• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Aircraft propulsion unit, comprising a motor and a nacelle comprising a casing (16) of revolution delimiting a flow vein of an air flow, characterized in that this casing comprises at least two openings closed by panels ( 18) removable and interchangeable, at least one of these panels carrying equipment (24) of the propulsion system.
    公开号:FR3015569A1
    申请号:FR1362957
    申请日:2013-12-19
    公开日:2015-06-26
    发明作者:Jeremy Edmond Fert；Julien Pavillet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to a revolution housing for an aircraft propulsion unit, as well as to an aircraft propulsion unit comprising such a housing. STATE OF THE ART A propulsion unit for an aircraft comprises a nacelle and a motor of the turbomachine type, the nacelle comprising a housing of revolution delimiting an annular flow vein of an air flow called secondary flow in the case of a turbomachine with a double flow. The nacelle defines around the casing an annular space. Some equipment of the turbomachine are mounted in the nacelle, that is to say in the aforementioned space, and can be fixed on its housing. The outer wall of the nacelle may comprise removable covers to allow access to these equipment during a maintenance operation. An aircraft is generally equipped with at least two lateral propulsion units, that is to say two propulsion units which are located on the sides of the fuselage of the aircraft and are attached to this fuselage or to the wings via of pylons. Aircraft manufacturers may require that certain equipment of a propulsion system be located on the fuselage side of the aircraft. This is for example the case when this equipment includes an apparent portion on the outer wall of the nacelle. Aircraft manufacturers may indeed prefer that this apparent part is located on the side of the fuselage to make it less visible and thus improve the aesthetics of the propulsion system. When this is the case, the position of the equipment on the casing of one of the propulsion units of the aircraft is different from that of the equipment on the casing of the other propulsion unit, which results in propulsion units having different housings. Indeed, in the present art, the casing of a propulsion unit is such that it comprises a predefined area of implantation of the equipment and that it is not possible to use this same casing for a propulsion unit in which this equipment would not have the same position. In the current technique, to avoid being confronted with this problem, we adopt a solution that bypasses this problem. The present invention provides in particular a simple, effective and economical solution to this problem. DESCRIPTION OF THE INVENTION The invention proposes a propulsion unit for an aircraft, comprising a motor and a nacelle comprising a housing of revolution delimiting a flow vein of an air flow, characterized in that this housing comprises 10 at at least two openings closed by removable and interchangeable panels, at least one of these panels carrying at least one equipment of the propulsion unit. The present invention is particularly advantageous because, unlike the prior art, the nacelle casing is designed to accommodate equipment in a position selected from several possible positions. These positions are defined by the openings of the housing which are at least two in number. The equipment panel can close any of these openings. The equipment can thus be mounted at one or the other of the openings of the housing according to the desired position, for example by an aircraft manufacturer. The lateral propulsion units of the same aircraft can therefore be equipped with identical housings, only the positions of the panels of the housings can be different. The interest of removable panels with equipment is certain when this equipment has a size that it requires a bulge in the housing and that the same equipment must be positioned at several possible locations depending on configurations. This makes it possible to have a bulge in the vein only at the level where the equipment is installed and to faithfully reconstruct the vein via panels without equipment (trap doors) on the positions where the equipment is not installed. In addition, it can sometimes facilitate the assembly / disassembly if the assembly / disassembly of the panel is simpler than that of the equipment or it supports. The openings of the housing can be located substantially in the same transverse plane. They may be offset from each other by a predetermined angle with respect to the longitudinal axis of the housing. The openings may be located in crankcase recesses. At least one of the panels may define a housing recess of the equipment. This recess can facilitate the integration of the equipment in the nacelle particularly when it is bulky. In a particular embodiment of the invention, the equipment is a heat exchanger of the pre-cooler type for the air supply of the aircraft. In an aircraft, it is necessary to have hot air available in order to perform certain functions, such as the air conditioning of the cockpit and the passenger cabin or the defrosting of some passengers. parts of the aircraft. This hot air comes from the propulsion units of the aircraft and must undergo a significant cooling before use. To do this, at least one heat exchanger, generally called a pre-cooler (of the English precooler), is provided in which hot air taken from the engine of a propulsion unit is cooled by more air. cold taken in the secondary vein or blower of this propulsion unit. In the current technique, this exchanger is mounted in the connecting pylon of the propulsion unit to the aircraft. This exchanger comprises a first air circuit whose input is connected by a pipe to hot air sampling means on the engine and the outlet is connected to air conditioning means of the aircraft. The exchanger comprises a second air circuit which is supplied with air taken from the fan duct of the propulsion unit, this air then being discharged to the outside after heat exchange with the air of the primary circuit, in order to of its cooling. The exchanger may comprise an air intake scoop in said air flow, which is fixed to one of the aforementioned panels of the housing.
