• 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:
    Propulsive assembly comprising: - an internal casing (13); - an outer casing (3); an inter-vein casing delimiting a primary vein (12) between the inner casing (13) and an inner wall (14) and a secondary vein (16) between the outer casing (3) and a wall (17); ) external ; a blower capable of generating a flow (24) of circulating air downstream upstream in the secondary vein (16); the assembly further comprising: - at least one duct (27) for sampling said flow (24), this duct (27) comprising an orifice (28) for admission into the outer wall (17) and an orifice (29) exhaust in the inner wall (14); - a movable outer flap (30) between an open position of the inlet orifice (28) and a closed position; - an inner flap (31) movable between an open position of the exhaust port (29) and a closed position.
    公开号:FR3057620A1
    申请号:FR1660099
    申请日:2016-10-18
    公开日:2018-04-20
    发明作者:Rodolphe Jacques Gerard Pouyau Guillaume；Gabriela PHILIPPART；Sylvain Vessot Christian；Patrick Tesniere Marc
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to an aircraft propulsion unit comprising a double-flow turbomachine comprising a fan provided with blades with variable setting, and more precisely the supply of a gas generator of the turbomachine when the propulsion unit operates in a mode called "reverse" or "reverse thrust".
    STATE OF THE ART
    A propulsion unit comprises, for example, a double-flow turbomachine integrated in a nacelle, the turbomachine comprising from upstream to downstream, at least one fan and a gas generator comprising, for example, one or more compressor stages, low pressure and high pressure, a combustion chamber, one or more turbine stages, high pressure then low pressure.
    In a so-called "propellant" operating mode of the propulsion unit, for example when the aircraft is cruising, the air flow generated by the fan is divided, by a separator (or separation nozzle), a primary air flow and a secondary air flow circulating from upstream to downstream. More specifically, the primary flow flows in an annular primary vein of the gas generator and the secondary air flow flows in an annular secondary vein delimited radially between the gas generator and the nacelle, and participating predominantly in the thrust provided by the propulsion unit.
    By convention, in the present application, the terms “upstream” and “downstream” are defined with respect to the direction of gas flow in the propulsion unit when the latter operates in “propellant” mode. Likewise, by convention in the present application, the terms “internal” and “external” are defined radially with respect to the longitudinal axis of the turbomachine, which is in particular the axis of rotation of the rotors of the compressors and of the turbines. .
    To reduce the fuel consumption of the propulsion unit, engine manufacturers are continually seeking to increase the dilution rate commonly known as BPR for the propulsion unit's “By Pass Ratio”, the latter corresponding to the quotient of the air flow in the secondary vein and in the primary vein.
    To meet this objective, it is in particular possible to have a blower provided with variable pitch blades so as to adjust the pitch (and more precisely the wedge angle) of the blades according to the flight parameters, and thus so general optimize the operation of the propulsion system.
    The fact of having variable-pitch blades also makes it possible, in a so-called “reverse” operating mode, to use the latter to generate a counter-thrust, and thus participate in the slowing down of the aircraft in addition to the brakes. so as to reduce its braking distance during landing.
    Thus, in propellant operating mode, the setting of the fan blades is positive, and in reverse operating mode, the setting of the blades is negative.
    Unlike a blower fitted with blades with fixed timing which requires the addition of thrust reversers (for example reversers with pivoting doors and / or sliding covers incorporated in the nacelle) to generate this counter-thrust during landing of the aircraft, a propulsion unit comprising a fan fitted with variable pitch blades does not include thrust reversers in its structure, to the benefit of the mass of the propulsion unit.
    In reverse operating mode, the secondary flow circulates from downstream to upstream in the secondary flow, a first part of the secondary flow being used to supply the primary flow of the gas generator in which the air flow always flows d 'upstream downstream, a second part of the secondary flow escaping from the propulsion unit via the blower so as to generate a counter-thrust.
    By feedback, with reference to the first part of the secondary flow entering the primary vein, there is the appearance of zones of separation of the air flow at the level of the separation nozzle. These separation zones greatly degrade the efficiency of the gas generator, and in general of the propulsion unit. Depending on the engine speed used, these separation zones can jeopardize the operation of the gas generator.
