• 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 hub (2) for intermediate casing (1) for a turbofan engine comprising: - a discharge vein duct (18), - a discharge valve, comprising a movable door at the orifice inlet of the discharge vein duct (18), - a set of discharge vanes (22) rotatably mounted about a pivot (26) in the discharge vein duct (18) between an open configuration wherein a flow of air from the inlet (4) passes between the discharge vanes (22) and a closed configuration, the pivot (26) of each discharge fin (22) being closer to its leading edge (BA) than its trailing edge (BF).
    公开号:FR3037617A1
    申请号:FR1555549
    申请日:2015-06-17
    公开日:2016-12-23
    发明作者:Jean-Frederic Pierre Joseph Bruhat
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to the general field of turbomachines with a double flow, and more particularly to discharge valves allowing the regulation of the air at the outlet of a compressor of such a turbomachine, said valves being sometimes designated by their acronym VBV (for Variable Bleed Valves). BACKGROUND ART A turbomachine with a double flow generally comprises, upstream to downstream in the direction of flow of the gases, a streamlined fan, a primary flow annular space and an annular secondary flow space. The mass of air sucked by the fan is thus divided into a primary flow F1, which circulates in the primary flow space, and a secondary flow F2, which is concentric with the primary flow F1 and circulates in space secondary flow. The primary flow space passes through a primary body comprising one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine, and a low pressure turbine, and a gas exhaust nozzle. In a manner known per se, the turbomachine further comprises an intermediate casing whose hub is arranged between the low pressure compressor casing and the high pressure compressor casing. The intermediate casing comprises discharge or VBV valves, the role of which is to regulate the inlet flow of the high-pressure compressor in order, in particular, to limit the risks of pumping the low-pressure compressor by evacuating part of the air outside the compressor. primary flow space.
    [0002] As shown in FIG. 1, which is a partial view in axial section of a double-body and dual-flow aircraft jet engine of a known type, the hubs 2 of the intermediate casings usually comprise two annular coaxial ferrules, respectively internal 3 and outer 5, interconnected by an upstream transverse flange 7 and a downstream transverse flange 9.
    [0003] The upstream flange 7 is arranged downstream of the low pressure compressor while the downstream flange 9 is arranged upstream of the high pressure compressor. The inner ferrule 3 delimits the primary flow annular space 10 of the primary flow F1 of the turbomachine and has air intake orifices 4 10 distributed circumferentially around an axis X of the inner ferrule 3 (which is coaxial with the hub 2), which are closed by a corresponding discharge valve 12 for regulating the flow of the high-pressure compressor. Such a discharge valve 12 may take the form of a door 15 which is pivotally mounted on the inner shell 3 between a closed position, in which the door 12 closes the corresponding inlet port 4 and is flush with the inner shell 3 of the intermediate casing 1 forming a substantially continuous surface to minimize the risk of aerodynamic disturbances of the primary flow F1, and an opening position 20 (see Figure 1), wherein the door 12 projects radially inwardly by relative to the inner ferrule 3 and thus allows a part of the primary flow F1 to be withdrawn into the primary flow space 10. The outer ferrule 5 delimits the secondary flow space 14 of the secondary flow F2. the turbomachine, and has air outlet orifices 6 arranged downstream of the downstream transverse flange 9 and distributed circumferentially around the axis X. When the air flow can enter the compressor r high pressure is reduced, an excess of air in the secondary flow space 14 14 can then be discharged through these outlet orifices 6, thus avoiding pumping phenomena that can lead to deterioration or even complete destruction of the low compressor pressure.
