• 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 present invention relates to a device (1) for regulating a rotational speed, called the rotation speed NG, of a shaft (9) of a gas generator (4) of at least one turbine engine (5). a rotorcraft (3), said rotorcraft (3) comprising: at least one main rotor (2) for generating at least one lift and / or propulsion of said rotorcraft (3) in the air, a control member (6) of a collective pitch of the blades (7) of said at least one main rotor (2), said control member (6) for generating a command setpoint Cp of said collective pitch, at least one turbine engine (5) capable of rotating said at least one main rotor (2), said at least one turbine engine (5) producing at least temporarily a driving torque TQ transmitted to said at least one main rotor (2), and ? measurement means (8) for measuring at any moment a measurement of said engine torque TQ transmitted by said at least one turbine engine (5) to said at least one main rotor (2).
    公开号:FR3061142A1
    申请号:FR1601829
    申请日:2016-12-22
    公开日:2018-06-29
    发明作者:Setareh TAHERI；Nicolas Certain
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    (® Agent (s): GPI & ASSOCIES.
    (54) DEVICE FOR CONTROLLING THE ROTATION SPEED OF A SHAFT OF A GIRAVION TURBOMOTOR GAS GENERATOR, GIRAVION EQUIPPED WITH SUCH A DEVICE AND RELATED METHOD OF REGULATION.
    FR 3 061 142 - A1 (57) The present invention relates to a device (1) for regulating a rotation speed, known as the rotation speed NG, of a shaft (9) of a gas generator (4) d '' at least one turbine engine (5) of a rotorcraft (3), said rotorcraft (3) comprising:
    at least one main rotor (2) for generating at least one lift and / or propulsion of said rotorcraft (3) in the air, a control member (6) of a collective pitch of the blades (7) of said at least one main rotor (2), said control member (6) making it possible to generate a command setpoint Cp of said collective pitch, at least one turbine engine (5) capable of rotating said at least one main rotor (2), said at least one turbine engine (5) producing at least temporarily a motor torque TQ transmitted to said at least one main rotor (2), and measuring means (8) making it possible to measure at each instant a measurement of said engine torque TQ transmitted by said at least one turboshaft engine (5) to said at least one main rotor (2).

    Device for regulating the speed of rotation of a shaft of a rotorcraft gas turbine engine, rotorcraft equipped with such a device and associated method of regulation.
    The present invention relates to a device for regulating the speed of rotation, known as the speed of rotation NG, of a shaft of a gas generator of a turbine engine of a rotorcraft. Such a rotational speed NG is thus directly a function of the quantity of fuel injected into the turbine engine to produce combustion intended to drive at least one main rotor.
    Thus, the present invention is also in the field of methods for regulating the operation of one or more turboshaft engines of a power unit equipping a rotorcraft. Such a power unit includes for example at least one main combustion engine conventionally supplying the rotorcraft the mechanical power necessary to provide at least the drive of one or more rotors equipping the rotorcraft.
    Consequently, the present invention is more specifically part of a regulation device and method providing drive at a variable set speed of at least one main rotor of the rotorcraft, or even providing the case the drive of an anti-torque rotor.
    The main rotor (s) typically provide at least the lift of the rotorcraft, or even also its propulsion and / or its change of attitude in flight in the specific case of a helicopter. The tail rotor typically provides stabilization and guidance of the rotorcraft in yaw and is commonly formed by a rear rotor or at least one propeller in the case of a hybrid rotorcraft which can evolve at high speeds. advancement.
    Conventionally, the operation of the rotorcraft's main turboshaft engines is under the control of a regulating unit, such as a FADEC (short for Full Authority Digital Engine Control). The regulating unit controls the metering of fuel of the main turboshaft engines as a function of a speed setpoint of the shaft of the gas generator of a turboshaft engine for example, hereinafter designated by the speed of rotation NG, relative at a required speed of rotation of the gas generator shaft of a turbine engine. The NG speed setpoint can thus in certain special cases be generated by the regulation unit (FADEC). In other particular cases where, for example, this instruction is variable, it can be generated by all of the electronic, electrical and computer equipment of the rotorcraft, then transmitted to the regulation unit (FADEC) by management means, such as a AFCS (from the acronym Automatic Flight Control System). In this case, the regulation unit (FADEC) makes it possible to regulate the speed of rotation NG.
    Thus, the setpoint of the speed of rotation NG can be transmitted by the management means (AFCS) as a function of the mechanical power requirements of the rotorcraft identified according to the current flight case of the rotorcraft, and in particular as a function of the mechanical power requirements for drive the main rotor. The power consumed by the main rotor can for example be identified from an evaluation on the one hand of the resistant torque that the main rotor opposes against its drive by the power unit and on the other hand its speed of rotation.
    Furthermore, the driving of the main rotor at a speed of rotation NR is a direct function of the speed of rotation NG of the shaft of the gas generator. The rotational speed NG is then variably controlled with respect to a predefined nominal speed NGnom according to the most critical conditions for the rotorcraft corresponding, for example, to complex punctual take-off or landing procedures commonly designated by the expression of procedures. CAT A.