    The objective of the present invention is thus to remedy the aforementioned drawback.
    STATEMENT OF THE INVENTION
    To this end, the invention proposes a propulsion unit, in particular for aircraft, comprising:
    - an internal annular casing;
    - an external annular casing extending at least partially around the internal casing;
    an annular inter-vein casing disposed between the internal casing and the external casing so as to delimit an annular primary vein between the internal casing and an internal wall of the inter-vein casing, and a secondary annular vein between the external casing and a wall external of the inter-vein casing;
    - a blower surrounded by the external casing and comprising variable-pitch vanes capable of generating a flow of air flowing downstream upstream in the secondary stream;
    characterized in that it further comprises:
    - At least one duct for sampling said air flow to supply the primary vein, this duct comprising an intake orifice made in the external wall and an exhaust orifice made in the internal wall;
    - at least one movable external flap between an opening position of the intake port and a closed position of the intake port;
    - at least one movable internal flap between an open position of the exhaust port and a closed position of the exhaust port.
    The sampling duct associated with the internal and external flaps not only optimizes the flow of the air flow sampled during its passage from the secondary vein to the primary vein but also provides the adequate air flow in the vein primary when the propulsion system operates in reverse mode, for the benefit of the efficiency and the service life of the propulsion system.
    The propulsion unit according to the invention may include one or more of the following characteristics, taken in isolation from one another or in combination with one another:
    - The duct includes a device for orienting said air flow;
    - The device for orienting said air flow comprises at least one curved fin with a concavity facing downstream;
    - the inlet and exhaust ports are made at an upstream end of the inter-vein casing, forming a spout for separating the primary and secondary veins;
    - the duct is delimited axially by curved partitions with a concavity facing downstream and connecting the internal and external walls;
    - the internal and external shutters are each controlled by means of control for opening and closing;
    - the internal and external shutters are controlled by common means of opening and closing control;
    - the internal and external components are articulated around a common axis;
    - the common means include:
    • a compass system comprising internal and external rods whose upstream ends are articulated relative to each other about a common axis and whose downstream ends are each coupled in rotation, respectively, to the internal and external flaps ;
    • an actuation system;
    • a transmission system coupled in rotation to the actuation system and the compass system;
    - the transmission system includes:
    • internal and external connecting rods whose downstream ends are articulated with respect to each other about a common axis and whose upstream ends are each coupled in rotation, respectively, to the internal and external connecting rods;
    • a first lever articulated around a fixed axis relative to the inter-vein casing, the first lever having a downstream end coupled in rotation to the actuation system and an upstream end coupled in rotation to a transmission member;
    • a second lever articulated around a fixed axis relative to the inter-vein casing, the second lever comprising an oblong hole in which a finger of the organ is inserted;
    • an arm having a downstream end coupled in rotation to the second lever and an upstream end coupled in rotation to each of the downstream ends of the connecting rods.
    DESCRIPTION OF THE FIGURES
    The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings in which:
    - Figure 1 is a schematic view, in longitudinal section, of a propulsion unit operating according to a so-called "propellant" mode;
    - Figure 2 is a schematic view, in longitudinal section, of the propulsion unit operating in a so-called "reverse" mode;
    - Figure 3 is a schematic view, in longitudinal section, of a propellant assembly sampling system, this system comprising internal and external flaps in the closed position;
    - Figure 4 is a detail view, in longitudinal half-section, of the sampling system of Figure 3;
    - Figure 5 is a schematic detail view, in longitudinal half-section, of the sampling system with the flaps in the open position;
    - Figure 6 is a schematic detail view, in longitudinal half-section 5, of a variant of the sampling system, with the flaps in the open position;
    - Figure 7 is a schematic detail view, in longitudinal half-section, of the variant of the sampling system shown in Figure 6, with the flaps in the closed position.
    DETAILED DESCRIPTION
    FIG. 1 shows a propulsion unit 1, in particular for an aircraft, comprising a turbomachine 2 with double flow integrated in an annular external casing 3, the turbomachine 2 comprising from upstream to downstream, a blower 4 and a gas generator 5 comprising several compressor stages, low pressure 6 and high pressure 7, a combustion chamber 8, and several turbine stages, high pressure 9 then low pressure 10.
