• 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:
    A pitch actuating system (22) for a turbomachine propeller (10), comprising an actuator (24) having a movable portion (26) configured to be connected to propeller blades (14) for moving in rotation relative to the pitch pitch axes (B) of the blades, characterized in that the actuator is an electromechanical actuator, and comprises first electric pitch control means (36), which comprise at least two electric motors (40a, 40b) driving a common rotor (30), and a transmission screw (26) driven in rotation by said common rotor, and in that the system further comprises a nut (28) traversed by said transmission screw and configured to cooperate with the blades for their displacement.
    公开号:FR3050433A1
    申请号:FR1653470
    申请日:2016-04-20
    公开日:2017-10-27
    发明作者:Wergifosse Huguette De
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Simplified step actuation system for a turbomachine propeller
    TECHNICAL AREA
    The present invention relates to a pitch actuation system for a turbomachine propeller, such as a turboprop.
    STATE OF THE ART
    A turboprop engine comprises at least one propeller having a hub and blades carried by the hub and extending substantially radially outwardly with respect to the hub and the axis of rotation of the propeller.
    The turboprop engine is generally equipped with a propeller pitch actuation system, also known as the angular setting system of the propeller blades. The regulation of the pitch of the propeller blades makes it possible to improve their efficiency by guaranteeing a rotational speed of the propeller for each phase of flight.
    Each blade is movable in rotation about an axis, generally radial, between a first relief position called feathering in which it extends substantially parallel to the axis of rotation of the propeller, and a second position in which it is strongly inclined with respect to this axis. It can adopt any position between these two extreme positions.
    In the present art, the actuation system used is a hydraulic system, which is relatively complex and has several disadvantages. This system comprises an actuator whose movable part is connected to the blades of the propeller for their setting.
    The actuation system must not only be able to provide the step control function but also the blade feathering backup function. The step actuation system therefore comprises an auxiliary system for the emergency function.
    Failure related to hydraulic leakage, a common mode between the pitch control system and the auxiliary system, must be covered. In the absence of a source of pressure, it is essential to add counterweights to the blades to ensure the feathering function.
    The pitch actuation system shall also provide protection functions in the event of overspeed, in the event of a stationary engine, in the event of failure of the FADEC computer (acronym for Full Authority Digital Engine Control), and ensure the limitation of small steps in flight. A set of mechanical systems and hydraulic systems are therefore part of the pitch actuation system to perform these functions in the current art.
    The step control system is also subject to very stringent failure rate requirements, which involve redundancies and additional protection systems.
    In conclusion, the technology and operating principle of a hydraulic propeller pitch actuation system are currently complex. A multitude of hydraulic components integrate these systems.
    The present invention overcomes these drawbacks and provides a solution to all or part of the problems of the current technique described below.
    The first problem (Problem A) is the stringent FHA (acronym for Functional Hazard Assessment) string control requirements, which involve robust architectures with redundancy.
    The second problem (problem B) concerns the feathering function, which must be ensured even after a failure of the step control means.
    The third problem (problem C) concerns the risk of blockage of the moving part of the actuator. In a hydraulic system, the rotation of a blade of the helix is obtained by the translation of an eccentric at the foot of the blade. Axial locking of the hydraulic cylinder is considered a failure.
    Furthermore, in a hydraulic system, the rotation of the propeller is transmitted to the hydraulic actuator positioned in the rotating mark (piston and body without angular displacement). This cylinder is fed by pipes via a hydraulic slide positioned in the fixed reference. In this hydraulic concept, the rotation of the propeller does not cause a shift of the pitch of the propeller. The fourth problem (problem D) concerns the management of this phenomenon.
    Finally, the fifth problem (problem E) concerns protection functions other than that covering the failure of the step control, which require additional mechanical and hydraulic devices in a hydraulic system of the current technique.