    [0002] This scoop may be partially embedded in the housing or panel and include or not a protruding portion on the inner surface of the housing or panel. The present invention also relates to a revolution housing for a propulsion assembly as described above, characterized in that it comprises two identical openings configured to be closed by removable and interchangeable panels. The housing may have a non-axi-symmetrical shape and have, substantially in the same transverse plane, two recesses at which are respectively said openings. The present invention further relates to a heat exchanger of the pre-cooler type for a propulsion assembly as described above, characterized in that it is integral with a removable panel configured to close an opening of a housing of revolution of nacelle. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIGS. 1 and 2 are diagrammatic perspective views of two aircraft propulsion assemblies; FIG. 3 is a diagrammatic perspective view of a nacelle casing of a propulsion unit according to the invention; FIG. a schematic sectional view along the line IV-IV of Figure 3, the housing having two bulges in the vein, - Figure 5 is a schematic perspective view of a pre-cooler type heat exchanger, equipped with its air intake scoop and its exhaust nozzle for the cooling flow, - Figure 6 is a schematic axial sectional view of the exchanger of Figure 5, - Figures 7 and 8 are schematic views. in persp Another feature of the invention is a nacelle housing according to the invention, with Figure 7 showing the equipment group supported by a removable panel and interchangeable with another panel and Figure 8 showing the same view without the equipment group where the a panel with a bulge is seen and the neighboring panel does not have one, and - Figure 9 is a diagrammatic view in axial section of a heat exchanger. DETAILED DESCRIPTION Reference is first made to FIGS. 1 and 2, which represent two propulsion assemblies 10, 12 according to the invention that can equip one and the same aircraft, each of these propulsion units being fixed by means of a pylon (no shown) to a wing or a side of the fuselage of the aircraft.
    [0003] These propulsion units 10, 12 are here of the double flow type. They each comprise a motor (not visible) surrounded by a nacelle 14, the motor defining a first annular flow stream of a primary flow and a second flow path of a secondary flow. The engine typically comprises from upstream to downstream, in the direction of flow flow, a blower, at least one compression module, a combustion chamber, at least one turbine module, and a gas ejection nozzle. of combustion. The nacelle 14 comprises an outer wall which is visible in FIGS. 1 and 2, this external wall surrounding a casing 16 of revolution, which is visible in FIGS. 3 and 4. Equipment is mounted in the annular space delimited by the outer wall. and the casing 16 of the nacelle 14.
    [0004] The invention allows the propulsion units 10, 12 to be equipped with identical housings 16, which was not possible in the prior art, particularly when two identical equipment have different positions on the propulsion units of the aircraft.
    [0005] For this, the housing 16 comprises at least two through radial openings which are closed by panels 18 removable and interchangeable (Figure 3). The panels 18 are removable which means that they can be disassembled and removed from the housing 16 for example during a maintenance operation. They are also interchangeable which means that each opening can be closed by one or other of the panels 18 whose shapes and dimensions are substantially identical and correspond substantially to those of the openings of the housing. In the example shown, the panels 18 close openings of substantially rectangular shape. These openings are located at a distance from the upstream and downstream ends of the housing 16 and comprise an upstream peripheral edge, a downstream peripheral edge and two lateral peripheral edges. The openings of the casing 16 are situated substantially in the same transverse plane, that is to say that their upstream peripheral edges are situated on the same circumference and that their downstream peripheral edges are situated on another same circumference, these circumferences being centered on the longitudinal axis A of the housing 16. The openings are here angularly offset from each other by an angle α of about 70-100 °, in a plane perpendicular to the axis A. In the example shown, the openings are positioned symmetrically with respect to the plane P (see FIG. 4). In the example shown, the casing 16 has a non-axisymmetrical shape and comprises two recesses 20 at its openings (FIG. 3). These recesses 20 induce local decreases in the radial dimension of the flow stream 22 of the secondary flow of the propulsion unit. The housing 16 is further thinned at these recesses 20. The housing 16 is preferably made of composite material, from a mold of appropriate shape. It is therefore sufficient to adapt the die of the mold to achieve this type of non-axi-symmetric housing (with local deformations). Alternatively, the housing may be metallic. One of the panels 18 is connected to an equipment of the propulsion unit. In the example shown, this equipment is a heat exchanger 24 of the pre-cooler type (precooler).