    In the present case, the external casing 3 comprises in particular a fan casing, an intermediate casing and a nacelle 11.
    The propellant assembly 1 further comprises, on the one hand, an annular primary vein 12 of the gas generator 5 delimited radially between an internal annular casing 13 of the mobile rotors of the turbomachine 2 and an internal wall 14 of an inter-vein casing 15 annular, of axis C of revolution, disposed between the internal casing 13 and the external casing 3, and on the other hand an annular secondary vein 16 delimited radially between an external wall 17 of the inter-vein casing and the external casing 3.
    The axis C of revolution of the inter-vein casing 15 coincides with the longitudinal axis of the turbomachine 2, which is in particular the axis of rotation of the rotors of the fan 4, of the compressors 6, 7 and of the turbines 9, 10 .
    In the following description, the air flows circulating in the primary and secondary veins 12, 16 are respectively called primary flow and secondary flow.
    The fan 4 is surrounded by the external casing 3 and has blades 18 with variable setting. The setting of a blade is quantified via the setting angle which corresponds to the angle, in a longitudinal plane, between the chord of the blade 18 and the plane of rotation of the fan 4.
    In Figure 1 is shown the propellant assembly 1 operating in "propellant" mode. The setting angle of the blades 18 of the fan 4 is positive, the primary and secondary flows 21, 22 generating a positive thrust, that is to say a thrust whose axial result is oriented downstream towards the upstream.
    More specifically, as illustrated in FIG. 1, the air flow 20 generated by the fan 4 (circulating from upstream to downstream) is divided, by a spout 19 for separating the inter-vein casing 15 separating the veins 12 , 16 primary and secondary, in a primary air flow 21 and a secondary air flow 22 flowing from upstream to downstream, the secondary flow 22 participating predominantly in the thrust provided by the propellant assembly 1. This operating mode is for example used when the aircraft is in the take-off and / or cruise phase.
    FIG. 2 shows the propellant assembly 1 operating in "reverse" (or "reverse thrust") mode. The setting angle of the blades 18 of the blower 4 is negative, a part 25 of the secondary flow 24 escaping from the blower 4 so as to generate a negative thrust (or back thrust), that is to say a thrust whose axial result is oriented from upstream to downstream.
    More specifically, as illustrated in FIG. 2, the blower 4 generates a flow 24 of secondary air flowing downstream upstream in the secondary vein 16. A first part 23 of the secondary flow 24 is used to supply the primary vein 12 of the gas generator 5 in which the primary air flow always flows from upstream to downstream. A second part 25 of the secondary flow 24 escapes from the propellant assembly 1 via the fan 4 so as to generate a negative thrust, and thus participate in the deceleration of the aircraft in addition to the brakes so as to reduce its braking distance during landing.
    The propellant assembly 1 comprises a sampling system 26 comprising at least one conduit 27 for sampling the secondary air flow 24 (circulating from downstream to upstream) to supply the primary stream 12 when the propellant assembly 1 operates in “ reverse >>. The conduit 27 includes an inlet port 28 in the outer wall 17 and an exhaust port 29 in the inner wall 14.
    The sampling system 26 further comprises, on the one hand, at least one movable external flap 30 (for example in translation or in rotation), between an open position (FIGS. 5 and 6) of the orifice 28 of inlet and a closed position (Figures 3, 4 and 7) of the inlet port 28, and on the other hand, at least one movable internal flap 31 (for example in translation or in rotation) between a position opening (Figures 5 and 6) of the exhaust port 29 and a closed position (Figures 3, 4 and 7) of the exhaust port 29.
    Thus, when the propellant assembly 1 operates in “propellant” mode, the internal and external flaps 31, 30 are in the closed position, and in other words, respectively, flush with the peripheral edges of the intake and intake ports 28, 29 exhaust, so as to ensure aerodynamic continuity and thus not disturb the flow of primary and secondary flows 21, 22.
    When the propulsion unit 1 operates in "reverse" mode, the internal and external flaps 31, 30 are in the open position, and in other words the internal and external flaps 31, 30 are angularly spaced from the peripheral edges of the orifices 28, 29 d intake and exhaust so as to remove the first part 23 of the secondary flow 24 used to supply the primary stream 12 of the gas generator 5. The first 23 part of the secondary flow 24 is thus deviated by substantially 180 degrees by successively crossing the intake port 28, the conduit 27 then the exhaust port 29, to join the primary stream 12.
