• 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 dome (20) for a rotor of a rotorcraft, 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 be opposite a hub (18) of the rotor (14) towards an upper face (32) to the plumb with said upper face (32). At least one of said upper (32) and lower (31) faces is an undulating face (33) which is undulated at least in azimuth between the periphery (27) and said elevational axis of rotation (100) including azimuth along at least one inner circle (90) is a succession of bumps (201) and depressions (202).
    公开号:FR3028496A1
    申请号:FR1402558
    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 a zone, 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 increase the intensity of the aerodynamic excitations on the tail, as well as to enrich the frequency signature of these excitations. To reduce these excitations, a dome can be arranged on the head of the lift rotor. A dome is generally in the form of a substantially ellipsoidal cap 20 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. Therefore, a dome may comprise an ellipsoidal crown of revolution provided with a cell by blade of the rotor.
    [0005] During a flight in translation, this dome 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 tail-shake effect is then reduced. 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.
    [0006] 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 3028496 4 of a lower face intended to be facing a hub of the rotor to an upper face in line with this upper face. In addition, at least one of the upper and lower faces is a corrugated face at least in azimuth between its periphery and the axis of rotation in elevation, comprising in azimuth along at least one inner circle a succession of bumps and grooves. hollow with regard to a flow of incident air so that the incident air flow successively impacts a bump and a hollow during a rotation of the dome around the axis of rotation in elevation.
    [0007] This cupola makes it possible to modify the air flow by generating geometrical variations of the cap. Indeed, the corrugated shape of at least one of the upper and lower faces introduces discontinuously discontinuous geometric variations of the dome radially and azimutally.
    [0008] Each undulating face describes along a circle a movement which successively lowers and rises. The presence of corrugations thus makes it possible to generate bumps and hollows on the dome with regard to the flow of incident air. The presence of bumps and valleys generates a pulsating flow. Indeed, the incident air flow impacting the cap undergoes successive passes bumps and valleys, especially due to the rotation of the dome. The undulating shape of the dome in azimuth in at least one radius has the effect of disturbing the flow of incident air at the frequency of successive bumps and valleys. The dome 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 due to the highly non-linear nature of this type of interaction. As a result, the wake generated by the cupola 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 vortices emitted are smaller in size than in the case of a standard dome. These vortices therefore dissipate naturally faster. The pulsed wake of the dome of the invention also makes it possible to act on any detachments of the air flow at the engine hoods at frequencies greater than the frequency of passage of the blades, which can reduce the intensity generated wakes.
    [0009] In addition, the magnitude of the forces and moments exerted on the means fixing the dome to a rotor tend to be reduced. These frequencies can be adjusted by adapting the corrugations, and therefore without changing the overall size of the dome.
    [0010] Therefore, the invention can be implemented in place of an existing dome. The dome according to the invention may further comprise one or more of the following features. For example, the upper face of the dome is a corrugated face. Furthermore, the corrugated face may have a plurality of upper edges and a plurality of lower ridges extending in span from the axis of rotation in elevation of the cap towards the periphery of this cap, each lower edge being arranged in azimuth between two upper edges, said upper edges being contained in a non-corrugated upper geometrical surface in line with a non-corrugated lower geometrical surface containing said lower edges, said corrugated undulating surface in azimuth between said upper geometrical surface and the lower geometric surface. So called "edge" a geometric line representing the top or the bottom of a wave of the corrugated face 10. The upper non-corrugated geometrical surface and the lower non-corrugated geometrical surface may be ellipsoidal caps of revolution, for example. Moreover, said periphery is not circular but crenellated to define a succession of crenellations and cells, each cell allowing in particular the flapping of a blade. The number of cells may be different from the number of upper edges. The number of upper edges is chosen according to the result expected by the manufacturer. This number of upper edges may be completely independent of the number of cells. Favorably, the number of upper edges is greater than the number of cells. In particular, the number of cells and the number of upper edges are for example prime between them. On the other hand, the azimuthal angle separating two adjacent upper edges may not be identical for all the upper edges.
    [0011] Furthermore, the cap may comprise a non-corrugated median geometric reference surface arranged between the lower face and the upper face. The cap then has in elevation a thickness between each corrugated face and the median non-corrugated reference median geometric surface 5 varying at least in azimuth, this thickness varying continuously between a maximum thickness reached at each upper edge and a minimum thickness reached at the level of each lower edge. The thickness between the corrugated face and the non-corrugated median reference geometrical surface may also vary continuously radially. In addition, the lower face and the upper face are optionally symmetrical with respect to the median non-corrugated reference geometrical surface.