    Indeed, such a significant variation in the speed NG of driving the shaft of the gas generator is exploited to optimize the power level supplied by the turbine engine as a function of the associated flight phase, for example to reduce noise pollution close to the ground and / or improve performance. As an indication, the rotational speed NG of the gas generator shaft can be controlled variable between 5% and 10% of the nominal speed NGnom, or even potentially more depending on the evolution of techniques, and more particularly can be controlled variable according to a range of values potentially between 90% and 115% of the nominal speed NGnom.
    In this regard, we can refer for example to the publication "Enhanced energy maneuverability for attack helicopters using continuous variable rotor speed control" (C.G. SCHAEFER Jr; F.H. LUTZE, Jr; 47th forum American Helicopter Society 1991; p. 1293-1303). According to this document, the performance of a rotorcraft in combat situations is improved by varying the drive speed of the main rotor according to a variation in the air speed of the rotorcraft.
    Reference may also be made, for example, to document US Pat. No. 6,198,991 (YAMAKAWA et al.), Which proposes to reduce the noise pollution generated by a rotorcraft when approaching a touchdown point by varying the speed of rotation of the main rotor.
    We can also refer in this regard for example to document US2007 / 118254 (BARNES GW et al.), Which proposes to vary the speed of rotation of the main rotor of a rotorcraft, according to two values considered as low and high, under predefined conditions of thresholds of values of various parameters linked to flight conditions of the rotorcraft previously identified.
    Again, for example, we can also refer to this subject in document WO2010 / 143051 (AGUSTA SPA et al.), Which proposes varying the speed of rotation of a main rotor equipping a rotorcraft in accordance with a map previously established according to various rotorcraft flight conditions.
    Finally, it is also known, as described by the Applicant in document FR 3 000 466, to use an altimeter to automatically control a variation in the speed of rotation of a rotor in a range between 90% and 110% of a predetermined nominal value.
    Furthermore, the documents FR 2 974 564, GB 2 192 163 and FR 2 981 045 describe other devices or methods for regulating the speed of rotation of a main rotor or rear rotor for rotorcraft.
    However, if such documents describe devices or methods for regulating the speed of rotation of the shaft of the gas generator NG (or by analogy of the speed of rotation of the rotor NR) during the flight of a rotorcraft, such documents do not provide any solution making it possible to adapt the speed setting NG during low power flight phases. However, there are two main situations that can cause a rotorcraft pilot to make it evolve at low power levels.
    The first situation corresponds to the case where at least one rotorcraft engine suddenly breaks down resulting in a loss of power and therefore an inability for the failed turbine engine to rotate the main rotor (s) (main) .
    The second situation is autorotation which is a flight phase which can be voluntarily triggered by the pilot of the rotorcraft. In this flight phase, the main rotor is no longer driven by the turbine engine (s): this is called desynchronization. The rotor is no longer rotated by a turbine engine but by an inversion of the air flow in the rotor. No more engine torque is then transmitted from the turbine engine to the rotor. Such a flight phase then makes it possible to carry out a controlled descent of the rotorcraft thanks to adapted piloting of a collective pitch of the blades of the main rotor (s).
    Generally, an autorotation flight phase is used in the event of failure of the turbine engine (s) by a pilot to maintain a sufficient main rotor speed, This flight phase is then performed by reducing the collective pitch main rotor blades when failure occurs. The transition to the flight phase in autorotation is then made possible thanks to a freewheel allowing the rotor and the turbine engine to be uncoupled under certain conditions. Such a freewheel is indeed a mechanical connection piece between the main power transmission box and the turbine engine which makes it possible to transmit the power from the turbine engine to the main power transmission box while preventing the reverse.
    In general, two shafts nested one inside the other and coaxial are connected to each other by means of this freewheel. One of the shafts is linked to the main power gearbox itself linked to the main rotor and the other shaft is linked to the turbine engine. These two shafts can then have a degree of freedom in rotation or be integral with one another. In the first case, the rotor and the turbine engine are said to be “out of sync”. This desynchronization occurs when the torque transmitted by the turbine engine to the rotor is zero.
    Usually, a pilot therefore performs an autorotation landing when an engine failure occurs. However, such a maneuver being complex to perform, it is necessary for rotorcraft pilots to train there regularly by simulating the engine failure.
    In addition, when descending at high vertical speed, for example during steep approaches characteristic of rotorcraft or in the presence of gusts of wind, the turboshaft engine can unexpectedly desynchronize and surprise the pilot. When the pilot manually re-increases the collective pitch setpoint of the rotor blades, the turbine engine again supplies a non-zero torque. There then occurs a drop in the speed of rotation of the NR rotor on resynchronization of the turboshaft engines (regulated on a free turbine setpoint, called NTL, of a turboshaft engine) with the rotor. Such a fall in the speed of rotation NR can then reach several percent of the nominal value of the speed of rotation NRnom.