    [0004] 303 7 6 1 7 3 The turbomachine further comprises discharge veins formed between the inlet orifices 4 and the outlet orifices 6. Each discharge stream is delimited, from upstream to downstream, between an inlet port 4 and an associated outlet orifice 6, by an annular intermediate space 16, 5 delimited by the ferrules 3, 5 and the transverse flanges 7, 9, then by a discharge vein duct 18 (also known by the acronym of a kit). engine), configured to guide the flow of air to the secondary flow space 14. The discharge vein conduit 18 thus comprises an intermediate orifice 19, which opens into the intermediate space 16 at the level of the Upstream surface of the downstream transverse flange 9. The doors 12, the intermediate spaces 16 and the associated discharge duct ducts 18 together form a system for discharging air to the secondary flow space 14 of the turbomachine.
    [0005] The hub 2 of the intermediate casing 1 thus comprises a plurality of such systems distributed around the axis X. Moreover, when a door 12 of a discharge valve is in the open position, a stream of air is discharged by the it passes through the intermediate space 16, the corresponding discharge duct 18 and then reaches the secondary flow space 14 via a discharge grille 20 comprising fins, or VBV grid. The discharge veins and fins of the VBV grids 20 are inclined with respect to the flow direction of the secondary flow F 2, in order to redirect the flow of air from the primary flow space and to align it as much as possible with that of the secondary flow F2. Modern turbomachines operate at dilution rates (better known by their English terminology of bypass ratio) increasingly important. In order to limit the shock losses in the supersonic flows at the blower head, the rotational angular speed of the blower is reduced. This has the effect of reducing the compression ratio of the blower. At lower compression rates, the pressure and separation losses of the secondary flow F2 therefore have a greater impact and must be limited to the maximum. These pressure losses are present in areas with particular surface irregularities. However, the Applicant has found that the presence of the VBV 20 grid creates a vein irregularity that can create pressure losses when the discharge vein is non-debiting (that is to say when the door 12 of the discharge valve is in the closed position), typically in cruising mode. The VBV gate 20 forms a porous surface in which the air can rush and may create pressure losses and / or boundary layer detachments in the secondary flow F2. It has therefore been proposed in document FR 15 52811 filed on April 1, 2015, in the name of the Applicant, an intermediate casing hub for a turbofan engine comprising: a set of discharge fins fixed in the vein duct discharge, at the outlet of the outer ferrule, and - shutter means, configured to adjust a passage section of the outlet orifice according to the position of the movable door. The closure means is movable between an open configuration, in which a flow of air from the inlet port is capable of passing through the discharge vanes, and a closed configuration, wherein the closure obturate a passage section of the outlet orifice. These sealing means may in particular be formed by the discharge fins which are then pivotally mounted in the discharge vein duct between the open configuration and the closed configuration. However, these shutter means require the implementation of servo means and therefore the addition of components in the engine and therefore the increase of its mass. Typically, in the application FR 15 30 52811, coupling is carried out using a digital control system or a servo system mechanically or hydraulically connecting the door to the closure means and thus ensuring their opening and closing them simultaneously. SUMMARY OF THE INVENTION An objective of the invention is therefore to propose a turbomachine with a double flow comprising discharge valves making it possible to reduce surface irregularities that can create pressure drops or take off the secondary flow in the secondary vein. which is simple and easy to implement, without increasing the mass of the turbomachine. For this, the invention proposes an intermediate casing hub for a turbomachine with a double flow, said hub comprising: an inner shell configured to delimit a primary flow space of the primary gas flow of the turbomachine, an outer shell configured to delimit a secondary flow space of the secondary gas flow of said turbomachine, - a discharge vein duct, extending between the inner ferrule and the outer ferrule, said discharge vein duct opening on the one hand 20 in the primary flow space through an inlet port formed in the inner shell, and secondly in the secondary flow space through an outlet port formed in the outer shell, - a movable door between a closed position, wherein the door closes a passage section of the inlet port, and an open position, in which the door releases a passage section of the inlet port. e, and - discharge vanes comprising a leading edge and a trailing edge, opposite to the leading edge. The discharge vanes are rotatably mounted about a pivot 30 in the discharge vein conduit at the outlet port between an open configuration, in which a flow of air from the inlet port is capable of passing between the discharge vanes, and a closed configuration, wherein the discharge vanes seal a passage section of the outlet port. The pivot of each discharge fin is closer to its leading edge than its trailing edge.