    [0012] This type of dome is obtained by considering an azimuthal modification of the thickness of the dome uncoupled from the radial modification of the thickness between each undulating face and a non-corrugated median geometrical surface. This median non-corrugated geometrical surface is arranged between said lower surface and said upper surface and may have an optionally ellipsoidal crown shape of revolution. The thickness of the dome varies continuously between two values characterizing generators of maximum thickness represented by upper edges and generators of minimum thickness represented by lower edges. The variation of the thickness for a given radial position with respect to the axis of rotation in elevation and an azimuth position 0 between two generators of minimum and maximum thickness may be monotonous.
    [0013] This thickness is for example determined by the following relation: e (r, B) = e0 + f (r) g (e) where e (r, O) represents said thickness, e0 is a constant representing an average thickness, and f (r) and g (6) respectively represent radial and azimuthal variation laws of the thickness between a non-corrugated median reference geometric surface and a wavy face. A constructor then determines the radial variation laws f (r) and azimuth g (8) by tests for example.
    [0014] In addition, according to a first embodiment, at least one of said upper and lower edges extends radially. Optionally, each edge extends from the axis of rotation in elevation to the periphery along a radius of the cap. According to a first variant of the first embodiment, said thickness varies linearly. This thickness is then possibly determined by the following relation between a given lower edge and the given upper edge which follows this given lower edge: 0-0m 1) e (r, 6) = eo + De (r) (em _om 2 where e (r, 6) represents said thickness, e0 is a constant 20 representing a mean thickness, represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "B" represents a position in azimuth between said given lower edge and said given upper edge, "Om" represents an azimuth position of said given lower edge with respect to a reference radius, "Om" represents an azimuth position of said given upper edge relative to the reference radius Optionally, the law providing a difference between a maximum thickness and a minimum thickness at a radial position is a constant. According to a second variant of the first embodiment, said thickness varies azimutally in a sinusoidal manner. This thickness is then possibly determined by the following relation: sin [ir (9 em 1) 1 e (r, 6) = e0 + Ae (r) em - Om 2 10 where e (r, O) represents said thickness, e0 is a constant representing an average thickness, Le represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "9" represents an azimuth position between said given lower edge and said given upper edge , "Om" represents an azimuth position of said given lower edge with respect to a reference radius, "Om" represents an azimuth position of said given upper edge with respect to the reference radius. Optionally, the law providing a difference between a maximum thickness and a minimum thickness at a radial position is a constant. According to a second embodiment, at least one of said ridges does not extend along a radius of the cap. For example, no ridge extends into the cupola along a radius of this dome.
    [0015] Each edge then has a broken or curved line passing through the elevational axis of rotation of the cupola. In particular, at least one edge is curved. This variant consists in bending the edges along curves and no longer rays. Non-regular curves can be considered. Nevertheless, at least one edge may have a convex shape having a convexity arrow directed in a direction of rotation of the dome.
    [0016] According to a first variant of the second embodiment, said thickness varies linearly azimuthally. This thickness is for example determined by the following relation: e (r, 6) = eo + De (r) (9m (r) 1) Um (r) - 8 ,,, where e (r, 9) represents said thickness , e0 is a constant 15 representing an average thickness, De represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "9" represents an azimuth position between said given lower edge and said edge given upper, "9m (r)" represents a law giving an azimuth position of said given lower edge with respect to a reference radius, "9M (r)" represents a law giving an azimuth position of said given upper edge relative to the reference radius. Optionally, the law providing a difference between a maximum thickness and a minimum thickness at a radial position is a constant.
    [0017] The curvatures of two successive edges of minimum and maximum thickness are constructed from increasing functions of the radial position r (condition of convexity), continuous in pieces. For any radial position, the azimuth position of an upper edge is greater than the azimuth position of the previous lower edge is: 0m (r)> Om (r). According to a second variant of the second embodiment, said thickness varies azimutally sinusoidally. This thickness is for example determined by the following relationship: Kr, 0) = e0 + De (r) 2 where e (r, 0) represents said thickness, e0 is a constant representing an average thickness, Le represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "8" represents an azimuth position between said given lower edge and said given upper edge, "Om (r)" represents a position giving direction. Azimuth of said given lower edge with respect to a reference radius, "Om (r)" represents a law giving an azimuth position of said given upper edge with respect to the reference radius. Like the first variant, the curvatures of two successive edges of minimum and maximum thickness are constructed from increasing functions of the radial position r (condition of convexity), continuous in pieces. For any radial position, the azimuth position of an upper edge is greater than the azimuth position of the previous lower edge is: 0m (r)> am (r). This type of cupola potentially contributes to an additional generation of vortices in the wake of the dome, via the curvature of the ridges, to tend to limit the direct impact of the dome. wake generated on the drift.
