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1.发明申请公开(公告)号：US20230033330A1
公开(公告)日：2023-02-02
申请号：US17789325
申请日：2020-12-24
申请人： LEONARDO S.P.A.
摘要： An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.
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公开(公告)号：US20240167561A1
公开(公告)日：2024-05-23
申请号：US18549272
申请日：2022-03-01
申请人： LEONARDO S.P.A.
CPC分类号： F16H57/082 , B64D35/02 , F16H2200/2007
摘要： An aircraft capable of hovering is described, comprising a motor member; a rotor connected to the motor member; a transmission shaft rotatable around a first axis and adapted to drive the rotor; and a transmission interposed between the motor member and the rotor and comprising a planetary gear formed by a sun rotatable around a second axis; a crown that is angularly fixed; and two satellites meshing, each, with the crown and the sun, and rotatable around respective third axes, which are, in turn, rotatable around the second axis; and a satellite carrier rotatable around the second axis and comprising two first pins with respect to which the satellites are rotatable around the respective third axes; the transmission comprises an interface, angularly integral with the satellite carrier around the second axis and said transmission shaft around the first axis; the interface being coupled to said satellite carriers and the transmission shaft so as to allow an angular misalignment between the second axis and a portion of the interface.
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公开(公告)号：US11319061B2
公开(公告)日：2022-05-03
申请号：US16621178
申请日：2018-06-28
申请人： LEONARDO S.P.A.
发明人： Attilio Colombo , Luigi Bottasso , Paolo Pisani , Andrea Favarotto , Dario Colombo , Federico Montagna , Roberto Regonini , Francesco Braghin , Simone Cinquemani
摘要： A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.
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公开(公告)号：US20210163124A1
公开(公告)日：2021-06-03
申请号：US17264180
申请日：2019-07-26
申请人： LEONARDO S.P.A.
发明人： Paolo Pisani , Federico Montagna , Stefano Poggi
摘要： A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.
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公开(公告)号：US11891187B2
公开(公告)日：2024-02-06
申请号：US17414499
申请日：2019-11-28
申请人： LEONARDO S.P.A.
CPC分类号： B64D35/00 , B64C29/0033 , F16C19/18 , F16C19/543 , F16C25/083 , F16C2326/43
摘要： An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.
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公开(公告)号：US11851171B2
公开(公告)日：2023-12-26
申请号：US17264180
申请日：2019-07-26
申请人： LEONARDO S.P.A.
发明人： Paolo Pisani , Federico Montagna , Stefano Poggi
CPC分类号： B64C27/04 , F02C7/14 , F28D9/0068 , F28D2021/0021 , F28D2021/0049 , F28D2021/0089
摘要： A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.
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公开(公告)号：US20240159310A1
公开(公告)日：2024-05-16
申请号：US18551029
申请日：2021-12-20
申请人： LEONARDO S.P.A.
IPC分类号： F16H57/08 , B64D35/00 , F16C19/38 , F16C33/30 , F16C33/36 , F16C33/46 , F16C33/48 , F16C33/58 , F16H1/28
CPC分类号： F16H57/082 , B64D35/00 , F16C19/38 , F16C33/303 , F16C33/36 , F16C33/4623 , F16C33/48 , F16C33/585 , F16H1/28 , F16C2326/43 , F16C2361/61 , F16H2057/085
摘要： A description is provided of a planetary gear comprising a sun rotatable around a first axis, a crown angularly fixed with respect to the first axis; two satellites that are meshing, rotatable around respective second axes; a satellite carrier rotatable around the first axis and comprising at least two first pins with respect to which the satellites are rotatable around respective second axes (I); and a plurality of bearings comprising: a first ring defining a first raceway that is at least partially spherical; a second ring defining a second raceway; and a plurality of rolling bodies shaped as an hourglass rolling on the first spherical raceway and a second raceway; each rolling body being in contact with the raceways at a line with axial ends lying on respective straight lines tilted between them and converging in a point lying on a median plane of the rolling body and on the second axis; the straight lines define a first angle, whose bisector lies on the first median.
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公开(公告)号：US20220073201A1
公开(公告)日：2022-03-10
申请号：US17414499
申请日：2019-11-28
申请人： LEONARDO S.P.A.
摘要： An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element (rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component (defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component (defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.
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