-
公开(公告)号：US20200378339A9
公开(公告)日：2020-12-03
申请号：US16105159
申请日：2018-08-20
摘要： The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).
-
公开(公告)号：US20200376743A1
公开(公告)日：2020-12-03
申请号：US16770364
申请日：2018-12-06
发明人： Norman Bruno Andre JODET , Jeremy Paul Francisco GONZALEZ , Jacky Novi MARDJONO , Arnaud DUBOURG , Edith-Roland FOTSING , Annie ROSS , Daniel THERRIAULT
IPC分类号： B29C64/118 , B33Y10/00 , B29C70/32 , B33Y30/00
摘要： A method of a coating by additive manufacturing on a turbomachine casing, including depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments forming an ordered array of channels. A filamentary material deposition system is positioned at a predetermined position and distance from the internal surface of the casing; a first layer of the coating is deposited over 360°; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned at a predetermined position and distance from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out by a predetermined angular deviation corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system by a second predetermined angle.
-
公开(公告)号：US20200173396A1
公开(公告)日：2020-06-04
申请号：US16640198
申请日：2018-08-21
发明人： Jérémy Paul Francisco GONZALEZ , Guillaume BODARD , Norman Bruno Andre JODET , Jacky Novi MARDJONO
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).
-
公开(公告)号：US20180311859A1
公开(公告)日：2018-11-01
申请号：US15963985
申请日：2018-04-26
CPC分类号： B26F1/24 , B26F1/0038
摘要： Device for perforating an acoustic annular panel for a turbine engine, wherein it includes a perforation needle support ring, the ring having an axis A of revolution and being intended to be inserted substantially coaxially inside the panel, the ring being sectored and including ring sectors regularly distributed around the axis and each one radially mobile opposite the axis from a radially inner rest position up to a perforation position of the radially outer panel, and at least one rotating actuator of rotation axis A and mechanically connected to the ring sectors such that a rotation of the actuator leads to a radial movement of the ring sectors.
-
公开(公告)号：US20180009522A1
公开(公告)日：2018-01-11
申请号：US15547118
申请日：2016-01-27
发明人： Paul Antoine FORESTO , Anthony BINDER , Alexandre Gerard Francois COUILLEAUX , Norman Bruno Andre JODET
摘要： A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and an outlet leading to the trailing edge of the blade transversely directed in relation to the main elongation direction, such that an inner stream of air flowing in the inner air stream channel by entering via the inlet adjacent to the root of the blade is discharged via the outlet adjacent to the trailing edge of the blade by forming a stream of blown air that moves away from the trailing edge in a direction which is transverse to the main elongation direction and which has a component in the direction of a skeleton line of the blade at the trailing edge.
-
公开(公告)号：US20190078534A1
公开(公告)日：2019-03-14
申请号：US16105159
申请日：2018-08-20
摘要： The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).
-
7.发明申请公开(公告)号：US20180065727A1
公开(公告)日：2018-03-08
申请号：US15551921
申请日：2016-02-18
摘要： A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.
-
公开(公告)号：US20170283032A1
公开(公告)日：2017-10-05
申请号：US15471136
申请日：2017-03-28
摘要： An aircraft having a wing and an aeroengine having a longitudinal main axis M and including a ducted nacelle with at least one fan, the wing including an acoustic treatment surface on a bottom portion of its outer shell on either side of the main longitudinal axis M and over a width L perpendicular to the longitudinal axis M that is not greater than three times the diameter D of the fan, the acoustic treatment surface comprising a layer of porous material for attenuating acoustic waves coming from the fan.
-
公开(公告)号：US20190024586A1
公开(公告)日：2019-01-24
申请号：US16042195
申请日：2018-07-23
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.
-
公开(公告)号：US20180354634A1
公开(公告)日：2018-12-13
申请号：US15778415
申请日：2016-11-21
CPC分类号： B64D29/04 , B64C1/40 , B64C5/02 , B64D27/14 , B64D27/20 , F02C7/24 , F05D2220/323 , F05D2240/126 , G10K11/162
摘要： An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine.
-
-
-
-
-
-
-
-
-
搜索结果
11 条记录 (耗时 0.011 秒)