    In addition, the generalization of laws regulating the rotor speed NR known as highly variable laws for the needs of acoustic limitations leads the new generations of rotorcraft to evolve at speeds of rotation NR of the rotor lower than their level in hovering, and this to from a forward speed corresponding to the minimum power required for flight and usually designated by the abbreviation Vy.
    For a given flight configuration, this drop in the speed of rotation NR of the rotor on resynchronization is then all the more troublesome as it occurs close to the ground, a zone of reduction of the speed of rotation NR of the rotor in order to respond to acoustic level constraints and where the rotational speed NR of the rotor is already reduced to a value which can reach for example up to 90% of the nominal value NRnom. Such a fall then temporarily brings the speed of rotation NR to very low levels, that is to say much less than 97% of the nominal value NRnom and therefore dangerous to allow piloting of a rotorcraft.
    The risk of unwanted desynchronization during operations with high descent rates has led on rotorcraft of recent generations to display to the pilot the collective step of desynchronization on an indicator of first limitation, also called according to the acronym FLI for First Limit Indicator. However, if the pilot's activity level is already high, which is typically the case during the approach phases, he may not see this display because he must integrate many other visual indications or even look at him outside the rotorcraft during this type of maneuver.
    The object of the present invention is therefore to propose a device making it possible to overcome the limitations mentioned above. In particular, an object of the regulation device or method according to the invention is therefore to allow automatic regulation of the rotational speed NG of a shaft of the gas generator of a rotorcraft turbine engine during flight phases at low power.
    The invention therefore relates to a device for regulating a rotation speed, known as the rotation speed NG, of a shaft of a gas generator of at least one turbine engine of a rotorcraft, such a rotorcraft comprising:
    • at least one main rotor for generating at least one lift and / or propulsion of the rotorcraft in the air, • a member for controlling a collective pitch of the blades of the main rotor (s) (l), l '' control member making it possible to generate a collective pitch control instruction to collectively control an angular orientation of the blades relative to a hub of the main rotor (s), • at least one turbine engine capable of driving in rotation of the main rotor (s), the turboshaft engine (s) at least temporarily producing a TQ engine torque transmitted to the main rotor (s), the TQ engine torque being able to vary as a function of the command setting for the collective pitch of the blades of the main rotor (s) (and), and • measurement means making it possible to measure at any instant a measurement of the motor torque TQ transmitted by the (or) turbine engine (s) to the main rotor (s) (pri ncipals).
    The regulating device then generates at least one control law for a control command for the speed of rotation NG of the shaft of the gas generator of the turbine engine (s), the law (s) ) for controlling the setpoint for controlling the speed of rotation NG being a function of a speed of advance of the rotorcraft in a substantially horizontal direction and of a height of the rotorcraft relative to the ground.
    According to the invention, such a regulation device is remarkable in that it comprises:
    • input means connected with the measurement means, the input means allowing the regulating device to receive and analyze the measurement of the motor torque TQ, • at least one storage unit for storing a first threshold value TQ1 and a second threshold value TQ2, the second threshold value TQ2 being chosen to be greater than the first threshold value TQ1, and • a calculation unit for comparing the measurement of the motor torque TQ with the first and second threshold values TQ1 and TQ2, the calculation unit generating at least two control laws NG1 and NG2 of the speed control command setpoint NG, these at least two control laws NG1 and NG2 being distinct from each other and function of the measurement of the motor torque TQ, a first control law NG1 being implemented at least when the measurement of the motor torque TQ is less than the first threshold value TQ1 and a second control law NG2 being implemented out at least when the measurement of the engine torque TQ is greater than the second threshold value TQ2.
    In other words, such a regulation device makes it possible to constantly compare a current value of the motor torque TQ with the first and second threshold values TQ1 and TQ2 and then to automatically modify the law governing the control of the speed control command NG according to the flight case.
    The first control law NG1 can thus make it possible, for example, to go up at least temporarily during low power flight phases, the speed control command instruction NG at a nominal value when the torque transmitted by the turbine engine to ( x) main rotor (s) (main) goes below the first threshold value TQ1.
    Conversely, the second control law NG2 makes it possible to lower at least temporarily during low power flight phases, the speed control command NG to a level lower than the nominal value, for example equal to 94% of the nominal value, when the torque transmitted by the turbine engine to the main rotor (s) goes above the second threshold value TQ2. Thus in this case, only the second control law NG2 makes it possible to meet requirements for reducing the acoustic level as a function of the height of the rotorcraft relative to the ground and of a speed of advance of the rotorcraft in a substantially horizontal direction.
    Thus, the second control law NG2 will preferably be the control law implemented by default because it corresponds to the flight phases at normal power distinct from the flight phases at low power. Consequently, the second NG2 control law makes it possible to limit the acoustic footprint of the rotorcraft on the outside environment.
    The first control law NG1 is therefore not the control law implemented by default and can then be implemented automatically and temporarily only if a flight condition at low power level, or more precisely torque, occurs voluntarily if the latter corresponds to pilot flight training in autorotation of a rotorcraft or involuntarily in the event of an engine failure, for example.
