• 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 system for controlling the orientation of the fan blades of a turbomachine propeller, comprising a jack (2) integral with a casing (5) of the turbomachine, comprising a movable part (6) in translation. with respect to said housing, the movable portion being mechanically coupled to a motion transfer bearing (10) having an outer ring (12) which is coupled to fan blade pivots (16) such that a translation of the mobile part of the cylinder causes a change in the orientation of said fan blades, and at least one locking pin (20) integral with the casing of the turbomachine and adapted, in the event of malfunction of the jack, to mechanically lock the transfer bearing of movement in feathering position of the fan blades.
    公开号:FR3046409A1
    申请号:FR1650042
    申请日:2016-01-05
    公开日:2017-07-07
    发明作者:Didier Jean-Louis Yvon；Clementine Charlotte Marie Mouton；Emmanuel Pierre Dimitri Patsouris
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to the general field of turbomachines equipped with one or two fan (s) ducted (s) or not careened (s), and more particularly to the control of the orientation of the fan blades (s) of these turbomachinery.
    A preferred field of application of the invention relates to jet engines with counter-rotating propellers, called "Open Rotors" in English, which comprise two counter-rotating propellers placed downstream ("pusher" version in English) or upstream ("puller" version in English). English) of the gas generator. However, the invention also applies to turboprop engines with one or more propulsive propellers.
    In a propeller-driven turbojet engine, it is known that the orientation (or wedging) of the blades that form these propellers constitutes one of the parameters making it possible to manage the thrust of the turbojet engine, in particular by still operating the propeller in the propellers. best conditions possible. Indeed, the speed of the propellers is almost constant on all phases of operation, and it is the pitch of the propeller blades that varies the thrust. Thus, in the cruising flight phase, it is sought to obtain the lowest power possible on the turbine shaft which is necessary for a given traction at a given speed of the airplane, so as to obtain the best efficiency ( that is, the efficiency to minimize fuel consumption and increase the range. Conversely, on takeoff, the strongest possible traction is sought to accelerate and then take off the plane. The orientation of the blades of the propellers requires taking certain safety measures to ensure that the blades do not remain blocked in certain positions following in particular a malfunction of the control systems of their orientation. For example, under their own centrifugal effect, the blades tend to move into a flat position (or "sail" position which corresponds to a wedging for which their rope forms a 90 ° angle with the axis of rotation of the propeller). However, a blade locked in this flat position generates little resistive torque and may overspeed, with the risk that it involves losing the blade and / or the rotating hub that carries it.
    In order to remedy this problem, it is known to implement a device allowing, in the event of a failure of the control system, to force the blades to return to their feathering position and to maintain them (the feathering position corresponds to a pitch of the blades in which the rope of the blades aligns with the axis of rotation of the helix, thus reducing the drag which they generate).
    The known devices for feathering fan blades (and their retention in this position) are generally based on the use of counterweights which, thanks to the centrifugal force applied by the rotation of the rotor on which they are installed, allow, in In case of failure of the control system of the orientation of the blades, to bring the blades in feathering position.
    The specification for the sizing of these counterweights imposes to give an equivalent inertia on the axis of rotation of the propeller of 2.1 times (at least) the inertia of the blades. With such a constraint, it is easy to conceive that this type of feathering device generates a very large supplementary mass on the turbomachine, increasing the overhang and shifting its center of gravity.
    Moreover, it is known to seek to reduce the size of the turbomachines with non-faired fan, to reduce the length and bring their center of gravity suspensions to the aircraft. This constraint causes a strong limitation of the place within the turbomachine. Given the inertia necessary for the feathering of the blades by the counterweights, the latter represent a large space required to be housed inside the turbomachine. However, on the "Open Rotor", these counterweights are usually housed at the pivots of the fan blades. Also, for engines with a low hub ratio, the integration of these counterweights at the blade pivots is complicated. Similarly, if they were to be installed inside the turbomachine, their radius of implantation would be smaller, which would require a larger mass.