    [0006] As explained in the foregoing, hot air taken from the engine is cooled by means of this type of exchanger and feeds the aircraft to perform certain functions, such as air conditioning cockpits and passengers or the deicing of certain organs of the aircraft.
    [0007] The exchanger 24, better visible in Figures 5 and 6, comprises two circuits, respectively primary and secondary. The primary circuit, also called hot circuit, has its input connected by at least one pipe 26 to hot air sampling means on the engine (for example in the compression module), the output of this primary circuit being connected by at least one other pipe 28 to hot air supply means of the aircraft. The secondary circuit, also called cold circuit, has its input connected to means for withdrawing air from the secondary flow of the propulsion unit, the outlet of this circuit being connected to means for evacuating the air at the outside the propulsion unit. In the example shown, the exchanger 24 essentially comprises six elements: a scoop 30 forming said means for withdrawing air from the secondary flow, a valve 32 for regulating the flow of air flowing in the secondary circuit, a heat exchange block 34 comprising for example bricks defining said primary and secondary circuits, a nozzle 36 forming the air evacuation means of the secondary circuit, and respectively air inlet 38 and outlet collectors 40 of the primary circuit. The flow direction can be reversed in the pre-cooler depending on the position on the propulsion unit. Thus the air inlet 38 can become an air outlet and vice versa for the air outlet 40. The scoop 30 is fixed here by bolting via the flange 44 secured directly to the removable panel 18. It comprises an inlet 42 or mouth which is surrounded by a peripheral collar 44 applied and fixed on the outer surface of the casing 16. In the example shown, this inlet 42 of the scoop 30 communicates with an orifice of the panel 18 and opens predominantly radially (and preferably at an angle so as to facilitate entry of the flow into the scoop) inward into the flow vein 22 of the secondary flow (Figure 3). The outlet 46 of the scoop 30 is oriented substantially axially downstream.
    [0008] The valve 32 is mounted directly downstream of the scoop 30. It is for example a valve with valves, the valve having two valves movable in rotation about transverse axes from a closed position of the cross-section. passage of the valve to a release position of this passage section, the valve is controlled by a cylinder and a rod system not shown. The heat exchange block 34 may be of the type used in the prior art for this application. The nozzle 36 is mounted directly at the output of the secondary circuit of the block 34, its inlet 48 opening predominantly axially upstream and its outlet 50 being oriented substantially radially outwardly. As can be seen in FIG. 5, the peripheral edge of the nozzle 36, defining the outlet 50, can be equipped with a seal 54 intended to bear radially on the inner surface of the outer wall of the nacelle 14. The outlet 50 of the nozzle may also be covered with an exhaust grille 52 (FIGS. 1 and 2). This grid 52 can be carried by a removable cover of the outer wall of the nacelle 14.
    [0009] The six aforementioned elements of the exchanger 24 form here a one-piece assembly. In the example shown, the block 34 has a parallelepipedal shape and comprises two opposite sides (downstream and upstream) respectively connected to the nozzle 36 and the valve 32, and two other opposite sides respectively connected to the collectors 38, 40. The dimension of the block 34, between the manifolds 38, 40, defines the hot pass length of the primary circuit, and the size of the block 34, between the valve 32 and the nozzle 36, defines the cold pass length of the secondary circuit. As explained above, the propulsion units 10, 12 located on either side of the fuselage of an aircraft have identical housings 16. In FIG. 3, the exchanger 24 has its scoop 30 which is fixed to one of the panels 18 of the casing 16 so that the propulsion assembly equipped with this casing has the configuration shown in FIG. 1. When the exchanger 24 and its panel 18 are mounted at the other opening of the housing 16 of Figure 3, the propulsion assembly equipped with this housing has the configuration shown in Figure 2. The plane P shown in Figures 1 and 2 is a vertical plane which goes through an arm 12h (for 12 hours, by analogy with the dial of a clock - referenced 60 in Figure 4) of the propulsion system. The openings and the panels 18 are situated on either side of this plane P, which means that the exchanger 24 can be mounted on either side of this plane, that is to say on the right or on the left side of the propulsion unit. This makes it possible to mount the exchanger 24 of a propulsion unit on the fuselage side of the aircraft so that its exhaust grille 52 (FIGS. 1 and 2) is located on the fuselage side and is therefore not visible. when the aircraft is viewed from the side in particular. Figures 7 to 9 show an alternative embodiment of the invention in which the exchanger 124 is partially embedded in the casing 116 of the engine.