    Furthermore, the means for measuring the engine torque are generally designated by a torque meter advantageously comprising an electromagnetic sensor making it possible to measure a torsional deformation of a shaft for transmitting the engine torque generated by the rotorcraft (or) turboshaft engines. . Such a sensor can be a Hall effect probe generating electromagnetic pulses, the duration of which is a function of the relative positioning of notches and complementary teeth formed at the circumference of two facing pieces, secured respectively with two ends of a transmission shaft. engine torque.
    The input means are generally formed by an electronic data acquisition card with which the electromagnetic sensor can communicate and transmit a signal representative of its measurement. Such input means can then be connected by wired voice with the measurement means or even include a wireless communication module so as to communicate with the measurement means by a wireless communication protocol.
    Advantageously, the first threshold value TQ1 can be between 5 and 15% of a maximum torque value TQmax able to be generated by the turbine engine (s).
    Thus, such a first threshold value is able to correspond to a flight phase close to very low powers, implying, if the pilot persists in his maneuver, the desynchronization between the (or) turbine engine (s) and the (or ) main rotor (s). It is then certain to be able to detect a flight situation requiring modification of the speed control command NG. This modification then makes it possible either to alert the pilot that he will soon reach this desynchronization if his maneuver was not voluntary, or to be able to anticipate and compensate for the fall in the speed of rotation NG of the gas generator shaft which will then occur upon resynchronization.
    In practice, the second threshold value TQ2 can be between 10 and 20% of a maximum torque value TQmax capable of being generated by the turbine engine (s).
    In this way, the second threshold value TQ2 is important enough to identify a distinct flight phase and distant from the instant of desynchronization carried out between the (or) turbine engine (s) and (or) main rotor (s) (main). Consequently, it is certain that the need for modifying the speed control command NG is eliminated.
    According to a particular embodiment of the invention, the regulating device can implement the first control law NG1 when the measurement of the engine torque TQ falls below the first threshold value TQ1 and as long as the measurement of the engine torque TQ remains below the second threshold value TQ2.
    In other words, the first control law NG1 is implemented for an indefinite period which is a function of the current value of the engine torque TQ.
    According to an advantageous characteristic of the invention, the regulating device can implement the second control law NG2 when the measurement of the engine torque TQ passes above the second threshold value TQ2 and as long as the measurement of the engine torque TQ remains above the first threshold value TQ1.
    Similarly, the second control law NG2 is implemented for an indefinite period which is a function of the current value of the motor torque TQ.
    As already mentioned, the invention also relates to a rotorcraft comprising:
    • at least one main rotor for generating at least one lift and / or propulsion of the rotorcraft in the air, • a member for controlling a collective pitch of the blades of the main rotor (s) (l), l '' control member making it possible to generate a collective pitch control instruction to collectively control an angular orientation of the blades relative to a hub of the main rotor (s), • at least one turbine engine capable of driving in rotation the main rotor (s) main (main), the turbine engine (s) producing at least temporarily a TQ engine torque transmitted to the main rotor (s), the motor torque TQ being able to vary as a function of the command setting for the collective pitch of the blades of the main rotor (s) (main), • measuring means making it possible to measure a measurement of the motor torque at all times TQ transmitted by the turbine engine (s) to the main rotor (s) cipal (main), and • a regulation device generating at least one control law for a control command for a rotation speed, known as the rotation speed NG, of a shaft of a gas generator of the (or of) turboshaft engine (s), the law (or laws) for controlling the setpoint for controlling the speed of rotation NG being a function of a speed of advance of the rotorcraft in a substantially horizontal direction and a height rotorcraft in relation to the ground.
    According to the invention, such a rotorcraft is remarkable in that the device for regulating the speed of rotation NG is as described above.
    The invention also relates to a method of regulating a rotational speed, called rotational speed NG, of a shaft of a gas generator of at least one turbine engine of a rotorcraft, such a rotorcraft comprising:
    • at least one main rotor for generating at least one lift and / or propulsion of the rotorcraft in the air, • a member for controlling a collective pitch of the blades of the main rotor (s) (l), l '' control member making it possible to generate a collective pitch control instruction to collectively control an angular orientation of the blades relative to a hub of the main rotor (s), • at least one turbine engine capable of driving in rotation of the main rotor (s), the turboshaft engine (s) at least temporarily producing a TQ engine torque transmitted to the main rotor (s), the TQ engine torque being able to vary as a function of the command setting for the collective pitch of the blades of the main rotor (s) (and), and • measurement means making it possible to measure at any instant a measurement of the motor torque TQ transmitted by the (or) turbine engine (s) to the main rotor (s) (pri ncipals).
    In addition, such a regulation method generates at least one control law for a control command for the speed of rotation NG of the shaft of the gas generator of the turbine engine (s), the (or them). law (s) for controlling the setpoint for controlling the speed of rotation NG being a function of a speed of advance of the rotorcraft in a substantially horizontal direction and of a height of the rotorcraft relative to the ground.