    Object and summary of the invention
    The present invention therefore has the main purpose of providing a device for feathering fan blades that does not have the aforementioned drawbacks.
    According to the invention, this object is achieved by means of a control system of the orientation of the fan blades of a
    Turbomachine propeller, comprising: a jack integral with a casing of the turbomachine comprising at least one portion movable in translation relative to said casing, the movable portion of the jack being mechanically coupled to a motion transfer bearing having an outer ring which is coupled to fan blade pivots such that a translation of the movable portion of the jack causes a change in the orientation of said fan blades; and at least one locking pin integral with the casing of the turbomachine and adapted, in the event of malfunction of the jack, to mechanically lock the motion transfer bearing in the feathering position of the fan blades.
    By "jack integral with a casing of the turbomachine" is meant here that the cylinder body or the cylinder rod is fixed relative to the casing of the turbomachine. In normal operation of the cylinder, the control of the orientation of the fan blades is ensured by the jack whose moving part moves the rolling bearing for transfer of motion to freely rotate the fan blades. In this situation, the locking pin is in a position that allows it to not hinder the movement of the movable part of the cylinder. In the event of a malfunctioning of the control cylinder of the orientation of the blades, the locking pin is brought into a position which makes it possible to mechanically lock the motion transfer bearing in translation, the latter having been previously brought into the position of implementation. flag of the fan blades.
    The system according to the invention thus makes it possible, thanks to a simple blocking pin, to mechanically lock the blades in the feathering position in the event of malfunctioning of the control cylinder of the orientation of the blades. In particular, no counterweight is necessary to achieve this function, which represents a significant weight gain. In addition, the size of the system according to the invention is reduced, in particular because the locking pin can easily be housed inside the motion transfer bearing.
    Preferably, the blocking pin is able to take two different positions: an extended position in which it bears radially against an inner surface of an inner ring of the motion transfer bearing, and a retracted position in which it is missing. with said inner ring of the motion transfer bearing.
    In this case, in the extended position, the locking pin is advantageously able to bear radially against different ramps of a longitudinal groove formed at the inner surface of the inner ring of the motion transfer bearing, said ramps comprising less a first ramp corresponding to a feathering of the blades and a second ramp corresponding to a thrust reversal of the blades.
    The system may further comprise hydraulic means for holding the locking pin in the retracted position during normal operation of the jack, and mechanical means for holding the locking pin in the extended position in the event of malfunction of the jack. These hydraulic means are preferably also a supply source of the cylinder.
    More preferably, the system further comprises an auxiliary power source adapted to bring the movable portion of the jack in the feathering position of the fan blades in the event of malfunction of the jack, the locking pin then bearing against the radial support against the blade feathering ramp to mechanically maintain said moving part of the cylinder in this position. From upstream to downstream, the ramps of the inner ring of the rolling motion transfer bearing may comprise a following ramp distribution: the first ramp corresponding to the feathering of the blades, an intermediate ramp, and the second ramp corresponding to thrust reversal of the blades.
    In this case, the first ramp and the intermediate ramp may be separated by an upstream stop, the intermediate ramp and the second ramp are separated by a downstream stop, and the intermediate ramp may have a slope inclined downstream relative to a longitudinal axis of the cylinder. The invention also relates to a turbomachine comprising at least one set of controllably adjustable fan blades and a control system of the orientation of the fan blades as defined above.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures: - Figure 1 is a sectional view showing an example of implementation of the system according to the invention; FIG. 2 is a partial view of an inner ring of the motion transfer bearing according to one embodiment of the system according to the invention; - Figure 3 is a sectional view of a locking pin according to one embodiment of the system according to the invention; - Figures 4A to 4C are sectional views of the system of Figures 2 and 3 in different positions of the blower blade setting.
