• 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:
    The invention relates to a propulsion unit (10) of an aircraft, comprising a gas generator (11) and two blowers (12) rotated by the gas generator (11) and deported on both sides of the engine. a vertical plane passing through the axis of the latter. According to the invention, the propulsion assembly (10) comprises an air intake duct (20) comprising an inlet duct (21) oriented along a first axis (A1) substantially parallel and offset with respect to a longitudinal axis (X) of the gas generator, the inlet duct (21) separating into a supply duct (22) which is connected to an inlet opening (11e) of the gas generator (11) and a exhaust duct (24) configured in such a way that particles ingested by the inlet duct (21) are discharged without entering the gas generator.
    公开号:FR3043723A1
    申请号:FR1560895
    申请日:2015-11-13
    公开日:2017-05-19
    发明作者:Christian Sylvain Vessot；Bruno Albert Beutin；Philippe Gerard Chanez；Mathieu Patrick Jean-Louis Lallia
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Propulsion unit for an aircraft comprising a gas generator, two remote blowers and an air inlet sleeve 1. Field of the invention
    The present invention relates to the aeronautical field and aims a propulsion assembly comprising at least two blowers driven by a gas generator. 2. State of the art
    New propulsion assembly architectures comprising at least two remote blowers with respect to a gas generator, most often under the wings of an aircraft, have been proposed to optimize the propulsive efficiency thanks to a high dilution rate or BPR. (for the English designation "Bypass Ratio") while maintaining an acceptable ground clearance and small blowers. The dilution ratio is the ratio between the flow of secondary flow or cold flow through the blower or blowers to generate a thrust and a primary flow or hot flow through the gas generator. Such an architecture provides that the blowers and the gas generator are each arranged in casings more or less contiguous to each other. These housings extend downstream with reference to the flow of gas in the propulsion assembly and the housing of the gas generator is arranged astride the fan casings.
    Due to the remote blowers on the sides of the gas generator, and since the air inlet thereof is disposed in a space between the blowers, this air inlet is likely to ingest particles also called foreign bodies, such as sand, hail, birds, or others. Another disadvantage of this architecture lies in the fact that the space between the two fan casings is small enough to generate a sonic or even supersonic flow which generates a strong drag altering the efficiency of the propulsion assembly. 3. Objective of the invention
    The object of the present invention is to provide a propulsion assembly which makes it possible in particular to protect the gas generator from ingestion of particles while reducing the drag of the assembly. 4. Presentation of the invention
    This object is achieved according to the invention by means of a propulsion unit of an aircraft, comprising a gas generator and two blowers rotated by the gas generator and offset on either side of a vertical plane. passing through the axis of the gas generator thereof, the propulsion assembly comprising an air inlet sleeve having an inlet duct oriented along a first axis substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet duct separating into a supply duct which connects to an inlet opening of the gas generator and a discharge duct configured so that particles ingested through the duct entrance are evacuated without entering the gas generator.
    Thus, this solution achieves the aforementioned objective. In particular, this configuration of the propulsion assembly and in particular of the supply duct of the gas generator oriented along an axis offset from the inlet duct makes it possible to misalign the air inlet of the gas generator so as to protect it from particles or foreign objects that can be ingested by the air inlet sleeve. These possible ingested objects are then oriented towards the evacuation duct and evacuated. The air inlet of the gas generator is then masked and protected.
    According to a characteristic of the invention, the inlet duct has a frontal section whose downstream projection parallel to the longitudinal axis passes outside the perimeter of the inlet opening of the gas generator.
    According to a characteristic of the invention, the two blowers are contained in an aerodynamic fairing having an upper surface and a lower surface, and the front section of the inlet duct is inscribed in an air inlet opening which extends between the two blowers and between the upper surface and the lower surface of the fairing. In this way, this configuration makes it possible to fill this inter-blowing zone with strong Machs and, on the other hand, to reduce drag.
    According to another characteristic of the invention, the longitudinal axis of the gas generator passes inside the air inlet opening.
    According to another characteristic of the invention, the air inlet opening extends on either side of a plane of blowers containing the axes of rotation of the two blowers.
    In one embodiment, the air inlet opening is formed in one portion.
