• 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 method for stopping an over-speeding rotorcraft engine (10), said engine (10) comprising a gas generator (11) and a power unit (19). When said motor (10) is in operation. a law is established giving a limit derivative which varies as a function of the speed of rotation of the power unit (19). The so-called "current speed" rotation speed reached by the power unit is measured and the time derivative of said so-called "current derivative" rotation speed is determined. The motor (10) is automatically stopped when the limit derivative corresponding to the current speed according to said law (100) is less than or equal to the current derivative.
    公开号:FR3026438A1
    申请号:FR1402172
    申请日:2014-09-26
    公开日:2016-04-01
    发明作者:Bernard Certain
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method for stopping an overspeed engine, such an overspeed safety system, and an aircraft provided with this overspeed safety system. The invention relates to the general technical field of systems ensuring the operational safety of the engines of an aircraft, and in particular the operational safety of a turbine engine of a rotorcraft. The present invention more particularly relates to protection of a power plant in the event of overspeed of an engine. A rotorcraft includes at least one motor for rotating at least one rotor. Such a rotor at least partially ensures the lift of this rotorcraft, or even its propulsion. For example, a twin-engine rotorcraft includes a first engine and a second engine jointly driving a main lift and / or propulsion rotor by a power transmission chain. The first motor and the second motor are generally controlled respectively by a first control unit and a second control unit. Such control units are called "Full Authority Digital Engine Control" in English or more simply "FADEC". Each control unit may comprise a computer and peripheral control and control units interfacing between the cockpit and the associated engine of the aircraft. The engines may be turboshaft engines.
    [0002] A turbine engine conventionally comprises a gas generator. The gas generator comprises successively at least one compressor, a combustion chamber and at least one expansion turbine, the compressor being mechanically connected to the expansion turbine by a motor shaft. In addition, the turbine engine comprises a power unit located downstream of the gas generator. This power unit is sometimes provided with at least one power turbine rotated by the gas leaving the gas generator. This power turbine rotates a working shaft meshing with the power transmission chain which is connected to a rotor. The power turbine is called "free" when this turbine is not connected by a shaft to the gas generator. In case of breakage of the power transmission chain or slip of a freewheel of this particular transmission chain, the speed of rotation of the power turbine of a turbine engine can increase considerably. From a threshold, the skilled person then considers that such a turbine engine is overspeeding, such overspeed can lead to a runaway rotation speed and a burst of the engine. As a result, the aircraft are generally equipped with safety systems in an attempt to limit the impact of such overspeed on the aircraft and its occupants. A mechanical system called "blade shedding" in English is sometimes used on a turbine turbine free turbine. This mechanical system comprises a shielding ring arranged around the free turbine. In addition, each blade of the free turbine is fixed to a hub by a fuse element.
    [0003] Beyond a threshold rotation speed, the fusible elements break. Each blade is then disengaged from the hub. However, these blades remain contained in the motor through the shield.
    [0004] The ejection of the vanes of the free turbine induces a decrease in the rotational speed of this free turbine, and thus makes it possible to stop the overspeed of the free turbine. Nevertheless, the engine is in fact partially destroyed following the ejection of the blades. In addition, stopping the rotation of a free turbine does not necessarily induce the stopping of the engine gas generator. As a result, an electronic shutdown system can be implemented to stop the turboshaft engines to prevent the occurrence of overspeed.
    [0005] The builder of a turbine engine then establishes for example a fixed threshold speed of rotation of the free turbine of this turbine engine. When this threshold is reached, the control unit stops the motor. Document FR 2962165 suggests comparing only the engine torque transmitted by a free turbine to a torque threshold. Nevertheless, the use of a single speed or torque monitoring threshold can induce untimely cuts in the engine, for example when the rotorcraft makes a severe maneuver. Therefore, this monitoring system is sometimes not arranged on a single engine aircraft. On a multi-engine rotorcraft, the shutdown of one engine can be inhibited in case of overspeed cut of another engine to avoid untimely shutdown of other engines. After the shutdown of a first engine, stopping in flight of a second engine is then no longer allowed. In such a case, the second engine can not be stopped in case of overspeed. Such a situation is unlikely but possible. Consequently, if the second engine is subsequently under overspeed condition, this second engine can not be stopped automatically since its protection is inhibited. The second engine may therefore be in an overspeed situation. According to one variant, a pilot can then manually reset an electronic protection system against the overspeed of the second engine to avoid such a situation. In this context, the turbine engine of a single-engine rotorcraft 15 is sometimes equipped with a mechanical protection system of the "blade shedding" type. On the other hand, a single-engined rotorcraft is generally not equipped with an electronic system to avoid an untimely cut of the only engine of the aircraft. Multi-engine rotorcraft may, on the other hand, comprise a mechanical blade-type protection system and an electronic cut-off system. Furthermore, the technological background comprises a protection device which stops an engine in overspeed condition of a comparison between a mechanical power required by the rotorcraft and a predefined power threshold. The mechanical power required by the rotorcraft is calculated according to at least the current or anticipated value of the resisting torque of a main rotor of the rotorcraft.