    DETAILED DESCRIPTION OF THE INVENTION The invention applies to any turbomachine equipped with at least one ducted or non-ducted fan, and whose propeller blades (in the case of a non-ducted fan) or the fan blades. (in the case of a streamlined fan) are equipped with a change of pitch system. The invention applies in particular to turboprop engines with one or more propeller propellers, as well as propeller (s) (known as "Open Rotor") turbofan engines that comprise a propeller (and a variable-pitch stator for the propeller). USF - "Unducted Single Fan", or "single fan unsheathed") or two contra-rotating propellers placed upstream (in "puller" version in English) or downstream (in "pusher" version in English) of the gas generator. The invention is still applicable to streamlined fan turbomachines. The architecture of these types of turbomachines is well known to those skilled in the art and will not be described here in detail. Briefly, these turbomachines comprise one or more propellers (in the case of a non-ducted fan turbomachine) or a fan (in the case of a fan-cooled turbomachine) each consisting of a set of blades (or blades ) blowers variable pitch angle, that is to say that their orientation can be changed by means of a control system of the orientation of the blades described below.
    In the remainder of the description, reference will be made to propeller and propeller blades regardless of whether the invention applies to a non-ducted fan turbomachine or to a ducted fan turbomachine (in which case the propeller corresponds to the fan and the propeller blades correspond to the fan blades).
    A turbomachine propeller is constituted by a set of fan blades with variable pitch angle, independent or not, that is to say that their orientation can be modified by means of a control system of the orientation of the blades .
    As shown in FIG. 1, this control system may comprise an axial jack 2 centered on the axis of rotation of the propellers of the turbomachine and fixed with respect to the structures of the engine.
    More specifically, the jack 2 comprises a body 4 integral with a casing 5 of the turbomachine and a plurality of rods 6 (ie moving parts) which can translate axially synchronously when the jack is actuated (via a hydraulic circuit). At their free end, the rods 6 are connected to the inner ring 8 of a transfer transfer bearing 10 (called LTB for "Load Transfer Bearing"), the outer ring 12 of which is coupled, via lever arms. 14, to pivots 16 of the fan blade of the propeller mounted on a rotary ring 17 centered on the axis XX of rotation of the propellers.
    In this way, when the jack 2 is actuated, the rods 6 translate to move the motion transfer bearing 10, which causes a pivoting of the pivots 16 of the fan blades about their radial axis ZZ, and therefore a change in their orientation (or wedging).
    In normal operation, the fan blades can thus take different settings that vary for example from 0 ° to 120 ° relative to the X-X axis of rotation of the helix. A setting at 0 ° is a feathering of the blades which will be sought in case of malfunction of the turbomachine because it is the least restrictive position for the turbomachine and the aircraft (the drag of the blades in this position is minimal ). At the opposite end, a 120 ° wedge constitutes a thrust reversal position.
    Finally, under their own centrifugal effect, the blades may tend to take an intermediate setting of 90 ° with the axis of rotation of the propeller (called flat position or position "sail"). However, a blade locked in this flat position generates little resistive torque and may overspeed, with the risk that it involves losing the blade and / or the rotating hub that carries it and cause a loss of control of the aircraft.
    Note that it is possible to have an inverse configuration in which the cylinder rods are secured to the casing of the turbomachine and the cylinder body is movable (i.e. moving parts) relative to the cylinder rods.
    According to the invention, there is provided a device 18 allowing, in case of malfunction (ie failure) of the control cylinder of the orientation of the blades, to bring the blades in the feathering position and to maintain them in this position in particular to prevent them from moving into a flat position.
    This device comprises at least one locking pin 20 which is mounted in an orifice 22 formed in a strip 24 of the casing 5 of the turbomachine which carries the body 4 of the jack. This orifice 22 which receives the locking pin is located facing the inner surface of the inner ring 6 of the transfer bearing bearing, and more precisely facing a longitudinal groove 26 formed in the inner surface of this ring and s extending parallel to the axis XX.