    [0006] Some preferred but non-limiting features of the crankcase hub described above are as follows, taken alone or in combination: in closed configuration, the discharge vanes create a substantially continuous surface, each discharge fin is in contact with an adjacent discharge fin to form the substantially continuous surface; - the discharge vanes comprise a downstream portion, extending between the pivot and the trailing edge, and an upstream portion extending between the pivot and the d-shaped edge; the downstream portion and the upstream portion of the discharge vanes having a different density, the downstream portion is hollow, the inner ring has an axis of revolution and the hub comprises a plurality of circumferentially distributed discharge vanes; said axis, at least a portion of said discharge vanes having a different density distribution according to their angular position r of the axis, - each discharge fin is equipped with a spring system fixed on the one hand on the pivot and on the other hand on the discharge vein duct so as to apply a moment on the fin of discharge tending to bring said fin into its open configuration, and the hub further comprises a system for damping the discharge vanes. According to a second aspect, the invention also proposes an intermediate casing for a turbomachine with a double flow comprising a hub 30 as described above, as well as a turbomachine comprising such an intermediate casing.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with reference to the appended drawings given by way of non-limiting examples and in which: FIG. 1, which has been described above, is an axial sectional view of an intermediate case hub known from the prior art, and FIGS. 2a and 2b are diagrammatic sectional views of an exemplary embodiment. discharge vanes in open configuration and in closed configuration, respectively. DETAILED DESCRIPTION OF AN EMBODIMENT In the following, an intermediate casing hub 2 for a turbomachine with a double flow and an associated intermediate casing will now be described with reference to the appended figures. The hub parts 2 for the intermediate case of the prior art already described are also present in the following embodiments. In particular, an intermediate casing hub 2 according to the invention comprises: - an inner shell 3 configured to delimit a primary flow space 10 of the primary gas flow of the turbomachine, - an outer shell 5 configured to delimit a secondary flow space 14 of the secondary gas flow of said turbomachine, and - a discharge vein duct 18, extending between the inner ferrule 3 and the outer ferrule 5. The discharge vein duct 18 opens into the primary flow space 10 through an inlet port 4 formed in the inner shell 3 and the secondary flow space 14 through an outlet port 6 formed in the outer shell 5. As previously described, the hub 2 may further comprise an intermediate space 16 delimited by the inner and outer shells 3 and 5 on the one hand and the upstream and downstream flanges 7 on the other hand, interposed between an upstream end (defined intermediate port) of the discharge vein conduit 18 and the inlet port 4. The inlet port 4, which is formed in the inner shell 3 of the hub 2, 5 can be selectively opened or closed by a door 12 according to the flight phases of the turbomachine. Preferably, the door 12 is movable between a closed position, in which the door 12 closes the inlet port 4, and an open position, in which the door 12 releases the inlet port 4. By For example, the door 12 may be hinged to the inner shell 3 or include a slide door. The hub 2 further comprises a VBV grid 20 comprising a set of discharge vanes 22, fixed in the discharge vein duct 18 at the outlet orifice 6 of the outer shell 5 and configured to guide a flow of water. discharge air F3 from the primary flow space 10 and inject it into the secondary flow space 14 in a direction substantially parallel to that of the secondary flow F2, in order to reduce the pressure losses in the secondary flow space 14.
    [0008] The discharge vein duct 18 further comprises closure means 22, configured to adjust a passage section of the outlet port 6 according to the position of the door 12. For this purpose, the control means 22 are movable between an open configuration, wherein a flow of air from the inlet port 4 is likely to pass between the discharge vanes 22, and a closed configuration, in which sealing means 22 In one embodiment, in the closed configuration, the sealing means 22 are flush with the outer shell 5 and form a substantially continuous surface 30 in order to limit the surface irregularities that may occur. to create pressure drops or to take off the secondary flow F2.