    According to the invention, this method of regulation is remarkable in that it implements:
    • a storage step for storing in at least one storage unit a first threshold value TQ1 and a second threshold value TQ2, the second threshold value TQ2 being chosen to be greater than the first threshold value TQ1, • a reception step to receive the measurement of the engine torque TQ carried out by the measurement means, • a comparison step for comparing the measurement of the engine torque TQ with the first and second threshold values TQ1 and TQ2, and • a generation step for generating at least two control laws NG1 and NG2 of the rotational speed control setpoint NG, the at least two control laws NG1 and NG2 being distinct from each other and depending on the measurement of the engine torque TQ, a first law control command NG1 being implemented at least when the measurement of the engine torque TQ is less than the first threshold value TQ1 and a second control law NG2 being implemented at least when the measurement of the motor torque TQ is greater than the second threshold value TQ2.
    In other words, the storage step consists in implementing in a memory the threshold values TQ1 and TQ2. These threshold values TQ1 and TQ2 can for example be fixed values or alternatively variable and determined according to laws which depend on external parameters such as the force of the wind, the temperature of the air or even atmospheric pressure.
    The step for receiving the measurement of the engine torque TQ allows the control device to receive the current value of the engine torque TQ which is effectively transmitted by the turbine engine (s) to the rotor (s). ) main (main).
    The comparison step then makes it possible to compare this current value of the motor torque TQ with the first and second threshold values TQ1 and TQ2.
    Finally, the generation step makes it possible to generate the first and second control laws NG1 and NG2 so that they can then be implemented individually according to the measurement of the current value of the motor torque TQ.
    Advantageously, the first threshold value TQ1 can be between 5 and 15% of a maximum torque value TQmax able to be generated by the turbine engine (s). On the other hand and as already indicated previously, the second threshold value TQ2 can be between 10 and 20% of a maximum torque value TQmax able to be generated by the turbine engine (s).
    According to an advantageous characteristic of the invention, the regulation method can implement the first control law NG1 when the measurement of the engine torque TQ falls below the first threshold value TQ1 and as long as the measurement of the engine torque TQ remains below the second threshold value TQ2.
    In other words, the first control law NG1 is implemented by the regulation method for an indefinite period which is a function of the current value of the motor torque TQ.
    Likewise, the regulation method can implement the second control law NG2 when the measurement of the engine torque TQ passes above the second threshold value TQ2 and as long as the measurement of the engine torque TQ remains above the first value TQ1 threshold.
    Consequently, the second control law NG2 is implemented by the regulation method for an indefinite period which is a function of the current value of the motor torque TQ.
    The invention and its advantages will appear in more detail in the context of the description which follows with examples given by way of indication but not limiting in support of the appended figures in which:
    - Figure 1 is a schematic representation in side view of a rotorcraft according to the invention,
    FIG. 2 is a block diagram illustrating in particular a regulating device according to the invention,
    FIG. 3 of the curves illustrating a regulation of the speed of rotation NG of a shaft of a gas generator of a rotorcraft turbine engine and a corresponding regulation of the speed of rotation NR of a rotor, in accordance with invention,
    - Figure 4 is a schematic representation of a regulatory method according to the invention.
    The elements present in several separate figures are assigned a single reference.
    As already mentioned above, the invention relates to the field of rotorcraft comprising at least one main rotor making it possible to carry out at least the lift of the rotorcraft.
    As shown in FIG. 1, such a rotorcraft 3 comprises a device 1 for regulating the speed of rotation NG of a shaft 9 of a gas generator 4. Such a shaft 9 of the gas generator 4 is arranged at l inside a turboshaft engine 5 and makes it possible to rotate a free turbine secured to an output shaft to drive at least one main rotor 2 of the rotorcraft 3. Thus, the turboshaft engine 5, driving the main rotor in rotation 2, transmits a TQ engine torque which can be variable depending on the conditions and flight phases.
    This main rotor comprises a hub 10 around which blades radially emerge radially 7. The rotation of such a main rotor 2 thus makes it possible to produce a substantially vertical air flow and thus to generate at least one lift in the air of the rotorcraft 3 .
    Piloting this rotorcraft 3 is made possible in particular by a control member 6 of a collective pitch of the blades 7 of the main rotor 2. This control member 6 thus makes it possible to generate a command setpoint Cp of the collective pitch and then allows to simultaneously modify the angular orientation of the blades 7 with respect to the hub 10. The command setpoint Cp of the collective pitch of the blades 7 makes it possible in particular to vary the engine torque TQ transmitted by the turbine engine 5 to the main rotor 2.
    Measuring means 8 then make it possible to measure a measurement of the motor torque TQ at any time. Such measurement means 8 are generally formed by electromagnetic sensors such as torque meters measuring the torsional deformations of an output shaft of the turbine engine 5.