    As shown in FIG. 2, the groove 26 is notched so as to delimit longitudinally several ramps, namely here: a first ramp 26a situated at the upstream end of the groove and corresponding to a feathering of the blades, a second ramp 26b located at the downstream end of the groove and corresponding to a setting thrust reversal blades, and an intermediate ramp 26c formed between the first and second ramps.
    The intermediate ramp 26c has a slope inclined downstream with respect to the X-X axis, while the first and second ramps 26a, 26b may be substantially flat (with respect to this axis). Finally, the first ramp 26a and the intermediate ramp 26c are separated by an upstream stop 28, while the intermediate ramp and the second ramp 26b are separated by a downstream stop 30. The role of these stops will be detailed later in connection with the operation of the device.
    The number of grooves 26 formed in the inner surface of the inner ring 6 of the motion transfer bearing corresponds to the number of locking pins 20. By way of example, it will be possible to have three grooves 26 regularly distributed around the axis longitudinal XX.
    Figure 3 shows in more detail a locking pin 20 adapted to cooperate with one of these grooves.
    As indicated above, the locking pin 20 is housed in a cylindrical orifice 22 formed in a strip 24 of the casing of the turbomachine which carries the body of the control cylinder of the orientation of the blades.
    The locking pin 20 has an annular collar 20a which divides the orifice 22 into an upper chamber 32 and a lower chamber 34. The upper chamber 32 is in communication with a conduit 36 of a hydraulic control circuit of the jack. As for the lower chamber 34, it is closed by a nut 38 for locking the pin and it comprises a spring 40 wound around the locking pin and exerting an extension force on the collar thereof in the outer direction.
    The extension force of the spring 40 is predefined so that, when fluid of the hydraulic circuit is admitted inside the upper chamber 32 (via the duct 36) and exerts a pressure on the flange 20a of the locking pin 20 , the spring is compressed and the blocking pin is in a position called "retracted" (or retracted) in which it does not come in radial support against one of the ramps of the groove formed in the inner ring of the transfer bearing movement (in the case of FIGS. 4A and 4B). Conversely, when the pressure exerted by the fluid inside the upper chamber 32 weakens, the extension force of the spring 40 pushes the locking pin (by its flange) outwards to hold it in a said "output" position in which it bears in radial support against one of the ramps of the groove formed in the inner ring of the transfer-motion bearing (case of FIG. 4C).
    The operation of the device according to the invention is as follows.
    In normal operation of the cylinder 2 for controlling the orientation of the blades (FIGS. 4A and 4B), the hydraulic circuit makes it possible to control a displacement of the rod 4 of the jack which itself translates the transfer transfer bearing 10 to obtain the desired timing of the fan blades (via the lever arms 14 and pivots 16).
    In this situation, the upper chamber 32 of the orifice 22 is supplied with pressurized fluid through the conduit 36, so that the locking pin 20 comes into the retracted position and thus does not hinder the movement of the motion transfer bearing. . The blower blade setting is therefore free. Thus, FIG. 4A corresponds to a position of thrust reversal of the fan blades (120 ° with respect to the axis of rotation of the helix) and FIG. 4B corresponds to an intermediate wedging between the inversion position of the fan blade. thrust and the feathering position of the blades.
    In the event of a malfunction of the cylinder 2 for controlling the orientation of the blades, the pressure of the fluid inside the upper chamber 32 weakens until it can no longer oppose the extension force of the spring 40. last push then the blocking pin 20 in the extended position and maintains it in this position.
    In the extended position, the locking pin 20 bears radially against the ramp of the inner ring 6 of the motion transfer bearing which is opposite the locking pin.
    Thus, in the case of FIG. 4C, the pitch of the fan blades at the time of the malfunction of the jack 2 was in an intermediate position between the feathering position and the thrust reversal position, that is to say say that the blocking pin was located next to the intermediate ramp 26c.