    [0009] Thus, when the door 12 is in the closed position and no air flow is taken by the discharge valve in the primary flow space 10, the means of shutter 22 close the passage section of the outlet orifice 6, which makes it possible to reduce the surface irregularities in the secondary flow space 14 and thus to limit the pressure drops that may result therefrom. In this configuration, the secondary flow space is substantially similar to the conventional flow spaces of the turbomachines without discharge valves 12. This configuration, in which the doors 12 and the closing means 22 are closed, corresponds to approximately 70% of the operating cycle of the turbomachine (cruising speed). On the other hand, when air has to be taken from the primary flow space 10, for example during a take-off or landing phase, the door 12 is in the open position and the shut-off means 22 are brought into open configuration to release the passage for the discharge air and allow its introduction into the secondary flow F2. In the exemplary embodiment illustrated in FIGS. 2 to 4, the closure means are formed by the discharge vanes 22. For this purpose, the discharge vanes 22 are pivotally mounted in the duct 18 of the vane. discharge, between the open configuration and the closed configuration. In this way, in the open configuration (FIG. 2a), the discharge fins 22 extend in the usual manner in order to deflect the discharge air flow F3 and introduce it into the secondary flow F2 by reducing the losses of charge, while in the closed configuration (2b), they are flush with the outer shell 5 extending in the extension thereof and thus block the passage section of the outlet orifice 6.
    [0010] In one embodiment, each discharge fin 22 is in contact with an adjacent discharge fin 22 to form the substantially continuous surface. For this purpose, the pivot links 26 of two adjacent discharge fins 22 are separated by a distance substantially equal to or slightly smaller than a length of the fins 22. In this way, the surface formed by the discharge vanes 22 in the configuration The closed closure is substantially continuous, and in any case generates negligible surface irregularities in comparison with the conventional discharge fin grids 22 which are fixed with respect to the duct 18. For this purpose, the discharge vanes 22 are mounted rotating in the discharge vein duct 18 around a pivot 26 between the open configuration and the closed configuration. Preferably, the pivots 26 of the discharge vanes 22 are mounted at the outlet port 6. The pivots 26 may be integrally formed with the discharge vanes 22, or attached and fixed to the discharge vanes 22. This embodiment has the advantage of not weighing down the hub 2 by using the parts already present therein (the fins 22), and consequently of reducing the specific consumption of the turbomachine by reducing the pressure drops and detachments of the secondary flow F2 in cruising mode.
    [0011] Each discharge fin 22 comprises a leading edge BA and a trailing edge BF opposite the leading edge BA. The leading edge BA of a fin 22 corresponds to the front part of its aerodynamic profile. It faces the discharge air flow F3 and divides it into a lower airflow and an extrados airflow. The trailing edge BF corresponds to the rear part of the aerodynamic profile, where the intrados and extrados flows meet. In order to allow displacement of the discharge vanes 22 from one configuration to another without requiring active servocontrol, the pivot 26 of each discharge fin 22 is closer to its leading edge BA than to its trailing edge. LF. Furthermore, the axis of rotation 27 of each pivot 26 is preferably aligned or slightly spaced from the outer ferrule 5 (at the level of the passage section of the outlet orifice 6). In this way, in the open configuration, the discharge vanes 22 extend partially into the secondary flow space, while they form a substantially continuous surface in the extension of the outer shell 5 in the closed configuration. Thus, when there is no air flow in the discharge vein conduit 18, the portion 23 (said downstream portion 23) of the discharge vanes 22 which extends between the pivot 26 and the edge of BF leakage extends into the secondary flow space. The secondary flow F2 therefore exerts an aerodynamic force on this portion 23 of the discharge fins 22 which tends to fold down towards the discharge vein duct 18 so as to align said fins 