    Such a regulation device 1 thus makes it possible to generate at least one law for controlling a setpoint for the speed of rotation NG of the shaft 9 of the gas generator 4 of the turbine engine 5, this law of control being a function on the one hand a forward speed V of the rotorcraft 3 in a substantially horizontal direction Y and on the other hand a height z of the rotorcraft relative to the ground S. Such a forward speed V of the rotorcraft 3 is then variable and can exceed a predetermined threshold value Vy corresponding to a particular forward speed allowing the rotorcraft to fly with a minimum power level of the turbine engine.
    In fact, to limit the acoustic footprint of a rotorcraft to a height above the ground of less than 600 feet for example and when the forward speed V of the rotorcraft 3 is greater than the predetermined threshold value Vy, it is advantageous to reduce the speed control command NG. Such a reduction in the control command for the speed of rotation NG then also results in a reduction in the sound level (decibels) generated by the rotorcraft 3.
    Furthermore, as shown in FIG. 2, the regulating device 1 comprises input means 11 connected with the measuring means 8 allowing the regulating device 1 to receive and analyze the measurement of the engine torque TQ. In addition, the regulating device 1 also comprises at least one storage unit 12 for storing a first threshold value TQ1 and a second threshold value TQ2. The second threshold value TQ2 is chosen to be greater than the first threshold value TQ1.
    Such a regulation device 1 also includes a calculation unit 13 for comparing the measurement of the motor torque TQ with the first and second threshold values TQ1 and TQ2. This calculation unit 13 then generates at least two control laws NG1 and NG2 of the speed control command setpoint NG. The at least two control laws NG1 and NG2 are chosen distinct from each other and depends on the measurement of the engine torque TQ. A first control law NG1 is thus implemented at least when the measurement of the motor torque TQ is less than the first threshold value TQ1 and a second control law NG2 is in turn implemented at least when the measurement of said torque motor TQ is greater than the second threshold value TQ2.
    As already mentioned and as shown in FIG. 3, the engine torque TQ is a function, for the same flight case, of the command setpoint Cp of the collective pitch of the blades 7 of the main rotor 2.
    Thus when the pilot of the rotorcraft 3 begins to reduce the command setpoint Cp of the collective pitch of the blades 7, the engine torque TQ transmitted to the main rotor 2 also decreases. At an instant t1, the motor torque TQ is then equal to the first threshold value TQ1 then it continues to decrease below this first threshold value TQ1.
    Likewise at time t1, the control law NG1 of the speed control command setpoint NG then automatically goes from a low value of 94% to meet acoustic requirements at a nominal value of 100%.
    At time t2, the engine torque TQ transmitted to the main rotor 2 is canceled and then begins a phase of desynchronization between the turbine engine 5 and the main rotor 2. Furthermore, a rotation speed NR of the main rotor 2 continues as to it increase to a maximum value which can for example correspond to 110% of the nominal value. Indeed, this increase in the actual speed of rotation NR of the main rotor 2 is generated by the air flow passing through the rotor which is caused by the rapid descent of the rotorcraft 3.
    Then, from an instant t3, an action on the control member 6 of the collective pitch of the blades 7 then generates an increase in the setpoint Cp of the collective pitch and consequently an increase in the motor torque TQ transmitted to the main rotor 2 .
    Still from time t3 the actual rotation speed NR of the main rotor 2 drops and the main rotor 2 begins to be gradually driven in rotation by the turbine engine 5 towards a nominal rotation speed of 100% temporarily preventing a fall in the actual rotation speed NR below the minimum value of 94% at which the main rotor 2 was initially driven before time t1.
    Finally, from time t4, corresponding to a measurement of the motor torque TQ equal to the second threshold value TQ2, the control law NG1 of the setpoint for the speed of rotation NG is then reduced from its nominal value by 100 % up to a low value of 94% allowing a reduction in the sound level (decibels) produced by rotorcraft 3 in flight.
    As shown in FIG. 4, the invention also relates to a regulation method 20 making it possible to generate at least one control law for a command setpoint for controlling the speed of rotation NG of the shaft 9 of the gas generator 4 of the turboshaft engine 5. Such a control law for the setpoint for controlling the speed of rotation NG is a function of a forward speed V of the rotorcraft 3 in a substantially horizontal direction and of a height z of the rotorcraft 3 relative to the ground S.
    Such a regulation method 20 implements:
    • a storage step 21 for storing in at least one storage unit 12 a first threshold value TQ1 and a second threshold value TQ2, the second threshold value TQ2 being chosen to be greater than the first threshold value TQ1, • a step reception 22 to receive the measurement of the engine torque TQ carried out by the measurement means 8, • a comparison step 23 for comparing the measurement of the engine torque TQ with the first and second threshold values TQ1 and TQ2, and • a step of generation 24 to generate the at least two control laws NG1 and NG2 of the speed control command instruction NG.