    At first, the blades naturally tend to return to their flattening position under the effect of their own centrifugal force, they will cause, in their rotational movement, a translation of the transfer of motion transfer to the upstream (in the case of FIGS. 4A to 4C). During this translational movement, the locking pin 20 will slide along the inclination formed by the intermediate ramp 26c to come into axial abutment against the downstream stop 30 of the groove 26 (as shown in Figure 4C).
    In this position, the blocking pin prevents the motion transfer bearing from translating further upstream, to prevent the blades from moving to the flat position under the effect of their centrifugal force.
    In a second step, an auxiliary power source (not shown in the figures) will be applied on the cylinder 2 to bring the rod 6 in a position corresponding to a feathering of the blades. In the case shown in FIGS. 4A to 4C, this feathering position corresponds to a position of the rod completely downstream. Auxiliary power source means any source of energy (electrical, hydraulic, mechanical, etc.) which is distinct from the hydraulic circuit for activating the control cylinder of the orientation of the blades.
    The movement of the rod of the cylinder downstream will cause a displacement of the motion transfer bearing, allowing relative movement of the locking pin 20 downstream. The latter will then slide along the inclination formed by the intermediate ramp 26c to pass the upstream stop 28. Once this upstream stop crossed, the auxiliary power source is cut.
    In this position not shown in the figures, the motion transfer bearing is in a position corresponding to the feathering of the fan blades and the locking pin allows to maintain it. Indeed, while abutting against the upstream stop 28, the locking pin makes it possible to counter the effect of the centrifugal force of the blades which tends to cause the movement transfer bearing upstream.
    It will be noted that the maintenance in the feathering position of blades thus carried out by the locking pin does not require any source of energy (the maintenance is done by mechanical stop). In addition, the auxiliary power source that brings the blades into this feathering position is punctual and can be cut as soon as the locking pin has passed the upstream stop of the groove of the inner ring of the transfer transfer bearing . The sizing of this auxiliary power source is therefore less restrictive than if it were to maintain this position, which allows for a smaller mass.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Control system for the orientation of the fan blades of a turbomachine propeller, comprising: a jack (2) integral with a casing (5) of the turbomachine, comprising a movable part (6) in translation relative to to said casing (5), the movable portion being mechanically coupled to a motion transfer bearing (10) having an outer ring (12) which is coupled to fan blade pivots (16) so that a translation of the moving part of the jack causes a change in the orientation of said fan blades; and at least one locking pin (20) integral with the casing of the turbomachine and adapted, in the event of malfunction of the jack, to mechanically lock the motion transfer bearing in the feathering position of the fan blades.
    [2" id="c-fr-0002]
    2. System according to claim 1, wherein the locking pin (20) is adapted to take two different positions: an extended position in which it bears radially against an inner surface (26) of an inner ring (6). the motion transfer bearing (10), and a retracted position in which it is devoid of support with said inner ring of the motion transfer bearing.
    [3" id="c-fr-0003]
    3. System according to claim 2, wherein, in the extended position, the locking pin (20) is able to come into radial abutment against different ramps of a longitudinal groove formed at the inner surface of the inner ring of the bearing. motion transfer device, said ramps comprising at least a first ramp (26a) corresponding to a feathering of the blades and a second ramp (26b) corresponding to a thrust reversal of the blades.
    [4" id="c-fr-0004]
    4. System according to one of claims 2 and 3, further comprising hydraulic means (36) for holding the blocking pin in the retracted position during normal operation of the jack, and mechanical means (40) for holding the blocking pin in the out position in case of malfunction of the cylinder.
    [5" id="c-fr-0005]
    The system of claim 4, wherein the lock pin (20) is housed in a housing port (22) which includes an upper chamber (32) in communication with a hydraulic circuit and a lower chamber (34) comprising a spring (40) adapted to hold the locking pin in the extended position in case of malfunction of the jack.
