rays, but along broken lines or curves passing 20 by the axis of rotation in elevation of the dome or along lines not passing through the axis of rotation in elevation of the dome. The slots can be distributed on the surface of the dome in a regular arrangement being equidistributed angularly, or in an irregular arrangement.
    [0018] A third embodiment provides for the arrangement of at least one slot extending along a radius and at least one slot not extending along a radius.
    [0019] At least one slot may have a convex shape having a convexity arrow directed in a direction of rotation of the dome. Moreover, at least one slot may have a width in azimuth which varies radially. In addition, at least one slot optionally extends into a crown of the dome disposed between said periphery and said axis of rotation in elevation. Such a crown does not reach the periphery and / or the axis of rotation. The slots can then be partial by being confined in a crown of the dome. Alternatively, at least one slot is conversely called "total" extending from the vicinity of the axis of rotation in elevation to the periphery 15 Indeed, at least one slot can lead to the periphery . Such a slot can be a partial or full slot. Moreover, according to one variant, the cap of the dome comprises a plurality of arms extending in span from the axis of rotation in elevation towards said periphery, each arm extending in azimuth between two slots opening out on the periphery, each arm having an aerodynamic profile extending in azimuth between a leading edge in the vicinity of a slot and a trailing edge in the vicinity of another slot. At least one arm may have a twisting law determining a twisting angle of each section of the arm as a function of a reference section. Therefore, each arm represents a twisted aerodynamic bearing surface.
    [0020] At least one arm may further have an azimuth width which increases away from the elevational axis of rotation. In addition to a dome, the invention is directed to a rotorcraft rotor having a hub carrying a plurality of blades. This rotor then comprises a dome of the type described above. The blades can not then penetrate the slots since these slots do not constitute cells capable of allowing in particular the flapping of the blades.
    [0021] In addition, the invention is directed to a rotorcraft comprising at least one rotor of this type. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a view of a rotorcraft according to the state of the technique without a cupola, - Figure 2, a view of a rotorcraft according to the invention, - Figure 3, a view of a dome provided with total slots 20 extending along the rays of the dome the slits having a constant azimuth width; and, FIG. 4, a view of a dome provided with partial slits extending along rays of the dome to the periphery of the cupola, the slits having a width of 25 mm. variable azimuth; FIG. 5, a view of a dome provided with partial slots extending along rays of the cupola in the vicinity of the axis of rotation in elevation of the dome, the slots having an azimuth width; variable, - figure 6, a view of a dome provided with a slot s partial disposed along lines not passing through the axis of rotation in elevation, and - Figure 7, a view of a dome provided with convex total slots defining arms having a variable width azimuth. The elements present in several separate figures are assigned a single reference. Note that three directions X, Y and Z orthogonal to each other are shown in the figures. The X direction is called longitudinal. Another direction Y is said transverse. Finally, a third direction Z is called elevation. Figure 1 shows a rotorcraft of the state of the art illustrating the problem of the invention. The rotorcraft 1 is conventionally provided with a cell extending from a nose to a tail including a tail boom 3. The tail beam 3 may carry a fin, empennages, or even a rotor. The cell carries at least one main rotor 4 at least partially ensuring the lift or propulsion of the rotorcraft. The wake 5 generated by the upper parts of the rotorcraft and in particular the rotor 4 is capable of impacting the tail of the aircraft, and in particular the drift and empennages.
    [0022] In addition, this wake 5 tends to detach from the cell at a detachment zone 7 located near engine hoods 6. FIG. 2 shows a rotorcraft 10 according to the invention.
    [0023] The rotorcraft 10 is provided with a cell extending from a nose to a tail including a tail boom 13. The cell carries at least one main rotor 14 providing at least partially the lift or propulsion of the rotorcraft. The rotor 14 then comprises a hub 18 carrying a plurality of blades 19.
    [0024] In addition, the rotor 4 comprises a dome 20 according to the invention. The dome is provided with a cap 25, for example spherical. This cap is for example fixed to the hub 18 to be integral in rotation with the main rotor 14. This cap 25 extends radially from an axis of rotation in elevation 100 to a periphery 27. The cap 25 further extends 360 degree azimuth. The cap 25 extends in elevation along its thickness from a lower face facing the hub 100 to an upper face. The center 26 of each face is then arranged on the axis of rotation 20 in elevation 100. In addition, the dome comprises at least one slot 40 formed in the cap between the axis of rotation in elevation 100 and the periphery 27 included. Each slot then passes through the cap from one end to the other depending on its thickness. Indeed, each slot 40 extends in elevation from the lower face to the upper face. Each slot then delimits an opening. Air can thus pass through the cap of its upper face to its lower face and vice versa through the opening formed by each slot. The wake 5 generated by the upper parts of the rotorcraft is then deflected downwards by the dome 20.
