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公开(公告)号：US11952904B2
公开(公告)日：2024-04-09
申请号：US17905717
申请日：2021-03-04
发明人： Romain Truco , Claire Marie Figeureu , Paul Ghislain Albert Levisse , Pierre-Alain Jean Philippe Reigner , Michel Gilbert Roland Brault
CPC分类号： F01D15/10 , F01D21/045 , F02K3/06 , F05D2220/323 , F05D2220/36 , F05D2220/76 , F05D2260/311 , F05D2270/09
摘要： A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.
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2.发明授权公开(公告)号：US10351252B2
公开(公告)日：2019-07-16
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： B64D35/06 , B64D27/14 , B64C11/48 , F02K3/072 , F02C7/36 , B64D33/02 , B64D35/08 , 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), characterized 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：US11015521B2
公开(公告)日：2021-05-25
申请号：US15765404
申请日：2016-10-05
发明人： Augustin Marc Michel Curlier , Adrien Pierre Jean Pertat , Pierre-Alain Jean Philippe Reigner , Laurent Soulat , Kevin Morgane Lemarchand , Tewfik Boudebiza , Gilles Alain Charier , Nathalie Nowakowski
IPC分类号： F02C3/10 , B64D27/12 , B64D35/04 , F02K3/062 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , B64D27/18 , B64D27/26
摘要： An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.
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公开(公告)号：US11225317B2
公开(公告)日：2022-01-18
申请号：US15573163
申请日：2016-04-29
发明人： Tewfik Boudebiza , Olivier Belmonte , Gilles Alain Marie Charier , Emmanuel Pierre Dimitri Patsouris , Pierre-Alain Jean Philippe Reigner
摘要： A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.
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公开(公告)号：US11174781B2
公开(公告)日：2021-11-16
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
IPC分类号： F02C3/10 , B64D27/12 , B64D35/04 , F02K3/062 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , B64D27/18 , B64D27/26
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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