    [6" id="c-fr-0006]
    6. System according to claim 5, wherein the hydraulic circuit is also a power source of the cylinder (2).
    [7" id="c-fr-0007]
    7. System according to any one of claims 4 to 6, further comprising an auxiliary power source adapted to bring the movable part of the jack in the feathering position of the fan blades in the event of malfunction of the jack, the pin blocking then bearing radially against the first ramp (26a) to mechanically maintain said movable portion of the cylinder in this position.
    [8" id="c-fr-0008]
    8. System according to any one of claims 3 to 7, wherein, from upstream to downstream, the ramps of the inner ring of the rolling bearing motion transfer comprise a following ramp distribution: the first ramp (26a) corresponding to the feathering of the blades, an intermediate ramp (26b), and the second ramp (26c) corresponding to the thrust reversal of the blades.
    [9" id="c-fr-0009]
    9. System according to claim 8, wherein the first ramp (26a) and the intermediate ramp (26c) are separated by an upstream stop (28), the intermediate ramp and the second ramp (26b) are separated by a downstream stop ( 30), and the intermediate ramp has a slope inclined downstream with respect to a longitudinal axis of the jack.
    [10" id="c-fr-0010]
    A turbomachine comprising at least one set of adjustable-orientation blower blades and a blower blade orientation control system according to any one of claims 1 to 9.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2763893B1|2017-01-11|Aircraft propeller engine with pitch-changing mechanism
    EP3400170B1|2019-09-11|System for controlling the orientation of the fan blades of a turbine engine with feathering locking pin
    EP2030892B1|2010-03-03|Suspension pylon for an engine beneath an aircraft wing
    EP2640636B1|2018-01-10|Propeller pitch change mechanism having an actuator for biasing the propeller counterweights
    EP2720941B1|2015-08-05|Blade, particularly variable-pitch blade, propellor comprising such blades and corresponding turbomachine
    EP1609719B1|2008-06-18|Method for braking aircraft and turbo fan jet engine for implementing the method
    FR3034140A1|2016-09-30|AIRCRAFT TURBOMACHINE WITH PLANETARY OR EPICYCLOIDAL REDUCER
    CA2902851A1|2014-09-04|Variable-pitch vane
    EP3400168B1|2019-11-20|Pivot blade with variable pitch for a turbofan engine
    FR3082230A1|2019-12-13|NON-HULL ROTOR AIRCRAFT ENGINE WITH ADAPTATION OF STATOR BLADES
    FR3036141B1|2019-08-09|RADIAL CONTROL SHAFT FOR DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A NON - CARBENE BLOWER TURBOMACHINE AND METHOD FOR MOUNTING SUCH A SHAFT.
    FR2755729A1|1998-05-15|Twin flow gas turbine engine
    EP3400169B1|2019-11-13|Blade-pitch locking and feathering mechanism for variable pitch blades of a turbofan
    FR3036093A1|2016-11-18|LEVER ARRANGEMENT FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A NON-CARBONATED BLOWER TURBOMACHINE
    FR3046405A1|2017-07-07|DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
    FR3070368B1|2019-11-22|VARIABLE TIMING PROPELLER
    EP3325793B1|2019-03-20|Aircraft comprising a turbine engine incorporated into the rear fuselage comprising a system for blocking the fans
    FR3046407A1|2017-07-07|FIXED CYLINDER DEVICE FOR SYSTEM FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOMACHINE
    FR2992376A1|2013-12-27|VARIABLE TIMING BLOWER BY DIFFERENTIAL ROTATION OF BLOWER DISKS
    FR3046406A1|2017-07-07|DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
    FR3098850A1|2021-01-22|TURBOMACHINE MODULE EQUIPPED WITH A PROPELLER BLADE PITCH CHANGING SYSTEM AND A BLADE FLAGING DEVICE.