    [0018] A third embodiment may provide for the arrangement of at least one edge extending along a radius and at least one edge not extending along a radius. Independently of the embodiment, at least one corrugated face may present in azimuth, along a circle at a given radius of the axis of rotation in elevation, a sinusoidal shape between an upper edge and a lower edge adjacent to this upper edge. 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 previously described which is integral in rotation with said hub, for example. 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 2, a view of a rotorcraft according to the invention, FIGS. 3 and 4, top and bottom views, respectively, of a dome provided with undulating faces 3028496 13 having upper and lower edges extending along rays of the dome; - Figure 5, a diagram explaining the arrangement of a corrugated face between two non-wavy geometric surfaces, 5 - Figure 6, a view from above a dome provided with corrugated faces having sinusoidal portions between upper and lower edges extending along rays of the dome; - Figure 7, a diagram explaining the construction of a cap defining a relationship; Thickness with respect to a reference geometrical surface, and - Figures 8 and 9 respectively top and bottom views of a dome provided with corrugated faces having convex upper and lower edges.
    [0019] 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 called 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 boom 3 can carry a fin, empennages, or even a rotor.
    [0020] The cell carries at least one main rotor 4 ensuring at least partially 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 likely to impact the tail of the aircraft, and in particular the drift and empennages. In addition, this wake 5 tends to detach from the cell at a detachment zone 7 located near engine hoods 6. Figure 2 shows a rotorcraft 10 according to the invention.
    [0021] 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 at least partially providing lift or even propulsion of the rotorcraft. The rotor 14 then comprises a hub 18 carrying a plurality of blades 19.
    [0022] In addition, the rotor 4 comprises a dome 20 according to the invention. The cupola is provided with a cap 25. This cap 25 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 in azimuth 360 degrees. The cap 25 extends more and more in elevation along its thickness with a lower face 31 facing the hub 100 towards an upper face 32. The center 26 of each of the lower faces 31 and upper face 32 is then arranged on an axis of rotation in elevation 100.
    [0023] In addition, the lower face 31 and / or the upper face 32 is an undulating face 33 at least in azimuth. Such an undulating face 33 is then sinuous by having azimuthally a succession of depressions forming depressions 5 and protrusions forming bumps. The wake 5 generated by the upper parts of the rotorcraft is then deflected downwards by the cupola 20. During the rotation ROT of the dome around the axis of rotation in elevation 100, an incident airflow 300 impacts 10 successively a hump and a hollow. The undulations of each undulating face then generate a pulsed wake. This pulsed wake generated by the dome 20 potentially leads to a reduction in the overall intensity of the wake dynamic behavior 5 and tends to at least limit the wake 5 detachment in the detachment zone 17 located close to the engine hoods 16. Referring to Figure 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.
    [0024] This periphery 27 may be crenellated so as to define a succession of crenellations 28 and cell 29. Each cell 29 is then arranged vis-à-vis a blade to avoid interference between the blade and the cap following a movement in beat 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. The cap 25 further comprises at least one corrugated surface 33. For example, the upper face 32 of the cap 25 is an undulating face 33.
    [0025] However, and with reference to FIG. 4, the lower face alternatively or alternatively may be a corrugated face 33. With reference to FIG. 3, each undulating face has a sinuous shape in azimuth. This corrugated face thus has a plurality of upper edges 41 and a plurality of lower edges 42 which extend along their span from the center 26 of the undulating face towards the periphery 27. By construction, each lower edge 42 is arranged in azimuth between two upper edges 41. The corrugated face then undulates in azimuth between two upper edges 41 passing through a lower edge 42. With regard to an incident airflow 300, the cap 25 has during its rotation a succession of Hollow 202 and bumps 201 15 at least on a geometric inner circle 90 located at a radius 203 of the axis of rotation in elevation 100. Each depression 202 is materialized by a lower edge 42, each bump 201 being materialized by an upper edge 41. Due to the rotation ROT of the dome around the axis of rotation in elevation 100, this incident air flow 300 thus successively impacts a hollow and a bump. In particular the number of cells 29 may be different from the number of upper edges 41. This number of cells 29 and the number of upper edges 41 are for example prime between them. With reference to FIG. 5, the upper edges 41 are contained in a non-corrugated upper geometrical surface 37, in the form of a Chinese hat, for example. Likewise, the lower edges 42 are contained in a non-corrugated lower geometrical surface 36, in the form of a Chinese hat, for example. Therefore, the non-corrugated upper geometric surface 37 is plumb with the undulating underrowed geometric surface 36. In addition, the non-corrugated upper geometric surface 37 and the undulating underreamed geometric surface 36 are intersecting at the center of the the wavy face. As a result, the corrugated face undulates in azimuth between the non-corrugated upper geometrical surface 37 and the undulated underrubed geometrical surface 36. In particular and with reference to FIGS. 5 and 6, for example, at least one undulating face has azimuth along it. a circle at a given radius 200 of said elevation axis 100 has a sinusoidal shape between an upper edge 41 and a lower edge 42 adjacent to this upper edge 41. With reference to FIG. 7, a corrugated face may be obtained by modifying the thickness of this corrugated face 33 with respect to a median non-corrugated reference geometrical surface 50.