    According to another embodiment, the air inlet opening is formed of two parts distributed on either side of the fan plane and separated from each other by a wall.
    According to another characteristic of the invention, the air inlet opening brings air entering, on the one hand, into the inlet duct and, on the other hand, into a ventilation duct from which is taken. air to cool elements of the propulsion assembly and / or a wing of the aircraft. This ventilation duct makes it possible to ventilate the "compartment" of the gas generator and to cool certain accessories such as exchangers.
    According to another characteristic of the invention, the ventilation duct is delimited in part by a wall of the inlet duct, said wall separating the flow of air entering the ventilation duct into ventilation flows passing along the duct. an outer casing of the gas generator. In this way, each of the air intake openings is in fluid communication with the ventilation duct or the air inlet duct.
    According to another characteristic of the invention, the evacuation duct comprises an inlet section which divides downstream into two channels shaped to circumvent suspension means of the gas generator.
    According to another characteristic of the invention, the air inlet opening is bent so as to adapt to the circular configuration of the air inlet lips of the fan casings.
    Advantageously, but not exclusively, the curved shape of the air inlet opening is an hourglass shape or has rounded ends.
    According to a characteristic of the invention, the air inlet lips of the fan casings are defined in the same plane.
    Advantageously, but not exclusively, the air intake lips of the fan casings are defined in planes axially offset and parallel to each other so as to adapt to the deflection of the blade relative to to an axis of elongation of the fuselage. The invention also relates to a motorized wing comprising a propulsion assembly having any one of the preceding characteristics, said assembly being suspended from the wing. The invention also relates to a motorized wing comprising a propulsion assembly having any of the preceding characteristics, the propulsion assembly being integrated into the wing. 5. BRIEF DESCRIPTION OF THE FIGURES The invention will be better understood, and other objects, details, features and advantages thereof will become more clearly apparent on reading the following detailed explanatory description of embodiments of the invention. invention given by way of purely illustrative and non-limiting examples, with reference to the appended diagrammatic drawings in which:
    Figure 1 shows a partial front view of a wing of an aircraft supporting a propulsion assembly according to the invention;
    Figure 2 is a perspective view of an embodiment of a propulsion assembly according to the invention supported by a wing and comprising a nacelle;
    Figure 3 is a perspective view of another embodiment of a propulsion assembly according to the invention supported by a wing and comprising a nacelle;
    Figure 4 is a schematic cross sectional view of a propulsion assembly comprising an air intake sleeve, according to one embodiment of the invention;
    FIG. 5 is a cross-sectional and diagrammatic view of a propulsion assembly on which a supply duct of the gas generator and a duct for evacuating foreign objects from an air inlet duct can be seen. according to another embodiment of the invention;
    Figure 6 is a schematic and front view of another embodiment of the propulsion assembly according to the invention;
    Figure 7 is a schematic cross sectional view of a propulsion unit integrated with a wing of an aircraft, according to yet another embodiment of the invention;
    Figures 8 and 9 are schematic representations of the propulsion assembly illustrated in Figure 7;
    Figure 10 is a cross-sectional and schematic sectional view of a propulsion assembly according to the invention integrated into a wing of an aircraft;
    Figure 11 shows an axial section of the embodiment of Figure 10;
    FIG. 12 is a view from below of a wing supporting a propulsion assembly according to the invention;
    Figure 13 shows a front view of another embodiment of the propulsion assembly according to the invention. 6. Description of embodiments of the invention
    Figure 1 is a partial view of a motorized wing 1 or wing of lateral lift of an aircraft, and in particular of an aircraft (not shown), the wing being located in a fuselage of the aircraft. This wing 1 extends in a direction of E-E span from the fuselage and comprises an upper surface 2 said extrados and a lower surface 3 said intrados opposite to a plane comprising the E-E span direction. The intrados and extrados surfaces 2, 3 are connected to each other by a leading edge 4 upstream and a trailing edge 5 downstream of the wing. In the present invention the terms "upstream" and "downstream" are defined with respect to the direction of travel of the aircraft.