22 with the outer shell 5. Thus, when There is no discharge air flow F3 in the discharge vein conduit 18, the fins 22 are passive (i.e., without servo-controlled) positioning in their closed configuration. When a discharge air stream F3 passes through the discharge vein conduit 18, this discharge air flow F3 applies greater aerodynamic forces to the downstream portion 23 of the discharge fins 22 (ie ie the portion of the fins 22 which extends between the pivot 26 and the trailing edge BF) since this part is larger than the upstream part 24 (that is to say the part of the fins 22 which extends between the pivot 26 and the leading edge BA). If the discharge airflow F3 applies a greater force to the downstream portion 23 of the discharge vane 22 than the secondary flow F2 and gravity, the vane 22 pivots around the pivot 26 and aligns with the discharge air flow F3, thus allowing the discharge air flow F3 to exit the discharge vein duct 18. In order to reinforce the moment applied by the discharge air flow F3 on the discharge fins 22 and to ensure that the fins 22 open whatever the discharge rate of the secondary flow F2, the configuration of the discharge vanes 22 can be modified in order to increase the effect of the aerodynamic forces applied to the downstream part 23 fins 2, or conversely reduce the effects of the forces applied by the secondary flow F2 and gravity. For example, the position of the pivot 26 of each discharge fin 22 may be adjusted relative to the leading edge BA and the trailing edge BF so as to increase the lever arm between the pivot 26 and the trailing edge BF and therefore the moment applied by the discharge air flow F3 to the downstream portion 23 of the fins 22. Alternatively, the local density of the discharge vanes 22 (and thus the position of their center of gravity) can be adjusted by increasing the mass of all or part of the upstream portion 24 of the fins 22 and / or reducing the mass of all or part of the downstream portion 23 of the fins 22. For example, the downstream portion 23 of each discharge fin 22 may be partially hollow while the upstream portion 24 is full. This modification of the position of the center of gravity of the discharge vanes 22 by means of the distribution of their density thus makes it possible to modify the moment resulting from the aerodynamic forces and the gravity on the fins 22. In particular, in comparison with a discharge fin whose density is homogeneous: the moment resulting from the aerodynamic forces applied by the discharge air flow F3 on the downstream part 23 of the discharge vane 22 will be greater, and the moment resulting from the aerodynamic forces applied by the secondary flow F2 and the gravity will be lower.
    [0012] According to another variant, the behavior of the discharge vanes 22 can also be modified by enlarging or reducing the discharge vane 22 in the area adjacent to its leading edge BA. For example, the thickness of the leading edge BA of the discharge fin 22, or if appropriate the entire profile of the fin 22 in a zone adjacent to the leading edge BA, can be increased. In particular, it will be possible to perform a circular skewing in order to increase the internal volume of the discharge fin 22. This local enlargement here again makes it possible to move the center of gravity of the discharge fin 22 to increase the resulting moment applied to its downstream portion 23 and counterbalance the resulting moment applied on its upstream portion 24. Alternatively, the thickness of the leading edge BA can be reduced, for example by performing a sharp skew of said leading edge BA. Similarly, the thickness of the trailing edge BF can be increased or decreased in order to change the position of the center of gravity of the discharge vane 22. According to yet another variant, the discharge vane 22 can be equipped with a spring system, fixed on the one hand on the pivot 26 and on the other hand on the discharge vein conduit 18 (preferably on a wall that does not extend into the discharge air flow F3 ) so as to apply a moment on the discharge fin 22 tending to bring said fin 22 into its open configuration. The stiffness of the spring system is then chosen so as to ensure that the fin 22 returns to the open configuration when the door 12 is in the open position. Of course, these four embodiments to enhance the moment applied by the discharge air flow F3 on the discharge vanes 22 can be combined.