    [0010] The exchanger 124 comprises the same elements as the exchanger 24 described in the foregoing, namely a scoop 130, a valve 132, a heat exchange block 134, a nozzle 136 and collectors 138, 140. In the example shown, portions of the scoop 124 and the block 134 of the exchanger 124 are embedded in the casing 116 and project radially inside the casing 116. These protruding parts are therefore located in the duct 122. flow of the secondary flow of the propulsion unit. The inlet 142 of the scoop 126 opens predominantly axially upstream. The outlet of the nozzle 136 is here equipped with an exhaust grille 152. In this variant, although the openings of the casing 116 are substantially identical, the panels 118, 118 'for closing these openings are different. The panel 118 faithfully reproduces the general shape of the housing 116 while the panel 118 ', which carries the exchanger 124, defines a recess 120 of the aforementioned type. This is particularly advantageous because it simplifies the shape and therefore the realization of the housing which no longer includes recesses. These are the panels that define the recesses. Advantageously, a single panel (that intended to be equipped with equipment) forms a recess. The assembly comprising the casing removable panels thus defines a single recess in the vein, which limits the aerodynamic impact. The panels 118, 118 'have a substantially ovoid shape. The shape of the panels naturally depends on that of the equipment to be installed. The peripheral edge of the panel 118 is sealingly attached to the peripheral edge of an opening of the casing and the peripheral edge of the panel 118 'is attached sealingly to the peripheral edge of the other opening of the casing except at its part d. upstream end. Indeed, the peripheral edge 162 of the upstream end portion of the panel 118 'is offset radially inwardly relative to the peripheral edge 164 corresponding to the opening, and defines therewith an orifice 165 for communicating with the inlet 142 of the scoop 130 of the exchanger 124.
    [0011] As in the aforementioned case, the panel 118 equipped with the exchanger 124 can be used to seal (here partially) one or the other of the openings of the housing 116. In the example shown, the openings of the housing 116 are located on either side of an orifice 166 of the housing 116 for mounting the arm 12h above. Exchanger 124 can thus be positioned on one side or the other of this arm, as in the aforementioned case. The housing 116 may be made of metal alloy, and be obtained from foundry. The operation of the heat exchanger 24, 124 is identical to those of the prior art, for the air supply of an aircraft. The invention makes it possible in particular not to provide fixing systems (flanges, bosses, copings, etc.) for each possible position of the equipment or even bulge in the vein in the case of a very bulky equipment, such as c is the case in the concrete case that led to the invention. Thus, the invention simplifies and reduces the casing and limits the aerodynamic losses in the case of a bulge in the vein due to the size of the equipment that does not fit into the annular space between the housing and the nacelle.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Aircraft propulsion unit (10, 12) comprising a motor and a nacelle (14) comprising a housing (16) of revolution delimiting a vein (22) for the flow of an air flow, characterized in that housing has at least two openings closed by panels (18) removable and interchangeable, at least one of these panels carrying at least one equipment (24) of the propulsion unit.
    [0002]
    2. Propulsion unit according to claim 1, characterized in that the openings are located substantially in the same transverse plane and are offset from each other by a predetermined angle (a) with respect to the longitudinal axis (A). ) of the housing.
    [0003]
    3. Propulsion unit according to claim 1 or 2, characterized in that the openings are located in recesses (20) of the housing (16).
    [0004]
    4. Propulsion unit according to claim 1 or 2, characterized in that at least one of the panels (118) defines a recess (120) housing the equipment (124).
    [0005]
    5. Propulsion unit according to one of the preceding claims, characterized in that the equipment is a heat exchanger (24) of the pre-cooler type for the air supply of the aircraft.
    [0006]
    6. Propulsion unit according to claim 5, characterized in that the exchanger (24) comprises a scoop (30) for taking air in said air flow, which is fixed to one of the panels (18).