    A propulsion assembly 10 supported by each wing 1 comprises a gas generator 11 with a longitudinal axis X substantially parallel to the axis of elongation of the fuselage and two blowers 12 with axes offset relative to a vertical plane passing through the airfoil. X axis of the gas generator 11. The blowers 12 are disposed on either side of the gas generator 11. Preferably, but not exclusively, the axes of the blowers are defined in the same plane substantially parallel to the plane in which is defined the direction of EE span, ie the wing 1 of the aircraft.
    The blowers 12 are spaced from each other so as to allow the installation of the gas generator 11 between them. The longitudinal axis X of the gas generator 11 may be in the same plane as the axes of the blowers, or be offset vertically relative to the plane of the axes of the blowers, which allows closer to the blowers 12 one of the 'other.
    In Figures 1 to 4 and 6, the gas generator 11 and the blowers 12 are hooked to the motorized wing of the aircraft via a pylon (not shown). For this purpose, the blowers 12 are each disposed in a fan casing 14. The blowers are driven via a power transmission mechanism (not shown) coupled to the shaft of the gas generator.
    The gas generator 11 is housed in a casing 13 and comprises from upstream to downstream at least one inlet opening 11c, a compressor, a combustion chamber and a turbine. The housing terminates downstream by a throttle nozzle. It can be single or multi stream, single or multi body as needed. The casing of the gas generator has a generally cylindrical shape. Furthermore, the gas generator 11 can be arranged behind the blower housings or between the blower housings.
    The upper part of the casings 13, 14 is arranged substantially in the same plane. This configuration facilitates the attachment of the power unit to the wing. In the present invention, the terms "upper" and "lower" are defined with respect to a vertical direction, the aircraft generally being positioned substantially horizontally. The propulsion assembly 10 comprises an air inlet shroud 15 having a front wall 16 provided with an air inlet opening 17 which extends between the blowers 12. The front wall 16 is arranged between the blowers 12 and upstream of the gas generator 11, in a plane transverse to the axis of the gas generator. Furthermore, the front wall 16 may have a symmetry with respect to a median horizontal plane which includes the axes of the blowers. The front wall may also have a symmetry with respect to a median vertical plane passing between the two blowers 12 with reference to FIGS. 1, 2 and 6.
    More specifically, the propulsion assembly 10 includes a nacelle 25 which includes the air intake fairing 15. The nacelle 25 advantageously, but not exclusively, envelops the upstream portions of the blowers (see FIG. In this example, the nacelle 25 carries the upstream portions of the fan casings, and the front wall 16 is upstream of the gas generator. Alternatively and as shown in Figures 2 and 3, the nacelle 25 forms an aerodynamic fairing containing or completely enveloping the two blowers and the gas generator, as well as the air inlet opening 17. The opening air inlet 17 is configured to feed at least the gas generator 11. This air inlet opening 17 is disposed between the two blowers 12 and extends over the entire height of the front wall 16. In FIG. in other words, the air inlet opening extends on either side of the plane of blowers containing the axes of rotation of the two blowers. The air inlet opening is formed in a single portion 17 as can be seen in FIGS. 1 to 3. Alternatively and with reference to FIG. 6, the air inlet opening is formed of two parts 17, 17 'distributed on either side of the fan plane and separated from each other by a wall 18. The X axis of the gas generator 11 passes inside the air inlet opening 17 or one of the air inlet opening portions 17, 17 '. The air inlet opening 17 has a curved shape so as to fit at least partly in the form of an inter-fan zone which is delimited by air inlet lips 19 surrounding the air intakes. fan casings here of circular section. In particular, the air inlet opening 17 has concave portions inwardly facing each other at the location of the median horizontal plane. The curved shape may be an hourglass shape or have rounded ends as with reference to the example of Figure 3. Of course, any other shape to adapt to the interspersing zone is possible.
    In FIGS. 1, 2, 6 and 12, the air inlet lips 19 of the remote blowers 12 are defined in the same plane AB, which is here perpendicular to the axis of the gas generator. The front wall 16 carrying the air inlet opening 17 is also defined in this plane AB.
    In Figure 3, the blowers 12 are axially offset relative to each other so as to follow the arrow that presents the wing of the aircraft. In particular, the air intake lips 19 of the remote blowers 12 are defined in BC and CD planes axially offset relative to each other. In this example, the planes BC and CD of the air inlet lips 19 are substantially parallel and perpendicular to the axis of the gas generator 11. The air inlet opening 17 of the front wall 16 is defined in the plane of the fan 12 which is located on the side of the free end of the wing 1, the most downstream.