    [0025] During the rotation of the cupola, an incident air flow 300 successively impacts a solid surface of a face 31, 32 of the dome and an opening of a slot 40. The incident airflow 300 may impact a lower face 31 and an upper face 32 of the dome. The term "airflow impacting a slit" or equivalent expression means that the airflow is directed to a slit, and enters the opening formed by the slit. Conversely, the flow of air impacts, outside the slots, the solid surface of the lower face and / or the upper face. The slots 40 then make it possible to generate a pulsed wake that interacts with the wake generated by the cap. The overall wake generated by the cupola 20 potentially leads to a reduction in the overall intensity of the dynamic behavior of the wake 5 and tends to at least limit the detachment of the wake 5 in the separation zone 17 located near the engine hoods 16.
    [0026] FIGS. 3 to 7 illustrate variants of the cupola 20. With reference to FIG. 3, the cupola 20 is provided with a cap 25. The cap 25 thus extends radially from an axis of rotation in elevation 100 to A periphery 27. This periphery 27 can be crenellated to define a succession of crenellations 28 and cell 29. Each cell 29 is then arranged vis-à-vis a blade to prevent interference between the blade and the blade. cap after a flapping movement of the blade. By construction, no cell 29 is arranged between the periphery 27 and the axis of rotation in elevation 100 of the cap 26. In contrast, the cap is perforated between the periphery 27 and the axis of rotation. elevation 100 to present at least one slot 40. Each slot then passes through the thickness of the cap. With regard to an incident airflow 300, the cap 25 has a succession of openings 202 and solid surfaces 201 at least on a geometrical inner circle located at a radius 203 and centered on the axis of rotation in elevation. 100. Each opening is materialized by a slot 40, each solid surface being materialized by one face of the cap. Due to the rotation ROT of the dome around the axis of rotation in elevation 100, this incident air flow thus successively impacts an opening and a solid surface. The cap may comprise a plurality of slots 40. In particular the number of cells 29 may be different from the number of slots 40. This number of cells 29 and the number of slots 40 are for example prime between them.
    [0027] According to the first embodiment illustrated in FIGS. 3 to 5, at least one slot extends radially, and therefore along a radius 200 of the cap. For example, all slots extend radially. Independently of the embodiment, at least one slot may open out at the periphery 27.
    [0028] Thus, the variants of FIGS. 3 and 4 have slots which open out at the periphery 27, either at a crenel 28 or at a slot 29. Moreover, and independently of the embodiment, at least one slot may extend in span totally or partially along the cap. Therefore, the variant of Figure 3 has slots extending completely along a radius. These slots called "total slots" extend from an immediate proximity of the axis of rotation 10 in elevation 100 to the periphery 27. By cons, the variants of Figures 4 and 5 have slots extending partially along 'a ray. These slots called "partial slots" extend in a restricted ring 85 of the dome 20 disposed between the periphery 27 and the axis of rotation 15 in elevation 100. Each ring has a radius called "reduced radius 206" smaller than the smallest radius of the cap said "minimum radius 205". For example, the reduced radius 206 is less than 95% of the minimum radius, and in particular two-thirds of the minimum radius 205.
    [0029] In addition and independently of the embodiment, a slot may have a width 550 in a constant or variable azimuth direction. The width 550 of the slots 40 of the variant of FIG. 3 is thus constant in azimuth.
    [0030] Conversely, FIG. 4 shows slits having an azimuth width which increases away from the elevational axis of rotation 100.
    [0031] Figure 5 shows slits having an azimuth width which increases away from the elevational axis of rotation 100 to a maximum width. Then, the width decreases away from the axis of rotation in elevation 100.
    [0032] The elevation width of the slot from the underside to the upper face of the cap may also vary. According to the second embodiment illustrated in FIGS. 6 to 7, at least one slot does not extend radially. More specifically, Figure 6 illustrates partial slots, with Figure 7 showing total slots. According to the variant of FIG. 6, such a slot may extend along a line that does not pass through the center 26 of each face and the axis of rotation in elevation 100. Moreover, the example of the Figure 6 shows partial slots which have a constant width in azimuth and variable in elevation. According to variants, a slot may extend along a broken or convex line. For example, the example of FIG. 7 illustrates total slots that have variable width in azimuth. In addition, these slots have convex shapes having a convexity arrow 80 directed in a direction of rotation ROT of the dome 20. Furthermore, the cap 25 of Figure 7 comprises a plurality of aerodynamic arms 50.
    [0033] Each arm extends in span from the axis of rotation in elevation 100 to the periphery 27, and in azimuth in a direction D1 between two slots 40 opening on the periphery 27. Each arm 50 then has an aerodynamic profile which extends in azimuth between a leading edge 51 in the vicinity of a slot 40 and a trailing edge 52 in the vicinity of another slot 40. Figure 7 illustrates arms formed by non-radial slots. However, the caps of FIGS. 3 and 4 may also comprise arms provided with an aerodynamic profile. Regardless of the nature of the slots, at least one arm 50 may have a twisting law. Such twisting law usually determines a twisting angle of each section 54 of the arm as a function of a reference section 53. By "section" is meant a section of the arm in a plane extending in elevation from the trailing edge at the leading edge of the arm and perpendicular to a geometric stacking line of the arm. In addition, at least one arm 50 may have an azimuth width 55 that increases away from the elevational axis of rotation 100. Naturally, the present invention is subject to many variations in its implementation. artwork. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Dome (20) for a rotor (14) of a rotorcraft (10), said dome (20) comprising a cap (25) extending radially from an axis of rotation in elevation (100) to a periphery (27) ) and in 360-degree azimuth, said cap (25) extending in thickness from a lower face (31) intended to face a hub (18) of the rotor (14) towards an upper face (32) in line with said upper face (32), characterized in that said cupola (20) comprises at least one slot (40) extending between said periphery (27) and said axis of rotation in elevation (100), each slot (40) traversing from one side a thickness of the cap (25) extending in elevation from the lower face (31) to the upper face (32), said cupola (20) comprising in azimuth along at least one inner circle a succession of solid surfaces (201) represented by the upper face (32) and openings (202) represented by each slot (40) at the guarding an incident airflow (300) for said incident airflow (300) to successively impact a solid surface and an opening upon rotation of said dome (20) about the elevation axis (100).