    [0006] The document FR 2 967 213 describes a control method for controlling an overspeed safety system of an aircraft comprising at least two engines. This method consists in arming the overspeed safety system of the engines, monitoring the engine rotation speed, detecting an overspeed on one of the engines, shutting down the engine in question in the event of such detection and inhibiting the operation of the overspeed safety system for the other engine (s) remaining in operation. The overspeed safety systems of the engines remaining in operation may be rearmed according to one or more safety parameters. The document FR 2 980 174 describes a control method for controlling an overspeed safety system of an aircraft comprising at least two engines. According to this method, a first motor is switched off when a monitoring parameter of this first motor exceeds a first threshold and a second motor distinct from this first motor is switched off when the monitoring parameter of this second motor exceeds a second threshold, the second threshold being greater than said first threshold.
    [0007] In particular, the monitoring parameter is the speed of rotation of the free turbine of a turbine engine. The present invention thus aims at an alternative method for firstly avoiding the bursting of the engines of an aircraft following an overspeed of the engines, and secondly to limit the risk of occurrence of an untimely cut. The invention thus relates to a method for stopping an overspeed rotorcraft engine, said rotorcraft comprising at least one engine, the engine comprising a gas generator and a power unit, the power unit having at least one power turbine being rotated by gases from the gas generator, the power unit having at least one power shaft rotatably connected to the power turbine, said power unit rotating about a longitudinal axis at a speed known as " rotation speed ".
    [0008] According to this method: - prior to a flight, a law is determined providing a so-called derivative derivative "derivative limit" with respect to the time of said rotational speed over at least one range of rotational speeds, the limit derivative being according to said law function of the speed of rotation and varying according to this speed of rotation, during a flight: the speed of rotation known as the "current speed" reached by the power unit is measured, where the derivative with respect to the time of said rotation speed called "current derivative", o when the current speed is located in a said range provided in said law, it automatically stops said motor when the limit derivative corresponding to the current speed according to said law is less than or equal to the current derivative . Unlike a state of the art suggesting comparing the speed of rotation of the power unit with a fixed value, the invention proposes to establish a law providing a limit derivative of this speed of rotation with respect to time as a function of the rotational speed is: DL = f (N2) where "DL" represents said limit derivative, "N2" represents the rotational speed, and "f ()" represents said law. The law can be established by calculation or from tests and feedback of experiences for example.
    [0009] According to this law, the limit derivative can vary according to the speed of rotation. Therefore, this law is implemented on the rotorcraft. In flight, a current speed is determined at each instant following a measurement, and at a relatively high calculation frequency of the order of several tens of times per second, for example. In parallel, the current derivative is determined at each instant. For example, the current derivative is determined at a given instant t using the value of the current speed at that given instant t, and the value of the rotational speed measured at the measurement point t-1 preceding this given instant. When the current speed is within a range provided by the implemented law, the motor is then stopped if the current derivative is greater than or equal to the limit derivative obtained by applying said law by injecting the current speed therein. This condition may tend to limit the risk of inadvertent engine shutdown, while providing a relatively fast trip threshold to be reached, for example following the break in the power transmission chain connecting the motor to a rotor. Indeed, a manufacturer can according to the state of the art compare the rotational speed of the power set to a constant. However, the speed of rotation can increase significantly during a severe maneuver of the rotorcraft without the engine reaches an overspeed requiring its stop. Therefore, a too low threshold can induce an undue stop of the engine during a severe maneuver of the rotorcraft. Conversely, a threshold that is too high can induce a stop occurring late. The implementation of a limit derivative with a non-constant value and a function of the speed of rotation tends to optimize the procedure of automatic shutdown of the motor. Therefore, this method can be implemented both on a multi-engine rotorcraft and a single-engine rotorcraft. On a single-engine rotorcraft, a blade shedding protection is useful to prevent the engine from bursting in overspeed. However, the engine casing can be locally disemboweled due to deformation of the ring of the blade shedding protection system or following a crash. With the gas generator still operating, hot gases can escape from the engine through the orifices generated by this herniation, and may ignite oil or fuel, for example. The claimed process allows the engine to be shut down when overspeed is detected. Therefore, the gas generator is stopped which may tend to reduce the risk of fire after a crash for example. On a multi-engine rotorcraft, the process may tend to limit the risks of undue engine shutdown. Therefore, the rotorcraft may possibly be devoid of a cross-inhibition system likely in rare cases to maintain running an engine overspeed.