    With reference to FIGS. 4 and 5, the propulsion assembly further comprises an air inlet sleeve 20 comprising an inlet duct 21 and a supply duct 22 of the gas generator 11 fed by the duct input 21. The latter is oriented along a first axis Al substantially parallel and offset with respect to the longitudinal axis X of the gas generator. The supply duct 22 is connected to the inlet opening 11 of the gas generator 11 and is oriented along the axis X of the gas generator. The inlet duct 21 has a front section 21a substantially perpendicular to the axis X of the gas generator. The projection of this frontal section 21a downstream, parallel to the longitudinal axis X, passes outside the perimeter of the inlet opening of the gas generator. In other words, the inlet duct 21 and the supply duct 22 have an S-shaped axial section whose upstream end (front section 21a) is in fluid communication with the lower part of the opening. 17 and the downstream end in fluid communication with the inlet opening of the gas generator.
    The air intake sleeve 20 also comprises an air discharge duct 24 for diverting outside the supply duct 22 of the gas generator 11 the particles or foreign objects ingested by the inlet sleeve 20. In this example, the inlet of the exhaust duct 24 is located below the air supply duct 22, and the exhaust duct 24 extends axially beneath the gas generator 11. The air inlet opening 17 is also in fluid communication with a ventilation duct 23 which extends here on the two lateral sides of the gas generator 11, as well as above the latter while progressing towards the downstream. This ventilation duct 23 is configured to cool equipment of the gas generator, such as for example hot fluid pipes, electronic boxes, as well as volume or surface heat exchangers (not shown). In particular, the air brought by the air inlet opening and flowing in this ventilation duct 23 is on the one hand taken to cool elements of the propulsion assembly and, on the other hand, rejected above the primary flow having passed through the gas generator 11 to then form a fluidic protective film, in particular for an external wall of the lower surface 3 of the wing 1. This fluidic film of fresh air protects the airfoil. excessive heat caused by the gas generator exhaust gas.
    The ventilation duct 23 is delimited in part by a wall of the inlet duct 21, which wall separates the flow of air entering the ventilation duct 23 into ventilation flows passing along an outer casing of the ventilation unit. 11. With reference to FIG. 6 in which the front wall 16 comprises two air inlet opening portions 17, 17 'separated from each other by a wall 18 constituted by a median portion of the front wall 16, the lower part of the air inlet opening 17 feeds the air intake sleeve 20, and the upper air inlet opening portion 17 'is configured to feed the ventilation duct 23. In this case, In this case, the upper air inlet opening 17 'is situated above the median wall 18, while the lower air inlet opening portion 17 is located below this wall. median wall 18. Of course, in another configuration of the propulsion assembly as shown in Figure 13, the lower part of the air inlet opening 17 may be in fluid communication with the ventilation duct, and the upper part of air inlet opening 17 'in fluid communication with the air inlet sleeve 20, the gas generator 11 then being disposed substantially under the blower plane of the propulsion assembly.
    In FIGS. 7 to 11, the gas generator 11 and the blowers 12 are integrated directly into the motorized wing 1. The elements described above and identical or similar in the remainder of this description bear the same reference numerals.
    Referring to Figure 7, each wing 1 comprises an upstream structural spar 30 and a downstream structural spar (not shown) each extending in the wingspan direction EE of the wing 1. At least one of the upstream and downstream spars is formed of a first portion and a second portion, for example substantially rectilinear, which are connected together by a rigid structure 31. This rigid structure 31 can be formed solely by an upper structure of the wing, so as to facilitate the access to the propulsion system and allow it to be dismantled from the bottom of the wing. The two spars here each comprise a first and a second separate and distinct parts, connected together by the rigid structure 31. The gas generator and the remote blowers on either side of the gas generator are hooked at least in part to this upper structure 31 via suspension means 37 (Figures 8 and 9). Thus, the propulsion assembly 10 is arranged between the first and second parts in the span direction of the wing 1. The upper structure 31 surrounds the upper part of the gas generator 11 and the blowers 12. For this, the Upper structure 31 is bent so as to partially adapt to the profile of the gas generator 11 and the blowers 12. As a result, each wing is separated into two parts along its span, by the entire propulsion.