    SUMMARY OF THE INVENTION The invention proposes a pitch actuation system for a turbomachine propeller, comprising an actuator whose moving part is configured to be connected to blades of the propeller with a view to moving them in rotation relative to each other. to the pitch pitch axes of the blades, characterized in that the actuator is an electromechanical actuator, and comprises: - first electric pitch control means, which comprise at least two electric motors for driving a rotor common, and - a transmission screw rotated by said common rotor, and in that the system further comprises a nut traversed by said transmission screw and configured to cooperate with the blades for their displacement. The hydraulic actuator of the prior art is thus replaced by an electromechanical actuator whose movable part comprises a transmission screw. The rotational movement of the blades is obtained by a translation of the nut on the transmission screw which is rotated by the rotor common to the electric motors.
    This electromechanical concept, thanks to the electrical redundancy at the level of the electric motors, makes it possible to respect the reliability requirements FHA (problem A). To preserve a simple architecture, it is here propose to communicate the rotors of electric motors. This makes it possible to keep only one transmission chain and to have a relatively compact system. The proposed concept offers this advantage.
    The proposed system is preferably capable of providing the reliability required by electrical redundancy both at the level of the electrical components at the level of the control and independent power circuits controlled by a computer. This system is then able to perform its step control function even in the event of a short circuit in the power supply.
    This electromechanical concept may require no mechanical energy from the turbomachine. The cases of failure of the loss of engine power and the engine at a standstill can therefore be provided via a protective case by the nominal electromechanical system without any additional device. This electromechanical concept also makes it possible to cover the overspeed case and the failure of the FADEC without any additional device.
    In a hydraulic system, the rotation of a blade of the helix is obtained by the translation of an eccentric at the foot of the blade. The failure resulting from the axial blocking of the hydraulic cylinder (problem C), which generates this translation, is considered extremely unlikely. This low value of the failure rate seems to be consolidated by feedback. With the system according to the invention, the basic system may not include redundancy of the transmission screw. It is also assumed that the failure rate of the latter is low, which could be demonstrated by the low failure rates based on applications that incorporate transmission screws.
    Concerning the problem E, the proposed concept does not require any additional device unlike the hydraulic system, to cover the protection functions other than that covering the failure of the step control. In a hydraulic system, the case of engine stopped or loss of engine power leads to a suppression of the hydraulic power of the pump coupled to the engine, an auxiliary system is expected. In an electromechanical system, for these cases of failure, the electrical energy is delivered by an independent source. The feathering function therefore remains active to cover these cases of failure, preferably via a protective case. In a hydraulic system, the overspeed case is covered by a mechanical counterweight system. In the electromechanical system, preferably through a speed feedback, the engine control laws can act on electric pitch control motors via the protective case to provide feathering.
    The system according to the invention can comprise one or more of the following characteristics, taken separately from one another or in combination with each other: said common rotor and / or said transmission screw are guided in rotation by at least one bearing in a housing, preferably a stator; in the latter case, the casing of the actuator is fixed while the nut mounted on the transmission screw is integral in rotation with the propeller; to prevent this rotation of the nut causes a translation thereof on the transmission screw and therefore a variation of the pitch of the blades, it is necessary that the transmission screw is kept rotating continuously and therefore the electric motors running continuously ; the maintenance of the pitch therefore requires continuous rotation of the rotors of the motors; the control of the pitch is controlled by the differences in rotational speeds between the propeller and the electric motors (which therefore provides a solution to the aforementioned problem D), - said common rotor is connected to the transmission screw by a gearbox, by planetary example, said first electrical means and said reducer are surrounded by said housing, said first electrical means comprise at least two resolvers, said electric motors are synchronous machines; the choice of the technology and the strategy of the sizing of the electrical means make it possible to minimize the short-circuiting torque and to lead to reasonable motor sizes; the actuator furthermore comprises second electric means for feathering the blades which comprise at least one electric motor, such as an asynchronous machine, driving said common rotor; the choice of the electric machine of the feathering makes it possible to reduce the control box and to eliminate any resistive torque related to a short-circuiting (problem B), - said second electrical means are surrounded by said casing, - said two motors The electrical controls are respectively connected to two electronic control units which are each configured to be active when the other is passive, and vice versa.