    [0010] This method may further include one or more of the following features. Thus, the gas generator being fed by a fuel dispenser, said dispenser being adjustable between a minimum stop inducing a minimum flow of fuel and a maximum stop inducing a maximum flow of fuel, it automatically stops said motor by setting the doser of engine fuel on its minimum stop. For this purpose, the dispenser can be set to reach its minimum flow stop, especially when for a given rotational speed the current derivative reaches or exceeds the limit derivative. Alternatively or in addition, at least one engine comprising a valve on a fuel line, the engine is automatically shut off by closing the valve. Furthermore, each engine being supplied with fuel by at least one pump, each pump is shut down following an automatic shutdown of the engine. For example, all booster pumps arranged in a fuel tank are shut down to avoid spilling fuel in the event of a fuel line rupture. Moreover, the limit derivative can decrease, possibly linearly, between: an intermediate value reached for a speed of rotation called "intermediate speed", and a minimum value reached for a speed of rotation called "maximum permissible speed" of said set of power, the maximum permissible speed being greater than the intermediate speed, the minimum value being lower than the intermediate value. As a result, the limit derivative may be close to the operating range allowed by the manufacturer to reduce the time required to shut down an engine in overspeed. For example, the minimum value is zero. In addition, the motor may not be stopped automatically for a rotational speed lower than a lower threshold regardless of the current derivative. For example, the lower threshold is equal to the intermediate speed previously described. As a result, the motor is never stopped automatically when the rotational speed is lower than the lower threshold. Indeed, the motor is then in a normal operating range. On the other hand, beyond this lower threshold, the speed of rotation is within a range provided by the implemented law. The engine is then likely to be stopped, the stop depending at each instant of the comparison of the current derivative to the derivative limit at this time. In a phase diagram showing the rotational speed on the abscissa and the derivative with respect to time of said rotational speed on the ordinate, this aspect of the law providing the boundary derivative is represented locally by a vertical half-line moving away from the abscissa axis starting from a minimum value of the limit derivative obtained for a speed of rotation equal to the lower threshold, the half-line being positioned at an abscissa equal to the lower threshold.
    [0011] As a result, a failure of the system comparing the current derivative to the limit derivative does not lead to an inadvertent shutdown of the engine under these conditions. Furthermore, the motor is for example stopped automatically for a rotation speed greater than an upper threshold regardless of the current derivative. In a phase diagram showing the rotation speed on the abscissa and the derivative with respect to time of said rotation speed on the ordinate, this aspect of the law providing the boundary derivative is represented by a vertical half-line moving away from the X-axis starting from a maximum value of the limit derivative obtained for a speed of rotation equal to the upper threshold, the half-line being positioned at an abscissa equal to the upper threshold. Beyond the maximum permissible speed, the motor is stopped, regardless of the value of the current derivative. As a result, a system failure comparing the current derivative to the limit derivative does not prohibit motor shutdown in case of excessive rotational speed. For example, the law is established for a speed of rotation between the intermediate speed and the maximum permissible speed, the motor not being stopped automatically for a speed of rotation lower than the intermediate speed whatever the current derivative, the motor is automatically stopped for a rotational speed greater than the maximum permissible speed regardless of the current derivative. Moreover, in a phase diagram presenting the rotation speed on the abscissa and the derivative with respect to time of said rotation speed on the ordinate, the law providing the limit derivative with respect to the speed of rotation takes the form of a curve which is not parallel to the ordinate axis, said curve sharing the plane of the diagram in an authorized operating sector not requiring the stopping of the engine and an unauthorized operating sector requiring the stopping of the engine, said sector unauthorized being located downstream of said curve with respect to the direction of increase of the abscissa, said motor being stopped when an operating point corresponding to the current derivative and the current speed is located in the unauthorized sector. In addition to a method, the invention is directed to an overspeed safety system applying this method. Thus, the invention aims at an overspeed safety system for a rotorcraft engine, this engine comprising a gas generator and a power unit, the power unit having at least one power turbine rotated by the generator of gas, the power unit having at least one power shaft rotatably connected to the power turbine, the overspeed safety system comprising a shutdown system for stopping the operation of the turbine engine, the overspeed safety system comprising a unit treatment connected to the cutoff system. This overspeed safety system comprises a speed sensor for measuring a speed of rotation of the power unit, the processing unit being connected to the speed sensor to implement the method according to the invention by automatically stopping the motor. when the value of the limit derivative corresponding to the current speed is less than or equal to the current derivative.