    A lower structure 32 is arranged in the lower part of the upstream and downstream beams 30. The lower structure 32 here comprises three parts 33, 34, 35 which can form hoods and which comprise armatures articulated on the wing by means of hinge hinges 36 which can also constitute locking devices, the pivot axes of which are substantially parallel. to the axis of the gas generator. The side covers 33, 35 may also be articulated respectively to one of the first and second parts of at least one of the longitudinal members so as to easily and quickly access the propulsion assembly 10 and provide maintenance operations. This lower structure 32, and in particular the armatures of the covers 33, 34, 35, may also allow to second the upper rigid structure 31 to pass a portion of the forces between the first and second parts of the upstream and downstream beams. The lower structure 32 comprises a portion of the skin forming the lower surface of the wing 1. The lower structure 32 thus forms the lower outer aerodynamic lines for the blowers and the gas generator. As for the upper structure 31, the latter is covered with a sheet metal or composite skin forming the extrados surface 3 of the wing 1. In the vertical direction with reference to FIGS. 7, 10 and 11, the assembly 10 is disposed between the lower surface and the upper surface of the wing forming the aerodynamic fairing thereof.
    The front wall 16 extends in the inter-fan zone. The air inlet opening 17 extends here between the underside surface and the upper surface forming the aerodynamic fairing. The air inlet opening 17 formed in this front wall is in fluid communication with the air inlet sleeve 20, the inlet duct 21 of the first axis Al is located in the upper part of the opening of air inlet 17 and above the axis of the gas generator 11. The first axis Al and the axis X of the gas generator are misaligned and at a distance from each other, as shown in FIG. Figure 8.
    With reference to FIGS. 8 and 9, the particle exhaust duct 24 of the air intake duct 20 comprises an inlet section which divides downstream of the propulsion assembly 10 into two ducts. evacuation 24a, 24b. The evacuation channels 24a, 24b are shaped to bypass the suspension means 37 of the gas generator 11. As can be seen in FIG. 9, the evacuation channels 24a, 24b pass on either side suspension 37 of the gas generator 11 and in the upper part thereof. The section of the channels on either side of the suspension means 37 is locally shaped so as to occupy most of the radial space between an outer casing of the gas generator 11 and the upper structure 31. Advantageously, the evacuation channels 24a, 24b extend above the transmission shafts 39 of a power transmission mechanism.
    With reference to FIGS. 10 and 11, the air inlet opening 17 also communicates with a ventilation duct 23, the inlet orifice of which is below the inlet duct 21 of the inlet duct. 20. In this example, this ventilation duct 23 divides downstream into two ventilation channels 23a so as to bypass the supply duct 22. The ventilation channels 23a extend in the lower part of the generator 11, essentially below the level of the transmission shafts 39 as shown in Figure 11, for cooling equipment for example arranged on an outer casing of the gas generator, as a device 38 schematically shown in Figure 10. A piece of equipment 38 can consist for example of an air-oil surface exchanger comprising cooling fins. The air circulating in the ventilation duct 23 is rejected below the primary flow that has passed through the gas generator 11 and then forms a protective fluid film, in particular for an internal wall 6 of the intrados surface 3 of the wing 1 .
    Shielding means 40 are integrated on either side of the propulsion assembly 10 so as to protect the equipment installed in the wing, in particular the fuel tanks during a possible bursting disk of the gas generator. These shielding means comprise a shielding plate forming a cross member 41 passing through the wing 1 from its leading edge 4 to its trailing edge 5. Service passages 7 for the equipment installed in the wing 1 are provided above the upper structure 31 for their protection.