    [0007]
    7. Propulsion unit according to claim 6, characterized in that the scoop (30) is partially embedded in the housing (16) or the panel (18) and comprises a projecting portion on the inner surface of the housing or panel.
    [0008]
    8. Housing (16) of revolution for a propulsion unit (10, 12) according to one of the preceding claims, characterized in that it comprisestwo identical openings configured to be closed by panels (18) removable and interchangeable.
    [0009]
    9. Carter according to claim 8, characterized in that it has a non-axi-symmetrical shape and has, substantially in the same transverse plane, two recesses (20) at which are respectively said openings.
    [0010]
    10. Heat exchanger (24) of the pre-cooler type for a propulsion unit (10, 12) according to one of claims 1 to 7, characterized in that it is integral with a panel (18) removable configured for closing an opening of a casing (16) of nacelle revolution.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3015569A1|2015-06-26|CARTER FOR A PROPULSIVE ASSEMBLY
    CA2933353A1|2015-06-25|Aircraft turbomachine comprising a heat exchanger of the precooler type
    EP1907281B1|2018-03-07|Propulsion unit for aircraft and aircraft comprising at least one such propulsion unit
    CA2602141C|2014-09-02|Integrated propellant system that includes a by-pass engine
    EP0743435A1|1996-11-20|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
    CA2602176A1|2008-03-20|Propellant system with integrated pylon for aircraft
    FR3001199A1|2014-07-25|MOTOR COVER INCORPORATING AN EQUIPMENT VENTILATION CIRCUIT
    CA2637647A1|2009-01-26|External wall of a fan conduit in a turbine engine
    FR2961251A1|2011-12-16|Hub for use in intermediate casing of e.g. ducted-fan turbine engine of aircraft, has flange including air outlet orifices formed downstream from bleed valves, and deflectors permitting guiding of air between inlet and outlet orifices
    FR3020412B1|2019-08-23|LONGITUDINAL CONTRAFIC ASSEMBLY INCLUDING RECESSED LONGITUDINAL COUNTERFEIT FITTING
    WO2013190246A1|2013-12-27|Gas turbine engine comprising an exhaust cone attached to the exhaust casing
    EP3833861A1|2021-06-16|Exhaust cone with flexible attachment
    FR3043723A1|2017-05-19|PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING A GAS GENERATOR, TWO DEPTH BLOWERS AND AN AIR INLET HANDLE
    EP2234886A1|2010-10-06|Nacelle for turbojet engine
    FR3028289A1|2016-05-13|AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE HOUSING WITH A VARIABLE AERODYNAMIC PROFILE
    WO2015028756A1|2015-03-05|Two-part auxiliary arm for a turbofan nacelle
    FR3046200A1|2017-06-30|TURBOMACHINE COMPRISING AN OIL TANK AND AN AIR-OIL EXCHANGER
    FR2992018A1|2013-12-20|Casing for e.g. turbojet engine, of aircraft, has annular combustion chamber delimited by internal and external platforms that are made of metal and formed from single piece with walls of chamber, where platforms are welded onto walls
    FR2933128A1|2010-01-01|DEVICE FOR COLLECTING AIR IN A TURBOMACHINE
    FR3030627A1|2016-06-24|SERVITUDE PASSAGE SYSTEM FOR TURBOMACHINE
    WO2013068671A1|2013-05-16|Composite panel having a built-in sampling scoop
    FR2976616A1|2012-12-21|Ventilation system for hollow blade of turbine nozzle for e.g. turbojet engine for airplane, has tubular sleeve, air intake casing and plate that are assembled with each other to form single-piece component before assembling in blade
    CA2933353C|2022-03-01|Aircraft turbomachine comprising a heat exchanger of the precooler type
