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公开(公告)号：US20190285029A1
公开(公告)日：2019-09-19
申请号：US16317377
申请日：2017-07-11
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: The invention concerns a propulsion device (1) comprising a torque generator (2) driving an output shaft (3) via a power gearbox (4), the output shaft (3) being rotatably coupled to a thruster (5), said power gearbox (4) being fixed on a frame (7) by means of suspension means (8, 14, 15), said suspension means including hydraulic torque recovery means comprising at least a first hydraulic system (15) and a second hydraulic system (15) spaced from each other, each hydraulic system (15) having a pressure chamber whose volume varies according to the position of the housing (9) of the power gearbox (4) relative to the frame (7), the pressure chambers of the hydraulic systems (15) being connected by a capillary so that a hydraulic fluid is able to flow from one pressure chamber to another via the capillary.
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2.发明申请公开(公告)号：US20190331028A1
公开(公告)日：2019-10-31
申请号：US16347300
申请日：2017-11-09
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A turboprop including a propeller shaft and a gas generator running along this propeller shaft, this gas generator including a high-pressure shaft and a hollow low-pressure shaft both extending along the same longitudinal axis, the low-pressure shaft having a rear end coupled to a rear end of the propeller shaft via a reducer. It includes an accessory box contiguous to the reducer while being located facing a rear end of the low-pressure shaft, and coupled to the rear end of the high-pressure shaft by a shaft passing through the low-pressure shaft.
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公开(公告)号：US20190270524A1
公开(公告)日：2019-09-05
申请号：US16320264
申请日：2017-07-20
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Frederic Paul EICHSTADT , Nora EL GHANNAM , Romain Jean-Claude FERRIER , Antoine Elie HELLEGOUARCH
Abstract: The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said arches (16, 18) being open at their lower ends and connected to each other by at least one axial longeron (34) extending between said arches (16, 18), characterised in that the longeron (34) is arranged in an upper portion of the cradle (10) and is formed in a single piece with the front arch (16).
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公开(公告)号：US20180105278A1
公开(公告)日：2018-04-19
申请号：US15729504
申请日：2017-10-10
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Nora EL GHANNAM , Matthieu Etienne ATTALI , Romain Jean-Claude FERRIER , Caroline Marie FRANTZ , Thomas Gerard Daniel RIVIERE , Nicolas Xavier TRAPPIER
CPC classification number: B64D27/26 , B64D27/12 , B64D29/08 , B64D2027/264 , F02C6/206 , F02C7/04 , F02C7/20 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2250/312 , F05D2260/15 , F05D2260/40 , F05D2260/4031 , Y02T50/671
Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
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