    The number of intake and exhaust ports 28, 29, the geometric and dimensional characteristics of the intake and exhaust ports 28, 29, and the angular position of the flaps 30, 31 are parameters determined in order to provide the adequate air flow to the gas generator 5 when the propellant assembly 1 operates in "reverse" mode.
    According to the embodiments illustrated in the figures, the flaps 30, 31 are substantially circular and of complementary shape to the respective orifices 28, 29. Advantageously, in order to minimize the pressure losses, the flaps 30, 31 and / or the edges of the orifices 28, 29 comprise sealing means.
    Advantageously, to avoid any detachment of the first part 23 of the secondary flow 24 during its deflection, the conduit 27 comprises a device 32 for orienting the flow of air taken. The orientation device 32 comprises for example a plurality of circular fins 33, each fin 33 being, in longitudinal section, curved with a concavity facing downstream (Figures 6 and 7). The fins 33 are for example arranged axially one behind the other.
    According to the embodiments illustrated in the figures, the inlet and outlet orifices 28, 29 are formed at an upstream end of the inter-vein casing 15, said upstream end forming the spout 19 for separating the primary veins 12, 16 and secondary.
    The sampling system 26 may comprise a single annular conduit 27 (axis C of revolution) for sampling. As a variant, the sampling system 26 may comprise a sectored conduit 27 comprising a plurality of conduit sectors distributed angularly around the axis C, the different sectors being joined angularly to each other or separated angularly from each other, a regular or irregular step.
    Advantageously, as illustrated in the figures, each conduit 27 is delimited axially by curved partitions 34 with concavity turned downstream and connecting the walls 14, 17 internal and external, so as to facilitate the flow of the fluid in the conduit 27.
    The orifice 28 for admitting a sampling duct 27 is associated with one or more external flaps 30, this or these external flap (s) 30 being controlled by means 35 for opening and closing control . In the same way, the orifice 29 for the exhaust of a sampling duct 27 is associated with one or more internal flaps 31, this or these internal flap (s) 31 being controlled by control means 35 'opening and closing.
    According to the embodiment illustrated in FIGS. 3 to 5, a pair of flaps of a sampling conduit 27, namely an internal flap 31 and an external flap 30 facing each other, is articulated, at a upstream end, around a common (circular) axis A fixed relative to the inter-vein casing 15. The pair of flaps 30, 31 is controlled by common means 35 for opening and closing control. The flaps 30, 31 open from downstream to upstream so as to facilitate the intake and exhaust of the first part 23 of the secondary flow 24. Indeed, in the open position, the external flap 30 is opposed to the flow of the secondary flow 24 so as to orient the first part 23 in the direction of the corresponding conduit 27.
    More specifically, the common means 35 comprise a compass system 36 comprising internal and external links 37, 38 of identical length. Upstream ends of the links 37, 38 are articulated relative to each other about a common axis B, while downstream ends of the links are each coupled in rotation, respectively, to the internal and external flaps 31, 30 , around an anchoring axis D formed in an ear 39 projecting from a downstream end of the corresponding flap 31.30.
    The links 37, 38 and the flaps 31.30 form a so-called double triangulation mechanism having, in longitudinal half-section, a shape of double chevron. The internal and external links 37, 38 are thus respectively opposite the internal and external flaps 31, 30.
    The compass system 36 makes it possible to synchronize the opening and closing of the internal and external flaps 31, 30.
    The opening (respectively closing) movement of the flaps 30, 31 is initiated by means of an actuation system 40. The opening (respectively closing) movement is transmitted to the flaps 30, 31 by means of a transmission system 41 coupled in rotation to the actuation system 40 and to the compass system 36.
    According to the embodiment illustrated in Figures 3 to 5, the actuation system 40 is a linear actuator, such as a cylinder. It notably comprises a body 42 fixed relative to the internal casing-vein and a rod 43 movable in axial translation relative to the body 42.
