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1.发明授权公开(公告)号：US10584641B2
公开(公告)日：2020-03-10
申请号：US15566861
申请日：2016-04-14
发明人： Didier Rene Andre Escure , Jean-Francois Endy Bersot , Tewfik Boudebiza , Gilles Alain Charier , Thomas Julien Nguyen Van , Jean Philippe Pierre-Alain Reigner
摘要： Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).
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公开(公告)号：US20170240286A1
公开(公告)日：2017-08-24
申请号：US15284895
申请日：2016-10-04
CPC分类号： B64D27/18 , B64C3/182 , B64C3/32 , B64C11/001 , B64D27/12 , B64D27/26 , B64D35/02 , B64D35/04 , B64D2027/266 , F02K1/54 , F02K3/077 , Y02T50/671
摘要： An aircraft includes a wing having a first upstream longeron and a second downstream longeron extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream longeron via at least one first and second fastener.
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公开(公告)号：US10174634B2
公开(公告)日：2019-01-08
申请号：US15320702
申请日：2015-06-15
摘要： A device for lubricating a turbomachine rolling bearing includes a rolling bearing mounted between an internal component and an external component. The bearing has rolling elements mounted between an outer ring secured to the external component and an inner ring secured to the internal component. The internal component includes at least one first duct for the passage of oil for supplying the internal ring of the bearing with oil, wherein the internal component is a stator component and at least one first duct is connected to an oil supply source configured to deliver the oil at a pressure high enough that this oil can be conveyed as far as the rolling elements of the bearing.
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4.发明申请公开(公告)号：US20180283272A1
公开(公告)日：2018-10-04
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
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：US11371432B2
公开(公告)日：2022-06-28
申请号：US16488858
申请日：2018-02-28
摘要： A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-balance appears. Because it is positioned a long way from the bearing, the decoupler (15) can be designed with a greater degree of freedom at a location where there is more space available and where layout constraints are less of an issue. More specifically, it is housed in a cavity (30) of the external casing (13) which opens onto the flow path (5).
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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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公开(公告)号：US10557415B2
公开(公告)日：2020-02-11
申请号：US15088525
申请日：2016-04-01
发明人： Tewfik Boudebiza , Gilles Alain Charier , Augustin Marc Michel Curlier , Jean-Christophe Duffet
摘要： A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.
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公开(公告)号：US10077113B2
公开(公告)日：2018-09-18
申请号：US14162096
申请日：2014-01-23
CPC分类号： B64D13/006 , B64D29/00 , B64D33/08 , F01D25/14 , F02C7/12 , Y02T50/671 , Y02T50/675
摘要： An aircraft propulsion engine including a fan case, and a cowl forming part of the nacelle of the engine and being designed to at least partially surround the case leaving a space between the cowl and the case, in which space at least one piece of equipment is mounted and extends along the axis of the engine, is provided. The cowl includes a wall and wall stiffeners fixed to the internal face of the wall. At least a part of the stiffeners of the cowl is arranged to form air guide ducts, the air guide ducts being assembled into an air distribution circuit to ventilate the equipment.
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