    [0026] Such a non-corrugated central reference geometrical surface 50 may be in the form of an ellipsoidal crown of revolution or a Chinese cap, for example. In addition, the lower face 31 and the upper face 32 may be two corrugated faces 33 disposed symmetrically on either side of the median non-corrugated reference geometrical surface 50. As a result, the cap 25 has an ep thickness in elevation. between each undulating face 33 and the non-waved median reference geometrical surface 50 which varies at least in azimuth. This thickness ep varies for example continuously between a maximum thickness epmax reached at each upper edge 41 and a minimum thickness epmin reached at each lower edge 42. Such a thickness is determined by the following relation: e (r,, 9) = e0 + f (r) g (0) where e (r, 0) represents said thickness, e0 is a constant representing an average thickness, and f (r) and g (0) respectively represent laws of variation radial and azimuthal thickness between a non-corrugated median geometric reference surface and a wavy face. The azimuthal variation law can provide a value relative to the thickness to be attained at a position in azimuth 0 between a ridge 15 called a "given lower edge 42 '" and a ridge called "given upper edge 41'" adjacent to the ridge. lower datum 42 ', this azimuth position 9 being marked with respect to a reference ray 500. In addition, the azimuthal variation law can provide said value 20 as a function of the azimuth position m of said given lower edge 42 relative to to the reference radius 500 and the azimuth position 9M of said given upper edge 41 relative to the reference radius 500. According to the first embodiment explained by FIGS. 3, 4 and 6, at least one of said upper edges 41 For example, all the ridges extend along a radius of the cap. According to a first variant of the first embodiment illustrated in FIGS. 3 and 4, the thickness separating a corrugated face 5 from a median non-corrugated reference geometrical surface 50 is determined by the following relationship between a given lower edge 42 and a given upper edge 41 which follows this given lower edge 42: e (r, 0) = e0 + De (r) (- 1 Bly-Om where e (r, 0) represents said thickness, e0 is a constant 10 representing a mean thickness, Le represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "0" represents a position in azimuth between said given lower edge 42 and said given upper edge 41, "8m" represents an azimuth position of said given lower edge 42 with respect to a reference radius 500, "Om" represents an azimuth position of said given top edge 41 by For example, the law Ae is a constant according to the variant of FIGS. 3 and 4.