    The present invention also relates to a turbomachine, such as a turboprop, comprising a propeller whose blades are variable pitch and a system as described above, wherein the nut cooperates with eccentric provided on support plates and rotation of the blades.
    The present invention finally relates to a method for actuating blade pitch of a turbomachine propeller, by means of a system as described above, comprising the steps of: - maintaining the pitch of the blades by synchronizing the speed first electric means with the speed of the propeller, so that said common rotor and the propeller rotate at the same angular speed, and - change the pitch of the blades by desynchronizing the regime of the first electrical means of the speed of the helix, so that said common rotor rotates at an angular velocity different from that of the helix.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: Figure 1 is a partial schematic half-view in axial section of a blade pitch actuation system associated with a turbomachine propeller, and represents a first embodiment of the invention; FIG. 2 is a partial schematic half-view in axial section of a blade pitch actuation system associated with a turbomachine propeller, and represents a second embodiment of the invention; and - Figure 3 is a block diagram showing the general architecture of the actuating system according to the invention and electrical control means of this system.
    DETAILED DESCRIPTION
    We first refer to Figure 1.
    A propeller 10 of a turbomachine, and in particular a turboprop engine, is generally non-ducted and comprises a movable hub 12 (arrow Θ1 in FIG. 1) with axis A of rotation, the hub carrying blades 14 which extend substantially radially through relative to the axis A. Each blade 14 is connected at its radially inner end to a substantially cylindrical plate 16 for supporting and guiding the blade in rotation in order to rotate in rotation about an axis B, in this case substantially radial. . The plate 16 of each blade 14 is mounted in a housing of the hub 12 and is centered and guided in this housing by bearings 18 extending around the axis B. The radially inner end of each blade comprises an eccentric 20. This is integrally connected to the plate 16 and an actuating system 22 can move it in rotation about the axis B. The displacement of the eccentrics 20 causes a rotational movement of the plates 16 and therefore the blades 14 around the axes B. Each blade 14 can be wedged at a given pitch or position about its axis B, between two extreme positions, one of which, called feathering, corresponds to the case where the rope of the cross section of the blade extends substantially parallel to the axis A.
    In the prior art, the actuation system was hydraulic, and had many disadvantages. Figure 1 shows a first embodiment of the invention including the use of an electromechanical actuating system.
    The actuating system 22 of FIG. 1 comprises an electromechanical actuator 24 whose moving part comprises a transmission screw 26 which is associated with a nut 28 is guided in translation relative to the hub 12 and configured to cooperate with the eccentrics 20 of the blades 14 for rotational movement relative to the axis B. The nut 28 comprises housings for receiving the eccentric 20 and to drive them during the movements of the nut 28. Each housing receives, for example, an eccentric finger 20 of the corresponding blade 14, each finger being arranged projecting in the housing. The nut is thus integral in movement of the blades, and therefore of the propeller when it is rotated relative to the axis A. The nut 28 is thus arranged to be rotatable relative to the axis A in a fixed landmark.
    The transmission screw 26 extends along the axis A and is rotatable relative to the axis A. It passes through the nut 28 and therefore comprises a thread complementary to that of the nut. The nut 28 is thus also arranged to be movable in translation relative to the axis A in the same fixed reference. The transmission screw 26 advantageously has a reversibility function in that it is able to be subjected by the actuator to a torque so as to cooperate with the nut and move it, and also to be subjected by the nut to axial forces causing a rotation of the transmission screw. On this point, it is distinguished from an endless screw which has a function of irreversibility.