    [0002]
    2. Dome according to claim 1, characterized in that said periphery (27) is not circular but crenellated to define a succession of crenellations (28) and cells (29), each cell (29) allowing the beat of a blade (19), the number of cells (29) is different from the number of slots (40).
    [0003]
    3. Dome according to claim 2, characterized in that the number of cells (29) and the number of slots (40) are first between them.
    [0004]
    4. Dome according to any one of claims 1 to 3, characterized in that the cap (25) comprises a plurality of arms (50) extending in wingspan from said axis of rotation in elevation (100) towards said periphery ( 27), each arm (50) extending in azimuth (D1) between two slots (40) opening on the periphery (27), each arm (50) having an aerodynamic profile extending in azimuth between a leading edge (51) in the vicinity of a slot (40) and a trailing edge (52) in the vicinity of another slot (40).
    [0005]
    5. Dome according to claim 4, characterized in that at least one arm (50) has a twisting law determining a twisting angle of each section (54) of the arm according to a reference section (53). .
    [0006]
    6. Dome according to claim 4, characterized in that at least one arm (50) has a width (55) in azimuth which increases away from said axis of rotation in elevation (100). 20
    [0007]
    7. Dome according to any one of claims 1 to 6, characterized in that at least one slot (40) extends along a radius (200) of said dome (20).
    [0008]
    8. Dome according to any one of claims 1 to 7, characterized in that at least one slot (40) does not extend along a radius of the dome.
    [0009]
    9. Dome according to any one of claims 1 to 3028497 19 characterized in that at least one slot (40) has a convex shape having a convex arrow (80) directed in a direction of rotation (ROT) of the cupola (20).
    [0010]
    10. Dome according to any one of claims 1 to 5 9, characterized in that at least one slot (40) has a radially varying azimuth width.
    [0011]
    11. Dome according to any one of claims 1 to 10, characterized in that at least one slot extends in a ring (85) of the dome (20) disposed between said periphery (27) and said axis of rotation in elevation (100).
    [0012]
    12. Dome according to any one of claims 1 to 15 characterized in that at least one slot opens on said periphery (27).
    [0013]
    Rotorcraft rotor rotor (10) having a hub (18) carrying a plurality of blades (19), characterized in that said rotor comprises a dome according to any one of claims 1 to 12, said blades that can not penetrate into said slots.
    [0014]
    14. Giravion (10), characterized in that said rotorcraft (10) comprises at least one rotor (14) according to claim 13. 25
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    引用文献:
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    FR3028496B1|2014-11-14|2016-12-09|Airbus Helicopters|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    FR3028497B1|2014-11-14|2017-11-03|Airbus Helicopters|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    FR3041605B1|2015-09-28|2017-10-13|Airbus Helicopters|COUPOLE OF ROTOR, ROTOR AND GIRAVION|FR3028496B1|2014-11-14|2016-12-09|Airbus Helicopters|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    FR3028497B1|2014-11-14|2017-11-03|Airbus Helicopters|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    US10220939B2|2015-12-18|2019-03-05|Sikorsky Aircraft Corporation|Active airflow system and method of reducing drag for aircraft|
    US10232929B2|2015-12-18|2019-03-19|Sikorsky Aircraft Corporation|Plate member for reducing drag on a fairing of an aircraft|
    FR3075757B1|2017-12-22|2019-11-15|Airbus Helicopters|AERODYNAMIC WRAPPED AERODYNAMIC ENVELOPES FOR BLADE COLLARS AND BLADE SLEEPING OF A ROTOR OF AN AIRCRAFT|
    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-20| PLSC| Publication of the preliminary search report|Effective date: 20160520 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
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    FR1402562A|FR3028497B1|2014-11-14|2014-11-14|COUPOLE OF ROTOR, ROTOR AND GIRAVION|FR1402562A| FR3028497B1|2014-11-14|2014-11-14|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    US14/939,275| US10167077B2|2014-11-14|2015-11-12|Rotor dome, a rotor, and a rotorcraft|
    KR1020150159622A| KR101887154B1|2014-11-14|2015-11-13|A rotor dome, a rotor, and a rotorcraft|
    ITUB2015A005560A| ITUB20155560A1|2014-11-14|2015-11-13|DOME OF ROTOR, ROTOR AND AIRBRUSH|
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