    [0013] Thus, by adjusting the position of the pivot 26 with respect to the leading edge BA and the trailing edge BF, the possible modification of the fins 22 to move their center of gravity and to the optional spring system , shutter means are obtained which can pass from the open configuration to the closed configuration automatically according to the secondary flow F2 and the discharge air flow F3. It will be noted that, depending on the angular position of the discharge vanes 22 around the X axis of the inner ferrule 3 (for example at 12 o'clock or 6 o'clock), the effects of the gravity on the configuration of the discharge vanes 2 are different. . Typically, for discharge fins positioned at 12 o'clock (opposite the ground relative to the X axis), the moment applied to the fins 22 and resulting from the gravity tends to bring the fins 22 into their grooves. closed configuration, while for the discharge fins positioned at 6 o'clock (the opposite of the position at 12 o'clock relative to the X axis), the moment applied to the fins 22 and resulting from the gravity tends to bring the fins 22 in their open configuration.
    [0014] Therefore, the position of the pivot 26 with respect to the leading edge BA and the trailing edge BF, and possibly the position of the center of gravity of the fins 22, may be different depending on their angular position around the axis. X to take into account the effects of gravity on the configuration of the discharge vanes 22.
    [0015] Likewise, the angle between a given discharge fin 22 and the upstream wall 18a (in the gas flow direction in the hub 2) of the discharge vein duct may vary depending on the axial position of the vane 22 (along the X axis), to account for the local direction of flow of the discharge stream. For example, the discharge fin 22 closest to the upstream wall 18a of the duct 18 may be more inclined relative to the section of the outlet orifice 6 than the discharge fin 22 furthest from this wall 18a. . In particular, it will be possible to refer to the application FR 15 52808 filed on April 1, 2015 in the name of the Applicant Company for more information on the respective inclination of the various discharge vanes 22 in the discharge vein duct 18. As a result, the open configuration of each discharge vane 22 can be adjusted according to the optimum angle to be reached in order to limit the pressure drops during the introduction of the discharge air stream F3 into the secondary vein. by adjusting the position of the pivot 26 relative to the leading edge BA and the trailing edge BF of each fin 22 and / or the position of their center of gravity, as indicated above.
    [0016] Whether the discharge vein conduit 18 is flowable (i.e. traversed by a discharge airflow F3) or not, the discharge vanes 22 are capable of vibrating, to the extent that they are free. in order to ensure that the fins 22 change their configuration only when the discharge vein duct 18 becomes flowable or ceases to flow, the pivot 26 of the fins 22 may be equipped with a vibration damping system, fixed on the one hand on the pivot 26 and on the other hand on the discharge vein conduit 18 (preferably on a wall which does not extend into the air flow discharge F3). Such a damping system may in particular comprise a spring system, a hydraulic damping, etc. If necessary, the damping system may also participate in the reinforcement of the moment applied by the discharge air flow F3 on the discharge vanes 22 to allow the discharge vanes 22 to come into open configuration. The discharge vanes 22 may in particular be of butterfly wing type, or any other form adapted to deflect the flow of air from the primary flow space 10 in order to align it with the secondary flow F2.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Intermediate case (2) hub (1) for a turbofan engine, said hub (2) comprising: - an inner shell (3) configured to delimit a primary flow space (10) of the primary gas flow (F1) ) of the turbomachine, - an outer shell (5) configured to delimit a secondary flow space (14) of the secondary gas flow (F2) of said turbomachine, - a discharge vein duct (18), s' extending between the inner ferrule (3) and the outer ferrule (5), said discharge vein conduit (18) opening on the one hand into the primary flow space (10) through an inlet port (4). ) formed in the inner shell (3), and secondly in the secondary flow space (14) through an outlet (6) E formed in the outer shell (5), - a door ( 12) movable between a closed position, wherein the door (12) closes a passage section of the inlet port (4), and an open position, in which the door (12) releases a passage section from the inlet port (4), and - the discharge vanes (22) comprising a leading edge (BA) and a trailing edge (BF), opposite to the leading edge (BA), said discharge vanes (22) being rotatably mounted about a pivot (26) in the discharge vein duct (18) at the outlet port (6); ) between an open configuration, in which an air flow (F3) from the inlet (4) is likely to pass between the discharge vanes (22), and a closed configuration, in which the fins discharge port (22) obturates a passage section of the outlet port (6), the intermediate case hub (2) being characterized in that the pivot (26) of each discharge fin (22) is closer its leading edge (BA) than its trailing edge (BF). 3037617 17
    [0002]
    An intermediate case hub (1) according to claim 1, wherein in the closed configuration the discharge fins (22) create a substantially continuous surface. 5
    [0003]
    The intermediate case hub (2) according to claim 2, wherein each discharge fin (22) is in contact with an adjacent discharge fin (22) to form the substantially continuous surface.
