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1.发明申请公开(公告)号：US20180281979A1
公开(公告)日：2018-10-04
申请号：US15764302
申请日：2016-09-26
发明人： Pierre-Alain Jean Philippe REIGNER , Antoine Jean-Philippe BEAUJARD , Augustin Marc Michel CURLIER
IPC分类号： B64D27/14 , B64C11/48 , B64D35/06 , B64D35/08 , B64D33/02 , F16H48/05 , F16H48/08 , F16H48/10
CPC分类号： B64D27/14 , B64C11/48 , B64D33/02 , B64D35/06 , B64D35/08 , F02C7/36 , F02K3/072 , F05D2220/323 , F05D2260/40311 , F16H48/05 , F16H48/08 , F16H48/10
摘要： The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least one propeller (71, 73) driven mechanically by the engine shafts (32, 52), characterised in that the propulsion unit (7) includes two propellers (71, 73), each of the propellers being driven by a propeller shaft (72, 74), the two propeller shafts being driven by the engine shafts (32, 52) via a first differential epicyclic gear train (40). Specifically, the input of the first differential gear train (40) is connected to the output of a second differential epicyclic gear train (60), the second differential gear train (60) including two inputs (61c2, 62c2), each of said two inputs being connected mechanically to one of said engine shafts (32, 52).
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公开(公告)号：US20180266316A1
公开(公告)日：2018-09-20
申请号：US15764864
申请日：2016-10-05
发明人： Laurent SOULAT , Kevin Morgane LEMARCHAND , Tewfik BOUDEBIZA , Gilles Alain CHARIER , Nathalie NOWAKOWSKI , Augustin Marc Michel CURLIER , Adrien Pierre Jean PERTAT , Pierre-Alain Jean Philippe REIGNER
CPC分类号： F02C3/10 , B64D27/12 , B64D27/18 , B64D27/26 , B64D35/04 , B64D2027/266 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , F02K3/062 , F05D2220/323 , F05D2220/36 , F05D2240/14 , F05D2240/40 , F05D2240/60 , F05D2250/312 , F05D2260/40311
摘要： The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY′) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.
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公开(公告)号：US20170096942A1
公开(公告)日：2017-04-06
申请号：US15284329
申请日：2016-10-03
CPC分类号： F02C7/36 , F01D5/02 , F02C3/04 , F02C3/107 , F02C3/113 , F04D29/053 , F04D29/325 , F05D2220/323 , F05D2240/35 , F05D2240/60 , F05D2250/312 , F05D2260/40311 , F16H48/08
摘要： The invention relates to a propulsion unit of an aircraft comprising a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.
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