    It will be understood that the rotation of the transmission screw 26 (arrow 0 of FIG. A) causes the nut 28 to move in translation along the axis A. The rotation of the transmission screw 26 therefore causes the nut to be translated. 28, which in turn causes a displacement of the eccentrics 20 and a rotation of the blades 14 with respect to the axis B. The arrow X 'represents the axial displacement of the nut along the axis A and the arrow Θ1 represents the rotation of a blade 14 about a B axis.
    The transmission screw 26 is driven by a rotor 30 of the actuator 24 which is centered and guided by bearings in a casing 32 of the stator in the example shown. The housing 32 is thus fixed. It has a generally elongated cylindrical shape of axis A.
    The rotor 30 has an elongated shape of axis A and is here guided in the housing 32 by at least one bearing 34. The bearing 34, here bearing and more specifically with balls, is mounted at the axial end of the actuator opposite to the propeller (left end on the drawing). The actuator 24 comprises first electric means 36 blade pitch control. In the example shown, these electrical means 36 comprise two resolvers 38a, 38b and two electric motors 40a, 40b, which are here synchronous machines. The resolvers 38a, 38b are arranged next to each other and have the common axis, the axis A. The electric motors 40a, 40b are arranged next to each other and also have common axis , axis A. The resolvers 38a, 38b are here arranged between the bearing 34 and the electric motors 40a, 40b.
    Each resolver 38a, 38b comprises a resolver rotor mounted on the common rotor 30, and a resolver stator integral with the housing 32. The resolver rotors and stators are generally composed of coils. In a known manner, a resolver makes it possible to obtain an electrical value from a change of angle of a rotor. A resolver operates as a transformer whose coupling varies with the mechanical angle of the rotor. When the rotor winding is excited with an alternating voltage, an AC voltage is recovered on the stator winding. The redundancy associated with the use of two resolvers 38a, 38b instead of one, makes it possible to guarantee the reliability requirements mentioned above.
    Each electric motor 40a, 40b is here of the synchronous machine type and comprises a rotor mounted on the common rotor 30, and a stator secured to the casing 32. The rotor may consist of permanent magnets or be constituted by a coil supplied with current continuous and a magnetic circuit (electromagnet). To produce current, an external force is used to turn the rotor: its rotating magnetic field induces an alternating electric current in the stator coils. The speed of this rotating field is called "synchronism speed". The speed of synchronism is directly related to the frequency of the power supply. The motors are powered by a system of three-phase currents.
    As can be seen in the drawing, the transmission screw 26 is driven by the common rotor 30 by means of a gear reducer 42, which is here a planetary gear or epicyclic gear. This gearbox 42 comprises a sun shaft 42a integral in rotation with the common rotor 30, an outer ring 42b surrounding the sun shaft and secured to the housing 32, satellites 42c meshing with the sun shaft 42a and the ring 42b and carried by a door -satellites 42d which is here integral in rotation with the transmission screw 26. In the example shown, the transmission screw 26 and the planet carrier 42d are formed in one piece.
    The part comprising the planet carrier 42d and the transmission screw 26 is centered and guided in the housing 32 by a pair of rolling bearings, here ball. These bearings 44 are angular contact. They are inverted and mounted next to each other at the axial end of the actuator located on the side of the propeller 10 (right end in the drawing).
    The actuating system 22 further comprises at least one sensor 46 of the LVDT type (acronym for Linear Variable Differential Transformer). In the example shown, the transmission screw 26 comprises an internal axial bore in which is slidably engaged a LVDT ferromagnetic plunger 46a carried by a rear cover 48 of the actuator 22, which is itself fixed to the housing of stator 32. Although this is not shown, the plunger 46a is surrounded by several windings carried by the transmission screw 26, including at least one primary winding fed by an alternating current and two secondary windings. These coils are preferably redundant to increase the reliability of the system. The axial displacement of the plunger 46a inside the coils, channels the flow and generates voltages in the secondary windings whose amplitudes depend on the position thereof. The sensor 46 thus provides a voltage proportional to the displacement of the plunger 46a.