    WO2018002560A1|2018-01-04|Arrangement for the attachment of a connecting rod of a thrust reversal flap to a fixed internal structure of a jet engine nacelle and associated method for assembly/disassembly
    FR3055656A1|2018-03-09|TURBINE FOR A TURBOMACHINE, SUCH AS A TURBOREACTOR
    同族专利:
    公开号 | 公开日
    FR3015569B1|2019-01-25|
    US20150175269A1|2015-06-25|
    CA2875044A1|2015-06-19|
    US9981751B2|2018-05-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1568868A2|2004-02-05|2005-08-31|Snecma Moteurs|High by-pass ratio turbofan|
    EP1795708A2|2005-12-08|2007-06-13|General Electric Company|Shrouded turbofan bleed duct|
    EP1898069A2|2006-08-29|2008-03-12|Pratt & Whitney Canada Corp.|Turbofan bypass duct air cooled fluid cooler installation|
    EP1902952A1|2006-09-20|2008-03-26|Snecma|Fan conduit for a turbomachine|
    EP2128023A1|2008-05-29|2009-12-02|Pratt & Whitney Canada Corp.|Bleed air cooler assembly for a gas turbine engine, corresponding kit and installation method|WO2019229337A1|2018-05-30|2019-12-05|Safran Aircraft Engines|Outlet of a hot-gas pipe of an aircraft engine passing through an engine wall|
    WO2020043977A1|2018-08-30|2020-03-05|Safran Aircraft Engines|Outlet for ejecting a hot gas through an aircraft engine wall|
    FR3087840A1|2018-10-29|2020-05-01|Safran Aircraft Engines|NACELLE HOOD FOR POWERED AIRCRAFT ASSEMBLY|
    FR3097898A1|2019-06-26|2021-01-01|Safran Aircraft Engines|DISCHARGE OF A VEIN FROM A PROPELLENT ASSEMBLY TO REDUCE THE BLOWER BEAT OF A BLOWER|FR2865001B1|2004-01-12|2008-05-09|Snecma Moteurs|TURBOREACTOR COMPRISING A SERVITUDE CONNECTING ARM AND THE SERVITUDE CONNECTING ARM.|
    FR2880920B1|2005-01-20|2007-07-06|Snecma Moteurs Sa|DOUBLE-BODY TURBOMOTEUR WITH DRIVING MEANS FOR THE ACCESSORIES HOUSING|
    FR2891313A1|2005-09-26|2007-03-30|Airbus France Sas|DOUBLE FLOW TURBOMOTEUR HAVING A PRE-COOLER|
    FR2902830B1|2006-06-27|2008-08-08|Airbus France Sas|TURBOREACTOR FOR AIRCRAFT|
    US8714923B2|2007-03-23|2014-05-06|Ogin, Inc.|Fluid turbine|
    DE102009011635A1|2009-03-04|2010-09-09|Rolls-Royce Deutschland Ltd & Co Kg|Air guide element of a running gap adjustment system of an aircraft gas turbine|
    FR2948636B1|2009-07-31|2012-01-13|Airbus Operations Sas|AIRCRAFT ENGINE ASSEMBLY INCLUDING A STRUCTURAL ENVELOPE FOR THE INTERNAL RADIAL DELIMITATION OF THE SECONDARY FLOW|
    US8529195B2|2010-10-12|2013-09-10|General Electric Company|Inducer for gas turbine system|
    US9267390B2|2012-03-22|2016-02-23|Honeywell International Inc.|Bi-metallic actuator for selectively controlling air flow between plena in a gas turbine engine|
    EP3084183B1|2013-12-18|2019-07-10|United Technologies Corporation|Heat exchanger flow control assembly and corresponding method|US10072584B2|2013-12-03|2018-09-11|United Technologies Corporation|Multi-bypass stream gas turbine engine with enlarged bypass flow area|
    US10125684B2|2015-12-29|2018-11-13|Pratt & Whitney Canada Corp.|Surface cooler for aero engine|
    US11090600B2|2017-01-04|2021-08-17|General Electric Company|Particle separator assembly for a turbine engine|
    FR3078947B1|2018-03-13|2020-03-13|Airbus Operations|AIRCRAFT PROPULSION SYSTEM COMPRISING A DUAL-FLOW TURBOREACTOR AND A REDUCED AIR TAKE-OFF SYSTEM|
    法律状态:
    2015-12-01| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 6 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362957|2013-12-19|
    FR1362957A|FR3015569B1|2013-12-19|2013-12-19|CARTER FOR A PROPULSIVE ASSEMBLY|FR1362957A| FR3015569B1|2013-12-19|2013-12-19|CARTER FOR A PROPULSIVE ASSEMBLY|
    CA2875044A| CA2875044A1|2013-12-19|2014-12-11|Casing for a propulsion assembly|
    US14/576,694| US9981751B2|2013-12-19|2014-12-19|Casing for a propulsion unit|
    [返回顶部]