    [0027] According to a second variant of the first embodiment illustrated in FIG. 6, said thickness is determined by the following relation between a given lower edge 42 and a given upper edge 41 which follows this given lower edge 42: sin rir t9 61n 1) Where e (r, 0) represents said thickness, e0 is a constant 25 representing an average thickness, De represents a law providing a difference between a maximum thickness and an e (r, 0) = e0 + De (r) 3028496 minimum thickness at a radial position "r", "61" represents an azimuth position between said given lower edge 42 and said given upper edge 41, "On," represents an azimuth position of said given lower edge 42 with respect to a reference radius 500, "Om" represents an azimuth position of said given upper edge 41 with respect to the reference radius 500. According to the second embodiment of FIG. 8 and 9, at least one of said upper and lower edges 41 and 42 does not extend along a radius of the cap 25. For example, at least one edge 40 has a convex shape with a convexity arrow 80 according to a direction of rotation ROT of the cupola 20. According to a first variant of the second embodiment illustrated in FIG. 8, the thickness separating a corrugated face from a median non-corrugated reference geometrical surface 50 is determined by the following relation between a given lower edge 42 and a given upper edge 41 which follows this given lower edge 42: e (r, = eo + De (r) t51 (9 - em (r) 1 , 11 (r) - 8m (r) 2) where e (r, 6) represents said thickness, e0 is a constant representing a mean thickness, / le represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r" , "8" represents e an azimuth position between said given lower edge 42 and said given upper edge 41, "8m (r)" represents a law giving an azimuth position of said given lower edge 42 with respect to a reference radius 500, "8M (r) "represents a law giving a position in azimuth of said given upper edge 41 with respect to the reference radius 500. According to a second variant of the second embodiment illustrated in FIG. 9, the thickness separating a face 5 The corrugated waveform of a nonwaved reference median geometric surface 50 is determined by the following relationship between a given lower edge 42 and a given upper edge 41 which follows that given lower edge 42: sin [n (61ftie (r39-mt5 (smr ( r) 121 e (r, 0) = e0 + The (r) 2 where e (r, O) represents said thickness, e0 is a constant 10 representing an average thickness, De represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "0" represents an azimuth position between said given lower edge 42 and said given upper edge 41, "Orn (r)" represents a law giving a position azimuth of said given lower edge 42 with respect to a reference radius 500, "9M (r)" represents a law giving an azimuth position of said given upper edge 41 with respect to the reference radius 500. Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the 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 (18)
    [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 at least one of said upper (32) and lower (31) faces is an undulating face (33) at least in azimuth between the periphery (27) and said axis of rotation in elevation (100) comprising, in azimuth, along at least one inner circle (90) a succession of bumps (201) and recesses (202) with respect to an incident air flow (300) so that said incident airflow (300) successively impacts a hump and a depression upon rotation of said dome (20) about the elevational axis of rotation (100).
    [0002]
    2. Dome according to claim 1, characterized in that the upper face (32) is a corrugated face.
    [0003]
    3. Dome according to any one of claims 1 to 2, characterized in that said corrugated surface has a plurality of upper edges (41) and a plurality of lower edges (42) extending in wingspan of said axis of rotation in elevation (100) to said periphery (27), each lower edge (42) being arranged in azimuth between two upper edges (41), said upper edges (41) being contained in a non-corrugated upper geometrical surface (37) to perpendicular to a lower non-corrugated geometric surface (36) containing said lower edges (42), said undulating corrugated surface in azimuth between said non-corrugated upper geometric surface (37) and the undulated underride geometric surface (36) . 5
    [0004]
    4. Coupole according to claim 3, characterized in that said cap (25) having a median non-corrugated reference geometrical surface (50) arranged between said lower face (31) and said upper face (32), said cap (25) has in elevation a thickness (ep) between each corrugated surface (33) and said non-corrugated median reference geometrical surface (50) which varies at least in azimuth, said thickness (ep) continuously varying between a maximum thickness (epmax) reached at each upper edge (41) and a minimum thickness (epmin) reached at each lower edge (42).
    [0005]
    5. Dome according to said claim 4, characterized in that said lower face (31) and said upper face (32) are symmetrical with respect to said median non-corrugated reference geometrical surface (50).
    [0006]
    Dome according to claim 4, characterized in that said thickness is determined by the following relation: e (r,, 0) = e0 + f (r) g (0) where e (r, 6) represents said thickness, e0 is a constant representing an average thickness, and f (r) and g (0) respectively represent radial and azimuthal variation laws of the thickness between a non-corrugated median reference geometric surface and an undulating face. 3028496 24
    [0007]
    7. Dome according to any one of claims 3 to 6, characterized in that at least one of said ridges (41, 42) extends radially.
    [0008]
    Dome according to claim 4, characterized in that said thickness is determined by the following relation between a given lower edge (42) and the given upper edge (41) following said given lower edge (42): Where e (r, 0) represents said thickness, e0 is a constant representing an average thickness, represents it a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "0" represents an azimuth position between said given lower edge (42) and said given upper edge (41), "em" represents an azimuth position of said edge given datum (42) relative to a reference radius (500), "Om" represents an azimuth position of said given upper edge (41) relative to the reference radius (500).
    [0009]
    9. Dome according to said claim 4, characterized in that said thickness is determined by the following relationship: - em 2- sin L - 077, 1) 1 ne (r, 0) = e0 + Ae (r) t911,1 where Kr, 0) represents said thickness, e0 is a constant representing an average thickness, De represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "0" represents an azimuth position between said given lower edge (42) and said given upper edge (41), "Om" represents an azimuth position of said given lower edge (42) with respect to a reference radius (500), "Om" represents an azimuth position of said given upper edge (41) with respect to the reference radius (500).