    In the embodiment of FIG. 1, the turboprop is equipped with an auxiliary system for feathering the blades 14, which is not shown and which comprises counterweights which equip the blades 14 or their plates 16 and which are intended to ensure the emergency flagging of the blades in the event of failure of the actuator 24. This auxiliary system is then mechanical.
    The variant embodiment of FIG. 2 differs from the previous embodiment in that the auxiliary system 50 for feathering the blades 14 is electromechanical. The system 50 is here integrated with the actuator 22 and comprises an electric motor 52, which is preferably an asynchronous machine (not to generate a resistive torque), whose stator is integral with the housing 32 and whose rotor is integral with the common case 30. In the example shown, it is mounted between the rear cover 48 and the bearing 34. The use of the electromechanical system according to the invention for feathering offers the following advantages: the control box is simple and high reliability; the case of short-circuiting is not to be covered, it is not necessary to oversize synchronous machines to cover this case of failure; in the absence of short-circuiting induced by this motor, the rotor can be mounted directly on the rotor axis of the synchronous machines and benefit from the reduction ratio of the gears. There is no necessary addition of reducers.
    In the two embodiments described above, the housing 32 is in a fixed reference and the nut 28 is in the rotating reference of the propeller 10 because it is rotated by the eccentric 20 of the blades 14. For avoid that the nut 28 moves in translation on the transmission screw 26 (which would cause a change in the pitch of the blades), it is necessary that the latter rotates at the same angular speed as the propeller. To maintain the pitch of the blades, it is necessary to synchronize the engine speed 40a, 40b with the speed of the propeller 10. On the contrary, to vary the pitch of the blades, it is necessary to desynchronize the speed of the electric motors of the speed of the 'propeller.
    Reference will now be made to FIG. 3, which schematically represents the electrical block diagram of the operation of the system of each of FIGS. 2 and 3.
    The elements described in the above are designated by the same reference numbers in FIG.
    FIG. 3 shows in particular the control means of the electrical machines of the system, namely, in the case where the redundancy applies to all these machines, two sensors 46 LVDT, two resolvers 38a, 38b, and two electric motors 40a, 40b .
    The control means comprise in particular two segregated electronic control units 54a, 54b which are each connected to a resolver, a sensor and an electric motor, and which have the ability to drive these machines independently.
    The housings 54a, 54b operate in "passive-active" mode. In nominal mode, the pitch is controlled by the control unit 54a for example, and the control unit 54b is in passive mode. In case of failure detected by a position error for example, the housing 54a is deactivated and the housing 54b is activated. The housings 54a, 54b comprise three interlocking local loops: a torque loop using the phase current measurements, a speed loop using the resolver, and a linear position loop using the LVDT sensor. The housings 54a, 54b receive the position instruction respectively of computer housings 56a, 56b and are associated with electrical networks 58a, 58b, to send a current command to the motors 40a, 40b.
    Although this is not shown in FIG. 3, in the case of the embodiment variant of FIG. 2, the control means also comprise an independent power supply device for the electric motor 52.
    This concept of the electromechanical type for the pitch actuation system is very innovative because it offers the following advantages: - Simple and robust architecture with a minimum of electromechanical components, meeting the stringent reliability criteria, - Removing the case of failure related to hydraulic leakage, which required the addition of counterweight for feathering, - removal of counterweights in the case of the variant of Figure 2, and - removal of any additional devices to cover failure cases other than that related to the failure of the step control.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A pitch actuating system (22) for a turbomachine propeller (10), comprising an actuator (24) having a movable portion (26) configured to be connected to propeller blades (14) for to move them in rotation with respect to the axes (B) for pitch pitch setting, characterized in that the actuator is an electromechanical actuator, and comprises: first electric pitch control means (36), which comprise at least two electric motors (40a, 40b) for driving a common rotor (30), and - a transmission screw (26) driven in rotation by said common rotor, and in that the system further comprises a nut (28) traversed by said transmission screw and configured to cooperate with the blades for their displacement.