    [0012] The speed sensor comprises for example an electromagnetic sensor placed in front of a sound wheel rotating in rotation with the rotary member whose speed of rotation is to be measured.
    [0013] Conventionally, a sound wheel is provided with a peripheral zone comprising teeth distributed circumferentially. The passage of the teeth of the voice wheel in front of the electromagnetic sensor modifies the magnetic field produced, and induces an alternating current in a coil of the electromagnetic sensor whose frequency is proportional to the speed of rotation. In addition, the shutdown system may include a fuel dispenser conveying fuel to the gas generator. This shutdown system may also include at least one pump conveying fuel to the gas generator. Furthermore, the processing unit may comprise a logic circuit or the like, or processor-type computing means or equivalent that executes instructions stored in a memory. In particular, the processing unit may be a FADEC of the engine. For the record, a FADEC represents the control unit of a turbine engine, this control unit being called "Full Authority Digital Engine Control" in English. The processing unit is also favorably arranged in parallel with the FADEC to allow the shutdown of an engine in overspeed even in the event of failure of a FADEC. In addition, the overspeed safety system may comprise a shield ring surrounding said power turbine, said power turbine having a plurality of blades, each blade being attached to a fuse member. The overspeed safety system is then provided with an electronic system automatically stopping the engine if necessary, and a mechanical "blade shedding" type system. In addition to an overspeed safety system, the invention is directed to a rotorcraft comprising such a system. Therefore, this rotorcraft comprises at least one rotor, the rotorcraft comprising at least one motor, the motor driving a power transmission chain 10 connected to the rotor. In addition, the rotorcraft comprises at least one overspeed safety system of the type described. previously, each overspeed security system being connected to a motor. For example, each engine is associated with an overspeed security system. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1 a rotorcraft equipped with a single motor; FIG. 2, a rotorcraft equipped with two motors; FIG. 3, a phase diagram explaining the invention. Figure 1 shows an aircraft 1, in particular a rotorcraft. The aircraft components that are not directly concerned by the invention are not shown in the figure in order not to unnecessarily increase this figure. In particular, this aircraft 1 is a rotorcraft comprising a lift rotor 2 and / or propulsion. This rotor 2 is rotated by a power plant comprising at least one motor 10 and a power transmission chain 3. Such a power transmission chain 3 comprises for example a freewheel 56 and a power transmission gearbox 55. The power transmission gearbox 55 is provided with a mast driving a hub of the rotor 2. Therefore, at least one engine 10 is mechanically linked to this power transmission chain 3 The engine 10 of the rotorcraft is in particular a turbine engine . Therefore, the engine 10 comprises a gas generator 11. The gas generator 11 is conventionally provided with at least one compressor 12, a combustion chamber 13 and at least 15 an expansion turbine 14. The turbine 14 is rigidly connected to the compressor 12 by a shaft called "motor shaft 13 '". FIG. 1 shows a single compressor 12 and a single expansion turbine 14. Nevertheless, the number of compressor (s), and expansion turbine (s) can be optimized as required, and in no way restricts the scope of the compressor. 'invention. In addition, the compressor 12, the expansion turbine 14 and the drive shaft 13 'are able to jointly perform a rotary movement about a longitudinal axis AX of the engine 10. More precisely, the compressor 12, the expansion turbine 14 and the motor shaft 13 'are integral in rotation about this longitudinal axis. The gas generator then rotates at a speed N1, this speed Ni corresponding to the speed of the rotating assembly of the gas generator which comprises the compressor 12 as well as the expansion turbine 14 and the drive shaft 13 '. Furthermore, the turbine engine 10 comprises a power unit 19 located downstream of the gas generator. The power assembly is set in motion by the gases generated by the gas generator. The power unit 19 comprises at least one power turbine 15 located downstream of the gas generator. The term "downstream" is to be considered by taking into consideration the direction of flow of the gases within the engine 10. This power turbine can be linked to the gas generator. However, the power turbine is a free turbine independent of this gas generator according to FIG. 1. Thus, the power turbine 15 is integral with a power shaft 16 connected to the power transmission chain 3. Conventionally , the power transmission chain 3 is fixed to the power shaft by a not shown member allowing angular and axial misalignments. FIG. 1 shows a power unit 19 including a single power turbine 15. Nevertheless, the number of power turbine (s) can be optimized as required, and does not in any way limit the scope of the invention. The gases leaving the gas generator then rotate the power unit of the turbine engine about the longitudinal axis AX at a rotation speed N2.