    Naturally, the present invention is subject to numerous variations as to its implementation. Although several embodiments have been described, it is understood that it is not conceivable to identify exhaustively all the possible modes. It is of course conceivable to replace a means described by an equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Device for regulating (1) a rotational speed, called the rotational speed NG, of a shaft (9) of a gas generator (4) of at least one turboshaft engine (5) of a rotorcraft (3), said rotorcraft (3) comprising:
    • at least one main rotor (2) for generating at least one lift and / or propulsion of said rotorcraft (3) in the air, • a control member (6) of a collective pitch of the blades (7) of said at least a main rotor (2), said control member (6) making it possible to generate a command setpoint Cp of said collective pitch to collectively control an angular orientation of the blades (7) relative to a hub (10) of said at least one main rotor (2), • at least one turbine engine (5) capable of rotating said at least one main rotor (2), said at least one turbine engine (5) producing at least temporarily a motor torque TQ transmitted to said at least one main rotor (2), said motor torque TQ being able to vary as a function of said command setpoint Cp of said collective pitch of the blades (7) of said at least one main rotor (2), and • measuring means (8) making it possible to measure at all times a measurement of said engine torque TQ transmitted by said at least one turbine engine (5) to said at least one main rotor (2), said regulating device (1) generating at least one control law for a command setpoint for controlling said speed of rotation NG of said shaft (9) of said generator gas (4) of said at least one turboshaft engine (5), said at least one control law of said speed control instruction NG being a function of a forward speed V of said rotorcraft (3) in a direction Y substantially horizontal and of a height z of said rotorcraft (3) relative to the ground S, characterized in that said regulating device (1) comprises:
    • input means (11) connected with the measurement means (8), said input means (11) allowing said regulation device (1) to receive and analyze said measurement of said motor torque TQ, • at at least one storage unit (12) for storing a first threshold value TQ1 and a second threshold value TQ2, said second threshold value TQ2 being chosen to be greater than said first threshold value TQ1, and • a calculation unit (13) to compare said measurement of said motor torque TQ with said first and second threshold values TQ1 and TQ2, said calculation unit (13) generating at least two control laws NG1 and NG2 of said rotation speed control instruction NG, said at at least two control laws NG1 and NG2 being distinct from each other and a function of said measurement of said engine torque TQ, a first control law NG1 being implemented at least when said measurement of said engine torque TQ is less ieure to said first threshold value TQ1 and a second control law NG2 being implemented at least when said measurement of said engine torque TQ is greater than said second threshold value TQ2.
    [2" id="c-fr-0002]
    2. Device according to claim 1, characterized in that said first threshold value TQ1 is between 5 and 15% of a maximum torque value TQmax able to be generated by said at least one turbine engine (5).
    [3" id="c-fr-0003]
    3. Device according to any one of claims 1 to 2, characterized in that said second threshold value TQ2 is between 10 and 20% of a maximum torque value TQmax able to be generated by said at least one turbine engine ( 5).
    [4" id="c-fr-0004]
    4. Device according to any one of claims 1 to 3, characterized in that said regulation device (1) implements said first control law NG1 when said measurement of said motor torque TQ falls below said first threshold value TQ1 and as long as said measurement of said motor torque TQ remains below said second threshold value TQ2.
    [5" id="c-fr-0005]
    5. Device according to any one of claims 1 to 4, characterized in that said regulation device (1) implements said second control law NG2 when said measurement of said motor torque TQ passes above said second threshold value TQ2 and as long as said measurement of said motor torque TQ remains above said first threshold value TQ1.
    [6" id="c-fr-0006]
    6. Rotorcraft (3) comprising:
    • at least one main rotor (2) for generating at least one lift and / or propulsion of said rotorcraft (3) in the air, • a control member (6) of a collective pitch of the blades (7) of said at least a main rotor (2), said control member (6) making it possible to generate a command setpoint Cp of said collective pitch to collectively control an angular orientation of the blades (7) relative to a hub (10) of said at least main rotor ( 2), • at least one turbine engine (5) capable of rotating said at least one main rotor (2), said at least one turbine engine (5) producing at least temporarily a motor torque TQ transmitted to said at least one main rotor ( 2), said motor torque TQ being able to vary as a function of said command setpoint Cp of said collective pitch of the blades (7) of said at least one main rotor (2), • measuring means (8) making it possible to measure at each instant a measurement of said motor torque TQ transmitted by said to m oins a turbine engine (5) to said at least one main rotor (2), and • a regulation device (1) generating at least one control law for a control command for a rotation speed, called rotation speed NG , of a shaft (9) of a gas generator (4) of said at least one turboshaft engine (5), said at least one control law of said control command for the speed of rotation NG being a function of a speed of advancement V of said rotorcraft (3) in a substantially horizontal direction Y and of a height z of said rotorcraft (3) relative to the ground S, characterized in that said device for regulating (1) the speed of rotation NG is according to any one of claims 1 to 5.