    [2" id="c-fr-0002]
    The system (22) of claim 1, wherein said common rotor (30) and / or said transmission screw (26) are rotated by at least one bearing (34) in a housing (32), preferably of stator.
    [3" id="c-fr-0003]
    3. System (22) according to one of the preceding claims, wherein said common rotor (30) is connected to the transmission screw (26) by a gearbox (42), for example planetary.
    [4" id="c-fr-0004]
    4. System (22) according to claim 3, in accordance with claim 2, wherein first electrical means (36) and said gear (42) are surrounded by said housing (32).
    [5" id="c-fr-0005]
    5. System (22) according to one of the preceding claims, wherein said first electrical means (36) comprise at least two resolvers (38a, 38b).
    [6" id="c-fr-0006]
    6. System (22) according to one of the preceding claims, wherein said electric motors (40a, 40b) are synchronous machines.
    [7" id="c-fr-0007]
    7. System (22) according to one of the preceding claims, wherein the actuator (24) further comprises second electrical means (50) for feathering the blades, which comprise at least one electric motor (52), such as an asynchronous machine driving said common rotor (30).
    [8" id="c-fr-0008]
    8. System (22) according to one of the preceding claims, wherein said two electric motors (40a, 40b) are respectively connected to two electronic control units (54a, 54b) which are each configured to be active when the other is passive, and vice versa.
    [9" id="c-fr-0009]
    9. Turbomachine, such as a turboprop, comprising a propeller (10) whose blades (14) are variable pitch and a system (22) according to one of the preceding claims, wherein the nut (28) cooperates with eccentrics (20) provided on platens (16) for supporting and rotating the blades.
    [10" id="c-fr-0010]
    10. A method of actuating pitch of the blades of a turbomachine propeller, by means of a system (22) according to one of claims 1 to 8, comprising the steps of: - maintain the pitch of the blades (14 ) by synchronizing the regime of the first electric means (36) with the speed of the propeller, so that said common rotor and the propeller rotate at the same angular speed, and - change the pitch of the blades by desynchronizing the regime first electric means of the speed of the propeller, so that said common rotor rotates at an angular speed (Θ) different from that of the propeller (a).
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    同族专利:
    公开号 | 公开日
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    引用文献:
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    FR2945680A1|2009-05-15|2010-11-19|Snecma|Electromechanical linear actuator for linearly displacing e.g. nozzle flap, of aircraft's turbojet engine, has satellite rollers including helical teeth cooperating with bush's internal thread and external thread of rod's rear end part|
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    FR3049572B1|2016-03-31|2019-07-12|Safran Aircraft Engines|PROPELLER STEM CONTROL SYSTEM|FR3060526B1|2016-12-21|2019-05-10|Safran Aircraft Engines|ELECTROMECHANICAL STEM ACTUATION SYSTEM FOR A TURBOMACHINE PROPELLER|
    FR3060523B1|2016-12-21|2019-05-17|Safran Aircraft Engines|ELECTROMECHANICAL STEM ACTUATION SYSTEM FOR A TURBOMACHINE PROPELLER|
    法律状态:
    2017-04-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-27| PLSC| Search report ready|Effective date: 20171027 |
    2018-03-22| 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 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1653470A|FR3050433B1|2016-04-20|2016-04-20|SIMPLIFIED STEP ACTUATION SYSTEM FOR A TURBOMACHINE PROPELLER|FR1653470A| FR3050433B1|2016-04-20|2016-04-20|SIMPLIFIED STEP ACTUATION SYSTEM FOR A TURBOMACHINE PROPELLER|
    US15/490,746| US10633987B2|2016-04-20|2017-04-18|Simplified pitch actuation system for a turbine engine propeller|
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