    [0010]
    10. Dome according to any one of claims 4 to 6, characterized in that at least one of said edges (41, 42) does not extend along a radius of the cap (25). 10
    [0011]
    11. Dome according to claim 10, characterized in that at least one edge (40) has a convex shape having a convexity arrow (80) directed in a direction of rotation (ROT) of the dome (20).
    [0012]
    12. Dome according to any one of claims 4 to 6, characterized in that said thickness is determined by the following relationship: e (r, = e 0 + Ae (r) 0 - 0, (r) m (r ) - 0, (r) 2) where e (r, 0) represents said thickness, e0 is a constant representing an average thickness, De represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position " r "," 0 "represents an azimuth position between said given lower edge (42) and said given upper edge (41)," 9m (r) "represents a law giving an azimuth position of said given lower edge (42). relative to a reference radius (500), "(r)" represents a law giving an azimuth position of said given upper edge (41) with respect to the reference radius (500).
    [0013]
    13. Dome according to any one of claims 4 to 6, characterized in that said thickness is determined by the following relation: sin [ff (9me (r39-mer) 211e (r, 0) = eo + Ae (r) 2 where e (r, 0) represents said thickness, e0 is a constant representing an average thickness, Lie represents a law providing a difference between a maximum thickness and a minimum thickness at a radial position "r", "9 "Represents an azimuth position between said given lower edge (42) and said given upper edge (41)," 9m (r) "represents a law giving an azimuth position of said given lower edge (42) with respect to a radius reference numeral (500), "0M (r)" represents a law giving an azimuth position of said given upper edge (41) with respect to the reference radius (500).
    [0014]
    14. Dome according to any one of claims 3 to 4 characterized in that at least one corrugated face has in azimuth, along a circle located at a given radius of said axis of rotation in elevation (100), a sinusoidal form between an upper edge (41) and a lower edge (42) adjacent to this upper edge (41).
    [0015]
    15. Dome according to claim 3, 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 flapping of a blade (19), the number of cells (29) is different from the number of upper edges (41).
    [0016]
    16. Dome according to claim 15, characterized in that the number of cells (29) and the number of upper edges (41) are first between them.
    [0017]
    17. rotorcraft rotor (14) having a hub (18) carrying a plurality of blades (19), characterized in that said rotor (14) comprises a dome (20) according to any one of claims 1 to 16.
    [0018]
    18. Giravion (10), characterized in that said rotorcraft (10) comprises at least one rotor (14) according to claim 17.
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    同族专利:
    公开号 | 公开日
    ITUB20155562A1|2017-05-13|
    KR20160058055A|2016-05-24|
    FR3028496B1|2016-12-09|
    KR101887153B1|2018-08-09|
    US20160137297A1|2016-05-19|
    US10040545B2|2018-08-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6443531B1|2000-09-21|2002-09-03|Mckechnie Vehicle Components , Inc.|Method for manufacturing a wheel cover|
    EP2474469A1|2011-01-11|2012-07-11|Eurocopter Deutschland GmbH|Device for adaptive balancing of rotary devices|
    EP2727832A1|2012-10-31|2014-05-07|Eurocopter Deutschland GmbH|Rotor head of a rotary wing flying machine and method of manufacturing and assembling such a rotor head|
    US20090304511A1|2005-09-30|2009-12-10|Brannon Iii William W|Aerodynamic shroud having textured surface|
    US8287243B2|2008-01-24|2012-10-16|General Electric Company|Spinner of a wind turbine|
    KR101494370B1|2013-07-31|2015-02-23|앰코 테크놀로지 코리아 주식회사|Tilt sensor package and method thereof|
    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|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|
    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:
    申请号 | 申请日 | 专利标题
    FR1402558A|FR3028496B1|2014-11-14|2014-11-14|COUPOLE OF ROTOR, ROTOR AND GIRAVION|FR1402558A| FR3028496B1|2014-11-14|2014-11-14|COUPOLE OF ROTOR, ROTOR AND GIRAVION|
    US14/939,208| US10040545B2|2014-11-14|2015-11-12|Rotor dome, a rotor, and a rotorcraft|
    ITUB2015A005562A| ITUB20155562A1|2014-11-14|2015-11-13|DOME OF ROTOR, ROTOR AND AIRBRUSH|
    KR1020150159616A| KR101887153B1|2014-11-14|2015-11-13|A rotor dome, a rotor, and a rotorcraft|
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