    [7" id="c-fr-0007]
    7. Method for regulating (20) a rotation speed, known as the rotation speed NG, of a shaft (9) of a gas generator (4) of at least one turboshaft engine (5) of a rotorcraft (3), said rotorcraft (3) comprising:
    • at least one main rotor (2) for generating at least one lift and / or propulsion of said rotorcraft (3) in the air, • a control member (6) of a collective pitch of the blades (7) of said at least a main rotor (2), said control member (6) making it possible to generate a command setpoint Cp of said collective pitch to collectively control an angular orientation of the blades (7) relative to a hub (10) of said at least main rotor ( 2), • at least one turbine engine (5) capable of rotating said at least one main rotor (2) to generate at least one lift and / or propulsion of said rotorcraft (3), said at least one turbine engine (5) producing at least temporarily a motor torque TQ transmitted to said at least one main rotor (2), said motor torque TQ being able to vary as a function of said command setpoint Cp of said collective pitch of the blades (7) of said at least one main rotor ( 2), and • measuring means (8) making it possible to measuring at all times a measurement of said engine torque TQ transmitted by said at least one turbine engine (5) to said at least one main rotor (2), said regulation method (20) generating at least one control law for a control setpoint of said speed of rotation NG of said shaft (9) of said gas generator (4) of said at least one turbine engine (5), said at least one control law of said command to control the speed of rotation NG being a function of forward speed V of said rotorcraft (3) in a substantially horizontal direction and of a height z of said rotorcraft (3) relative to the ground S, characterized in that said method of regulation (20) implements:
    • a storage step (21) for storing in at least one storage unit (12) a first threshold value TQ1 and a second threshold value TQ2, said second threshold value TQ2 being chosen to be greater than said first threshold value TQ1 , • a reception step (22) for receiving said measurement of said motor torque TQ carried out by said measuring means (8), • a comparison step (23) for comparing said measurement of said motor torque TQ with said first and second values of threshold TQ1 and TQ2, and • a generation step (24) for generating at least two control laws NG1 and NG2 of said speed control command instruction NG, said at least two control laws NG1 and NG2 being distinct l ' one of the other and a function of said measurement of said engine torque TQ, a first control law NG1 being implemented at least when said measurement of said engine torque TQ is less than said first value of threshold TQ1 and a second control law NG2 being implemented at least when said measurement of said motor torque TQ is greater than said second threshold value TQ2.
    [8" id="c-fr-0008]
    8. Method according to claim 7, characterized in that said first threshold value TQ1 is between 5 and 15% of a maximum torque value TQmax able to be generated by said at least one turbine engine (5).
    [9" id="c-fr-0009]
    9. Method according to any one of claims 7 to 8, characterized in that said second threshold value TQ2 is between 10 and 20% of a maximum torque value TQmax able to be generated by said at least one turbine engine ( 5).
    [10" id="c-fr-0010]
    10. Method according to any one of claims 7 to 9, characterized in that said method of regulation (20) implements said first control law NG1 when said measurement of said motor torque TQ falls below said first threshold value TQ1 and as long as said measurement of said motor torque TQ remains below said second threshold value TQ2.
    [11" id="c-fr-0011]
    11. Method according to any one of claims 7 to 5 10, characterized in that said regulation method (20) implements said second control law NG2 when said measurement of said engine torque TQ passes above said second value of threshold TQ2 and as long as said measurement of said motor torque TQ 10 remains above said first threshold value TQ1.
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    同族专利:
    公开号 | 公开日
    CA2986771C|2018-12-04|
    PL3339182T3|2019-10-31|
    EP3339182B1|2019-05-22|
    US20180178908A1|2018-06-28|
    US10752342B2|2020-08-25|
    EP3339182A1|2018-06-27|
    FR3061142B1|2019-01-25|
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    法律状态:
    2017-12-21| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-29| PLSC| Publication of the preliminary search report|Effective date: 20180629 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210806 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1601829A|FR3061142B1|2016-12-22|2016-12-22|DEVICE FOR REGULATING THE ROTATION SPEED OF A TREE OF A GIRAVION TURBOMOTEUR GAS GENERATOR, GIRAVION EQUIPPED WITH SUCH A DEVICE AND METHOD OF REGULATING THE SAME|
    FR1601829|2016-12-22|FR1601829A| FR3061142B1|2016-12-22|2016-12-22|DEVICE FOR REGULATING THE ROTATION SPEED OF A TREE OF A GIRAVION TURBOMOTEUR GAS GENERATOR, GIRAVION EQUIPPED WITH SUCH A DEVICE AND METHOD OF REGULATING THE SAME|
    PL17203414T| PL3339182T3|2016-12-22|2017-11-23|Device for controlling the rotational speed of a shaft of a gas generator of a rotorcraft turboshaft engine, rotorcraft provided with such a device and associated control method|
    EP17203414.2A| EP3339182B1|2016-12-22|2017-11-23|Device for controlling the rotational speed of a shaft of a gas generator of a rotorcraft turboshaft engine, rotorcraft provided with such a device and associated control method|
    CA2986771A| CA2986771C|2016-12-22|2017-11-23|Shaft rotation speed regulation device for a gas turbine generator in a rotorcraft, rotorcraft equipped with such a device and associated regulation method|
    US15/835,575| US10752342B2|2016-12-22|2017-12-08|Device for regulating the speed of rotation of a gas generator shaft of a rotorcraft turboshaft engine, a rotorcraft provided with such a device, and an associated method of regulation|
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