    According to another embodiment as shown in Figure 13, the gas generator 11 is carried upstream by the fan casings. The blowers 12 are supported by the motorized wing 1, either by integration in the wing, or by their suspension at the wing which can be achieved by means of a pylon. In this example, the plane EF tangent to the lower parts of the blowers 12 is also substantially tangential to the lower part of the gas generator 11. The last is fed by the supply duct 22 and the input duct 21 in the shape of S The intake duct 21, and in particular its front section 21a, are situated in the upper part of the air inlet opening 17.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. A propulsion unit (10) of an aircraft, comprising a gas generator (11) and two blowers (12) rotated by the gas generator (11) and offset on both sides of a plane vertical passing through the axis thereof, characterized in that it comprises an air inlet sleeve (20) having an inlet duct (21) oriented along a first axis (Al) substantially parallel and offset with respect to a longitudinal axis (X) of the gas generator, the inlet duct (21) separating into a supply duct (22) which is connected to an inlet opening (lie) of the gas generator ( 11) and an evacuation duct (24) configured in such a way that particles ingested by the inlet duct (21) are discharged without entering the gas generator.
    [2" id="c-fr-0002]
    2. Assembly (10) according to claim 1, characterized in that the inlet duct (21) has a front section (21a) whose downstream projection parallel to the longitudinal axis (X) passes outside the perimeter of the inlet opening (lie) of the gas generator (11).
    [3" id="c-fr-0003]
    3. Assembly (12) according to claim 2, characterized in that the two blowers (12) are contained in an aerodynamic fairing (15, 2, 3) having an upper surface (2) and a lower surface (3), and the front section (21a) of the inlet duct (21) is inscribed in an air inlet opening (17, 17 ') which extends between the two blowers (12) and between the upper surface (2) and the lower surface (3) of the fairing.
    [4" id="c-fr-0004]
    4. Assembly (12) according to claim 3, characterized in that the longitudinal axis (X) of the gas generator passes inside the air inlet opening (17, 17 ').
    [5" id="c-fr-0005]
    5. Assembly (12) according to claim 3 or 4, characterized in that the air inlet opening (17, 17 ') extends on either side of a plane of blowers containing the axes. rotation of the two blowers (12).
    [6" id="c-fr-0006]
    6. Assembly (12) according to claim 4, characterized in that the air inlet opening (17, 17 ') is formed in a single portion (17).
    [7" id="c-fr-0007]
    7. Assembly (12) according to claim 5, characterized in that the air inlet opening is formed of two parts (17, 17 ') distributed on either side of the plane of blowers and separated from each other by a wall (18).
    [8" id="c-fr-0008]
    8. Assembly according to any one of claims 3 to 7, characterized in that the air inlet opening (17, 17 ') brings the incoming air on the one hand into the inlet duct (21). ) and on the other hand in a ventilation duct (23) from which air is taken to cool elements of the propulsion assembly and / or a wing of the aircraft.
    [9" id="c-fr-0009]
    9. Assembly according to the preceding claim, characterized in that the ventilation duct (23) is delimited in part by a wall of the inlet duct (21), said wall separating the flow of air entering the ventilation duct ( 23) into ventilation flows passing along an outer casing of the gas generator (11).
    [10" id="c-fr-0010]
    10. An assembly according to any one of the preceding claims, characterized in that the discharge duct (24) comprises an inlet section which divides downstream into two channels (24a, 24b) shaped to circumvent means suspension (37) of the gas generator.
    [11" id="c-fr-0011]
    11. Wing (1) motorized, characterized in that it comprises a propulsion assembly (10) according to any one of the preceding claims, which is suspended from the wing.
    [12" id="c-fr-0012]
    12. Wing (1) motorized, characterized in that it comprises a propulsion assembly (10) according to any one of claims 1 to 10, which is integrated in the wing.
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    同族专利:
    公开号 | 公开日
    US10814989B2|2020-10-27|
    US20170137134A1|2017-05-18|
    FR3043723B1|2017-11-24|
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    法律状态:
    2016-11-03| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-19| PLSC| Publication of the preliminary search report|Effective date: 20170519 |
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    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1560895A|FR3043723B1|2015-11-13|2015-11-13|PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING A GAS GENERATOR, TWO DEPTH BLOWERS AND AN AIR INLET HANDLE|FR1560895A| FR3043723B1|2015-11-13|2015-11-13|PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING A GAS GENERATOR, TWO DEPTH BLOWERS AND AN AIR INLET HANDLE|
    US15/349,675| US10814989B2|2015-11-13|2016-11-11|Propulsion assembly for an aircraft, comprising a gas generator, two offset fans and an air inlet sleeve|
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