    The transmission system 41 comprises connecting rods 44, 45 internal and external, of identical length. Downstream ends of the connecting rods 44, 45 are articulated relative to each other about a common axis E, while upstream ends of the connecting rods 44, 45 are each coupled in rotation, respectively, to the connecting rods 37, 38 internal and external, appreciably mid-length.
    The transmission system 41 further comprises on the one hand a first lever 46 and a second lever 48. The first lever 46 is articulated around an axis F fixed relative to the inter-vein casing 15, and has a downstream end coupled in rotation to the rod 43 of the linear actuator and an upstream end coupled in rotation to a transmission member 47. The second lever 48 is articulated around an axis G fixed relative to the inter-vein casing 15. The second lever 48 comprises, at a downstream end, an oblong hole 49 into which a finger 50 of the member 47 is inserted. The levers 46, 48 are each, in longitudinal half-section, in the form of a square. , the axes F, G of articulation of the levers 46, 48 being located at the right angles.
    The transmission system 41 also includes a transmission arm 51. The transmission arm 51 has a downstream end coupled in rotation to an upstream end of the second lever 48, and an upstream end coupled in rotation to each of the downstream ends of the connecting rods 44, 45.
    The opening (respectively closing) movement initiated by the actuation system 40 is transmitted to the internal and external flaps 31, 30, successively, by the first lever 46 (by rotation about the axis F), the member 47 of transmission (by curvilinear translation), the second lever 48 (by rotation around the axis G), the arm 51, the connecting rods 44, 45 and the connecting rods 37, 38.
    Advantageously, several pairs of flaps 31, 30 are coupled to a circular transmission member 47 (axis C of revolution), so as to minimize the number of actuation systems 40. The member 47 thus comprises a finger 50 for each pair of flaps 31.30 to be controlled. Each pair of flaps 31, 30 is connected to the corresponding finger 50 by an assembly comprising a compass mechanism (provided with internal and external links 37, 38), internal and external links 44, 45, an arm 51 and a second lever 48 .
    Advantageously, in the case where the flaps 30, 31 of a pair are large, the latter is controlled via several compass mechanisms distributed angularly in a regular manner around the axis C, these various compass mechanisms being controlled by a common circular member 47 of axis C of revolution.
    According to the embodiment illustrated in Figures 6 and 7, the sampling system 26 comprises an external flap 30 movable in rotation relative to the external wall 17, at an upstream end, around a fixed axis relative to the casing 15 inter-vein. The sampling system also includes an internal flap 31 movable in translation relative to the internal wall. The flaps 30, 31 are movable between an open position (Figure 6) and a closed position (Figure 7).
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Propellant assembly (1), in particular for aircraft, comprising:
    - an internal annular casing (13);
    - an outer annular casing (3) extending at least partially around the internal casing (13);
    - an annular inter-vein casing (15) disposed between the internal casing (13) and the external casing (3) so as to delimit an annular primary vein (12) between the internal casing (13) and an internal wall (14) of the inter-vein casing (15), and an annular secondary vein (16) between the external casing (3) and an external wall (17) of the inter-vein casing (15);
    - a blower (4) surrounded by the external casing (3) and comprising blades (18) with variable setting capable of generating a flow (24) of air flowing downstream upstream in the secondary stream (16);
    characterized in that it further comprises:
    - at least one conduit (27) for withdrawing said air flow (24) to supply the primary vein (12), this conduit (27) comprising an inlet orifice (28) formed in the external wall (17) and an exhaust orifice (29) formed in the internal wall (14);
    - At least one movable flap (30) between an opening position of the intake port (28) and a closed position of the intake port (28);
    - at least one movable internal flap (31) between an opening position of the exhaust port (29) and a closed position of the exhaust port (29).
    [2" id="c-fr-0002]
    2. An assembly (1) according to claim 1, characterized in that the duct (27) comprises a device (32) for orienting said air flow (24).
    [3" id="c-fr-0003]
    3. An assembly (1) according to claim 2, characterized in that the device (32) for orienting said air flow (24) comprises at least one fin (33) curved with a concavity facing downstream.
    [4" id="c-fr-0004]
    4. Assembly (1) according to one of the preceding claims, characterized in that the intake and exhaust orifices (28, 29) are formed at an upstream end of the inter-vein casing (15), forming a spout (19) for separation of the primary and secondary veins (12, 16).