    WO2016181051A1|2016-11-17|Device with radial shaft for controlling the orientation of the fan blades of an unducted fan turbomachine
    EP3412876A1|2018-12-12|Variable geometry compressor of axial turbine engine
    WO2021165616A1|2021-08-26|Turbomachine module equipped with a stator blade pitch-changing system
    FR3046404A1|2017-07-07|DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
    同族专利:
    公开号 | 公开日
    CN108473195A|2018-08-31|
    EP3400170A1|2018-11-14|
    WO2017118810A1|2017-07-13|
    EP3400170B1|2019-09-11|
    US11104416B2|2021-08-31|
    FR3046409B1|2018-02-09|
    US20190009887A1|2019-01-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2872986A|1956-04-26|1959-02-10|Napier & Son Ltd|Control apparatus for aircraft propulsion units embodying variable pitch constant speed airscrews|
    WO2010130893A1|2009-05-15|2010-11-18|Snecma|Unducted propeller including variable pitch blades for a turbine engine|
    US3439745A|1966-03-30|1969-04-22|United Aircraft Corp|Combined propeller pitch lock and low pitch stop system|
    GB1445107A|1973-01-12|1976-08-04|Rolls Royce|Pitch varying mechanisms for a variable pitch fan|
    US3893789A|1973-02-21|1975-07-08|United Aircraft Corp|Pitch change actuator for a variable pitch fan propulsor|
    US3873235A|1973-10-01|1975-03-25|Gen Electric|Variable pitch turbofan engine|
    US6811376B2|2002-03-19|2004-11-02|Hamilton Sundstrand|Actuation system for a controllable pitch propeller|
    FR2911644B1|2007-01-23|2012-06-01|Snecma|TURBOPROPULSEUR COMPRISING A PROPELLED PROPELLER OF BLADES WITH ADJUSTABLE ORIENTATION.|
    WO2009142973A2|2008-05-13|2009-11-26|Rotating Composite Technologies Llc|Fan blade retention and variable pitch system|
    FR2931797B1|2008-05-29|2010-07-30|Snecma|SIMPLIFIED BLADE SETTING CONTROL SYSTEM OF A PROPELLER OF A TURBOMOTEUR FOR AN AIRCRAFT|
    FR2946010B1|2009-05-29|2011-06-24|Snecma|FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER|FR3046408B1|2016-01-05|2018-02-09|Safran Aircraft Engines|DEVICE FOR LOCKING THE FLAGS AND FLOWING BLADES OF REGULATLY ORIENTED BLOWER BLADES OF A TURBOMACHINE PROPELLER|
    US10393137B2|2016-02-12|2019-08-27|General Electric Company|Method and system for integrated pitch control mechanism actuator hydraulic fluid transfer|
    FR3071546B1|2017-09-25|2019-09-13|Safran Aircraft Engines|AXIAL RETENTION OF THE BLOWER TREE IN A GAS TURBINE ENGINE|
    法律状态:
    2017-01-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-07| PLSC| Publication of the preliminary search report|Effective date: 20170707 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-08| ST| Notification of lapse|Effective date: 20210905 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650042|2016-01-05|
    FR1650042A|FR3046409B1|2016-01-05|2016-01-05|SYSTEM FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOMACHINE WITH A FLAGING LOCKING PION|FR1650042A| FR3046409B1|2016-01-05|2016-01-05|SYSTEM FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOMACHINE WITH A FLAGING LOCKING PION|
    CN201780005658.3A| CN108473195A|2016-01-05|2017-01-04|The system with feathering locking bolt for controlling turbogenerator fan blade pitch|
    PCT/FR2017/050013| WO2017118810A1|2016-01-05|2017-01-04|System for controlling the direction of the fan blades of a turbine engine with feathering locking pin|
    US16/067,973| US11104416B2|2016-01-05|2017-01-04|System for controlling the pitch of fan blades of a turbine engine, the system having a feathering-locking peg|
    EP17702674.7A| EP3400170B1|2016-01-05|2017-01-04|System for controlling the orientation of the fan blades of a turbine engine with feathering locking pin|
    [返回顶部]