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1.发明申请公开(公告)号：US20220186682A1
公开(公告)日：2022-06-16
申请号：US17600071
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Jean-Loïc Hervé Lecordix , Nicolas Joseph Sirvin , Frédéric Dautreppe , Anthony Binder , Eva Julie Lebeault
IPC分类号： F02K1/62
摘要： An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.
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2.发明授权公开(公告)号：US11933246B2
公开(公告)日：2024-03-19
申请号：US17600071
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Jean-Loïc Hervé Lecordix , Nicolas Joseph Sirvin , Frédéric Dautreppe , Anthony Binder , Eva Julie Lebeault
IPC分类号： F02K1/62
CPC分类号： F02K1/62
摘要： An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.
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公开(公告)号：US11649765B2
公开(公告)日：2023-05-16
申请号：US17600076
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Laurent Louis Robert Baudoin , Nicolas Joseph Sirvin , Jagoda Alina Worotynska , Frédéric Dautreppe , Caroline Marie Frantz
CPC分类号： F02C7/042 , F02K1/70 , F02K1/66 , F05D2220/323 , F05D2300/501
摘要： Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.
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4.发明公开公开(公告)号：US20240229721A9
公开(公告)日：2024-07-11
申请号：US18546903
申请日：2022-02-24
发明人： Frédéric Dautreppe
摘要： An accessory gearbox for an aircraft turbine engine having a radial shaft connecting a high-pressure body of the turbine engine to a gear train having at least one mixed shaft coupled to a high-speed device. The accessory gearbox has a clutch system having a low-speed motor mounted thereon and configured to mate with the mixed shaft such that: in an engaged position of the clutch, the low-speed motor is coupled to the mixed shaft so as to drive the high-pressure body at low speed when the turbine engine is stationary and, in a disengaged position of the clutch, the low-speed motor is decoupled from the mixed shaft so as to be protected when the turbine engine is in operation.
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公开(公告)号：US11815027B2
公开(公告)日：2023-11-14
申请号：US17595809
申请日：2020-05-12
发明人： Romain Harold Patrice Pou , Frédéric Dautreppe , Bertrand Romain Adrien Dufour , Frédéric Jacques Eugène Goupil
IPC分类号： F02C7/25
CPC分类号： F02C7/25 , F05D2230/70
摘要： The invention relates to a firewall (112) for a turbomachine (100) auxiliary arm (106). This firewall (112), which has one or more through openings (180) in a thickness direction (Z) of the firewall (112), comprises a fixed portion (120) and a first removable portion (130) extending, in a width direction (Y), orthogonal to said thickness direction (Z), from at least one adjacent opening among the through openings (180), to a first outer edge (190) of the firewall (112). To open this firewall (112) in order to allow access to one or more ducts and/or electrical cables (111) received in the through openings (180), the first removable portion (130) can be dismantled.
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6.发明公开公开(公告)号：US20240133346A1
公开(公告)日：2024-04-25
申请号：US18546903
申请日：2022-02-24
发明人： Frédéric Dautreppe
摘要： An accessory gearbox for an aircraft turbine engine having a radial shaft connecting a high-pressure body of the turbine engine to a gear train having at least one mixed shaft coupled to a high-speed device. The accessory gearbox has a clutch system having a low-speed motor mounted thereon and configured to mate with the mixed shaft such that: in an engaged position of the clutch, the low-speed motor is coupled to the mixed shaft so as to drive the high-pressure body at low speed when the turbine engine is stationary and, in a disengaged position of the clutch, the low-speed motor is decoupled from the mixed shaft so as to be protected when the turbine engine is in operation.
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公开(公告)号：US11739688B2
公开(公告)日：2023-08-29
申请号：US17600550
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Mathieu Patrick Jean-Louis Lallia , Nicolas Joseph Sirvin , Jagoda Alina Worotynska , Frédéric Dautreppe
摘要： An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.
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公开(公告)号：US20220186663A1
公开(公告)日：2022-06-16
申请号：US17600076
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Laurent Louis Robert Baudoin , Nicolas Joseph Sirvin , Jagoda Alina Worotynska , Frédéric Dautreppe , Caroline Marie Frantz
摘要： Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.
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公开(公告)号：US20220170417A1
公开(公告)日：2022-06-02
申请号：US17600550
申请日：2020-04-08
发明人： Daniel-Ciprian Mincu , Mathieu Patrick Jean-Louis Lallia , Nicolas Joseph Sirvin , Jagoda Alina Worotynska , Frédéric Dautreppe
摘要： An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.
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