    [5" id="c-fr-0005]
    5. Assembly (1) according to one of the preceding claims, characterized in that the duct (27) is axially delimited by partitions (34) curved with a concavity turned downstream and connecting the internal walls (14, 17) and external.
    [6" id="c-fr-0006]
    6. Assembly (1) according to one of the preceding claims, characterized in that the internal and external flaps (31, 30) are each controlled by means (35) for opening and closing control.
    [7" id="c-fr-0007]
    7. Assembly (1) according to one of claims 1 to 5, characterized in that the internal and external flaps (31, 30) are controlled by common means (35) for opening and closing control.
    [8" id="c-fr-0008]
    8. Assembly (1) according to one of the preceding claims, characterized in that the internal and external flaps (31, 30) are articulated around a common axis (A).
    [9" id="c-fr-0009]
    9. An assembly (1) according to claim 8 when it depends on claim 7, characterized in that the common means (35) comprise:
    - a compass system (36) comprising internal and external links (37,38) whose upstream ends are articulated relative to each other about a common axis (B) and whose downstream ends are coupled each in rotation, respectively, with the internal and external flaps (31,30);
    - an actuation system (40);
    - a transmission system (41) coupled in rotation to the actuation system (40) 5 and to the compass system (36).
    [10" id="c-fr-0010]
    10. An assembly (1) according to claim 9, characterized in that the transmission system (41) comprises:
    - internal and external connecting rods (44, 45) whose downstream ends are
    10 articulated relative to each other about a common axis (E) and whose upstream ends are each coupled in rotation, respectively, to the internal and external links (37, 38);
    - a first lever (46) articulated around an axis (F) fixed relative to the inter-vein casing (15), the first lever (46) having a downstream end
    [11" id="c-fr-0011]
    15 coupled in rotation to the actuation system (40) and an upstream end coupled in rotation to a transmission member (47);
    - A second lever (48) articulated around an axis (G) fixed relative to the inter-vein casing (15), the second lever (48) comprising an oblong hole (49) in which a finger (50) is inserted the organ (47);
    [12" id="c-fr-0012]
    An arm (51) having a downstream end coupled in rotation to the second lever (48) and an upstream end coupled in rotation to each of the downstream ends of the connecting rods (44, 45).
    1/4
    2/4
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    同族专利:
    公开号 | 公开日
    GB201717054D0|2017-11-29|
    FR3057620B1|2020-07-31|
    US11255295B2|2022-02-22|
    US20180135557A1|2018-05-17|
    GB2557435A|2018-06-20|
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    US11073090B2|2016-03-30|2021-07-27|General Electric Company|Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine|US10502160B2|2016-02-09|2019-12-10|General Electric Company|Reverse thrust engine|
    US10612491B2|2017-09-25|2020-04-07|Rohr, Inc.|Mounting device with pin actuator|
    FR3100268A1|2019-08-29|2021-03-05|Safran Aircraft Engines|DOUBLE-FLOW TURBOMACHINE FOR AN AIRCRAFT|
    RU2765516C1|2021-06-11|2022-01-31|Акционерное общество "Научно Производственное Предприятие "Аэросила"|Method for protecting aircraft power plant from negative thrust in flight|
    法律状态:
    2017-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-20| PLSC| Publication of the preliminary search report|Effective date: 20180420 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660099|2016-10-18|
    FR1660099A|FR3057620B1|2016-10-18|2016-10-18|PROPULSION ASSEMBLY INCLUDING A GAS GENERATOR SUPPLY DUCT IN AN INTER-VEIN CRANKCASE|FR1660099A| FR3057620B1|2016-10-18|2016-10-18|PROPULSION ASSEMBLY INCLUDING A GAS GENERATOR SUPPLY DUCT IN AN INTER-VEIN CRANKCASE|
    GB1717054.9A| GB2557435A|2016-10-18|2017-10-17|Propulsion assembly comprising a duct for feeding the gas generator in an inter-duct casing|
    US15/785,953| US11255295B2|2016-10-18|2017-10-17|Propulsion assembly comprising a duct for feeding the gas generator in an inter-duct casing|
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