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1. 发明授权

US11149685B2 Modified acoustic secondary nozzle 有权
公开(公告)号：US11149685B2
公开(公告)日：2021-10-19
申请号：US16640198
申请日：2018-08-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Jérémy Paul Francisco Gonzalez , Guillaume Bodard , Norman Bruno André Jodet , Jacky Novi Mardjono
IPC分类号： F02K1/46 , F02K3/04
摘要： An assembly for the rear of a bypass turbomachine (10) comprises a primary nozzle (11) comprising a trailing edge defining a primary flow path portion and a secondary nozzle (110) defining a secondary flow path portion, defined about a longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary flow path (Vs) and from a primary flow path (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent shape with a throat (112) corresponding to a minimum cross section of the nozzle (110), the secondary nozzle (110) comprising, at the throat (112), a periodic succession of lobes (116, 118) which are situated along the internal circumference of the secondary nozzle (110). The assembly also comprises a lobed mixer (130) at the downstream end of the primary nozzle (11), this having an alternation of hot lobes (134) extending inside the secondary flow path and of cold lobes (132) extending inside the primary flow path. The lobes of the nozzle (110) which are concave (118), which is to say radially towards the outside, and respectively which are convex (116), which is to say radically towards the inside, if the longitudinal offset is disregarded, radically face the respectively hot lobes (134) and cold lobes (132) of the mixer (130).

2. 发明授权

US11572832B2 Method for preparing a support and for acoustic management on a turbine engine or a nacelle 有权
公开(公告)号：US11572832B2
公开(公告)日：2023-02-07
申请号：US17278557
申请日：2019-09-20
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Norman Bruno André Jodet , Jean-Michel Daniel Paul Boiteux , Francis Couillard , Jérémy Paul Francisco Gonzalez , Stéphane Orcel
IPC分类号： F02C7/045 , B64D33/02
摘要： The invention relates to acoustic management, on an aircraft turbomachine (3,12) or on a nacelle (1,10), via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess (34), mounting it removably with respect to the support, the panel being an acoustic panel or a non-acoustic panel.

3. 发明授权

US11560842B2 Acoustic panel and associated propulsion unit 有权
公开(公告)号：US11560842B2
公开(公告)日：2023-01-24
申请号：US16633249
申请日：2018-07-25
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Georges Jean Xavier Riou , Norman Bruno André Jodet , Jéremy Paul Francisco Gonzalez
IPC分类号： F02C7/045 , B32B3/12 , B32B3/26 , B64D33/02 , G10K11/168 , G10K11/172
摘要： An acoustic panel for an aircraft propulsion unit, comprises a core and an entry layer in contact with the core, the entry layer comprising lower elements and upper elements, each comprising an inner face, an outer face and at least one through-hole, the inner faces of the lower elements and upper elements being in contact with each other and forming a channel defining a baffle and opening into a cell of the core.

4. 发明授权

US11248530B2 Acoustic treatment panel for a turbojet engine 有权
公开(公告)号：US11248530B2
公开(公告)日：2022-02-15
申请号：US17046566
申请日：2019-04-09
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Jéremy Paul Francisco Gonzalez , Norman Bruno André Jodet , Georges Jean Xavier Riou
IPC分类号： F02C7/24 , G10K11/16
摘要： An acoustic treatment panel intended to be disposed on at least one wall of a turbojet engine in contact with a fluid flow, the panel including a first acoustically reflective plate, a second plate and a plurality of cavities mounted between the first plate and the second plate and including a plurality of cells. The second plate is a one-piece plate through which a plurality of channels pass, each opening out on the one hand onto a first orifice formed on a first face of the second plate and on the other hand onto a second orifice formed on a second face of the second plate, the length of each channel extending between its first orifice and its second orifice being greater than the thickness of the second plate.

5. 发明授权

US11047303B2 Supply duct of a compressor of a turbine engine 有权
公开(公告)号：US11047303B2
公开(公告)日：2021-06-29
申请号：US16042195
申请日：2018-07-23
申请人： Safran Aircraft Engines
发明人： Jacky Novi Mardjono , Norman Bruno André Jodet
IPC分类号： F02C7/045 , F01D1/02 , F01D9/06 , F04D29/54 , F04D19/02 , F02K3/06
摘要： A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.

6. 发明授权

US11377958B2 Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane and turbomachine equipped with said vane or said assembly 有权
公开(公告)号：US11377958B2
公开(公告)日：2022-07-05
申请号：US16642150
申请日：2018-08-28
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Kevin Morgane Lemarchand , Norman Bruno André Jodet , Guillaume Martin , Laurent Soulat
IPC分类号： F01D5/14 , F01D9/04
摘要： A flow-straightener vane of a bypass turbomachine includes a plurality of vane sections stacked radially with respect to a longitudinal axis (X) along a stacking line (L) between a root end and a tip end. Each vane section has a pressure-face surface and a suction-face surface extending axially between an upstream leading edge and a downstream trailing edge. Between the leading and trailing edges of each vane section there is formed a profile chord (CA) the length of which is substantially constant between the tip end and the root end, and the stacking line (L) exhibits a curvature in a plane passing more or less through the axis (X) and through the stacking line (L), situated in the vicinity of the tip end and oriented from downstream towards upstream.

7. 发明授权

US11472565B2 Turbomachine nacelle having acoustically porous walls 有权
公开(公告)号：US11472565B2
公开(公告)日：2022-10-18
申请号：US16970206
申请日：2019-02-19
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Norman Bruno André Jodet , Jérémy Paul Francisco Gonzalez
IPC分类号： B64D33/02 , F02C7/045 , B64D29/06 , F02K3/06
摘要： A nacelle for a turbomachine is provided and includes an inner wall that is annular about a longitudinal axis of the nacelle, the annular inner wall being designed to surround part of the turbomachine. The nacelle further includes an annular outer wall surrounding the annular inner wall. The annular outer wall includes a first acoustically porous part, and the annular inner wall including a second acoustically porous part. The first and second porous parts are arranged facing one another so as to allow soundwaves, emitted by the turbomachine housed in the nacelle, to pass through the annular inner wall and then the annular outer wall so as to escape from the nacelle.

8. 发明授权

US10787962B2 Active system generating destructive acoustic interference for an aircraft engine with multiple fan spools 有权
公开(公告)号：US10787962B2
公开(公告)日：2020-09-29
申请号：US16050039
申请日：2018-07-31
申请人： Safran Aircraft Engines
发明人： Jean Michel Roux , Norman Bruno André Jodet , Laurent Louis Robert Baudoin
IPC分类号： F02K3/00 , F02C3/107 , F02C7/045 , B64D29/00 , G10K11/16 , B64D33/02 , F02K3/06 , B64D27/10
摘要： An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.

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