    [0004]
    4. hub (2) of intermediate casing (1) according to one of claims 1 to 3, wherein the discharge fins (22) comprise a downstream portion (23) extending between the pivot (26) and the trailing edge (BF), and an upstream portion (24) extending between the pivot (26) and the leading edge (BA), the downstream portion (23) and the upstream portion (24) of the trailing fins (24). discharge (22) having a different density.
    [0005]
    5. hub (2) intermediate housing (1) according to one of claims 1 to 4, wherein the downstream portion (23) is hollow.
    [0006]
    6. hub (2) intermediate housing (1) according to one of claims 4 or 5, wherein the inner ring (3) has an axis (X) of revolution and the hub (2) comprises a plurality of fins discharge device (22) distributed circumferentially around said axis (X), at least a portion of said discharge fins (22) having a different density distribution according to their angular position about the axis (X).
    [0007]
    Intermediate casing hub (1) according to one of claims 1 to 6, wherein each discharge fin (22) is equipped with a spring system fixed on the one hand on the pivot (26) and on on the other hand on the discharge vein duct (18) so as to apply a moment on the discharge fin (22) tending to bring said fin (22) into its open configuration.
    [0008]
    8. Intermediate case hub (1) according to one of claims 1 5 to 7, further comprising a damping system of the discharge vanes (22).
    [0009]
    9. Intermediate casing (1) for a turbofan engine comprising a hub (2) of intermediate casing (1) according to one of claims 1 to 8.
    [0010]
    10. A turbofan engine comprising an intermediate casing (1) according to claim 9. 15
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    同族专利:
    公开号 | 公开日
    GB201721303D0|2018-01-31|
    US20180195465A1|2018-07-12|
    US10480454B2|2019-11-19|
    GB2555347B|2020-09-09|
    WO2016203157A1|2016-12-22|
    FR3037617B1|2019-06-28|
    GB2555347A|2018-04-25|
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    法律状态:
    2016-06-06| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-23| PLSC| Search report ready|Effective date: 20161223 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1555549|2015-06-17|
    FR1555549A|FR3037617B1|2015-06-17|2015-06-17|TURBOMACHINE DISCHARGE VEIN CONDUIT COMPRISING VARIABLE SECTION VBV GRID AND PASSIVE ACTUATION|FR1555549A| FR3037617B1|2015-06-17|2015-06-17|TURBOMACHINE DISCHARGE VEIN CONDUIT COMPRISING VARIABLE SECTION VBV GRID AND PASSIVE ACTUATION|
    PCT/FR2016/051457| WO2016203157A1|2015-06-17|2016-06-16|Bleed flow duct for a turbomachine comprising a passively actuated variable cross section vbv grating|
    US15/736,636| US10480454B2|2015-06-17|2016-06-16|Bleed flow duct for a turbomachine comprising a passively actuated variable cross section VBV grating|
    GB1721303.4A| GB2555347B|2015-06-17|2016-06-16|Bleed flow duct for a turbomachine comprising a passively actuated variable cross section VBV grating|
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