    [0014] Furthermore, the rotorcraft comprises at least one fuel tank 4 for fueling the combustion chamber 13. Therefore, a fuel supply line provided with at least one pump 5 and a metering device 7 connects the tank 4 to the combustion chamber 13. The engine may further include a valve 100 on an internal fuel line. The rotorcraft is furthermore provided with an overspeed safety system 20 to avoid an overspeed of the engine 10. This overspeed safety system 20 comprises a processing unit 21. The processing unit may comprise a logic circuit or the like. . According to the variant of Figure 1, the processing unit 21 is for example provided with a storage device 23 and a computer 22. The computer may for example comprise a processor or equivalent executing instructions stored on the device by applying the method according to the invention. This storage device may include a non-volatile memory storing such instructions and a volatile memory storing parameter values for example. The processing unit 21 may be an integral part of a control system of a turbine engine, such as a system known by the acronym ECU meaning "Engine Control Unit" in the English language or by the acronym FADEC. Therefore, the computer of the processing unit is the computer control system, the storage device is the storage device of the control system.
    [0015] The processing unit 21 is connected by wire and / or non-wire connections to a speed sensor 30. The speed sensor 30 is arranged on the power unit to measure the rotational speed N 2 of this power unit.
    [0016] Therefore, the speed sensor 30 transmits to the processing unit a signal carrying the rotation speed N2. Furthermore, the processing unit 21 is connected to a cut-off system 40 able to stop the engine 10. This cut-off system comprises in particular the metering device 7 supplying fuel to the engine 10 and / or the tap 100. Therefore, according to the applied method, a rotorcraft manufacturer establishes a limit operating law prior to the flight of the rotorcraft. Thus, during a development phase, the manufacturer determines a law giving a limit derivative with respect to the time of the speed of rotation N2 of the power unit. This law limits the authorized range of the motor 10. For at least one range of possible value of the speed of rotation N2 of the power unit, the law makes it possible to determine a limit value called "limit derivative". The term "range" means a range of values of the speed of rotation N2 extending between a lower bound and an upper bound. This law is then stored in the processing unit 21.
    [0017] The memorized law can take the form of one or more mathematical equations, or even of a database for example.
    [0018] In flight, the processing unit 21 determines whether the engine is in overspeed condition, and automatically stops this engine 10 if necessary. For this purpose, the processing unit 21 performs a series of continuous calculation operations at a predetermined processing frequency. During each iteration, the processing unit 21 determines the current speed of the power unit 19 from the signal from the speed sensor 30. The processing unit 21 further deduces the derivative from the speed sensor 30. time of this current speed, called "current derivative". Further, when the current speed is within a range of said law, the processing unit implements the stored law to determine if the current derivative is greater than or equal to the limit derivative obtained from the current speed. For example, the processing unit injects the value of the current speed into the stored law, and derives the resulting limit derivative. If the current derivative is greater than the limit derivative, the engine 10 is judged to be in overspeed condition. The processing unit then actuates the cut-off system to stop the motor 10. Where appropriate, each pump 5 is also cut off. FIG. 3 illustrates a law according to the invention through a phase diagram 80.
    [0019] This phase diagram 80 shows the rotational speed N2 of the power assembly 19 on the abscissa. This rotational speed is for example expressed as a percentage of a nominal rotation speed. In addition, the phase diagram 80 presents the derivative with respect to time of this speed of rotation in ordinate. The law providing the limit derivative with respect to the speed of rotation then takes the form of a curve 100 in this phase diagram 80.
    [0020] The curve 100 is not parallel to the ordinate axis, unlike a line 95 which would represent a constant speed of rotation. This curve 100 shares the plane of the phase diagram 80 into an authorized operating sector 81 and an unauthorized operating sector 82. The unauthorized sector 82 is in fact located downstream of said curve 100 with respect to the direction of increase of the abscissae. According to FIG. 3, the authorized sector 81 is located to the left of the curve 100, the unauthorized sector being located to the right of this curve 100. Under these conditions, the motor 10 is stopped when a corresponding operating point pt2 the current derivative and the current speed is located in the unauthorized sector 82. Conversely, if the operating point pt1 is located in the authorized sector 81, the engine is not stopped. To illustrate the interest of the invention, FIG. 3 shows a first line 91 which schematizes a tight turn of the rotorcraft. A second line 92 illustrates a sharp turn made brutally.
    [0021] If the manufacturer sets up a low constant threshold illustrated by the first vertical straight line 95, this constant threshold will cause an undue stop of the motor during the brutal maneuver illustrated by the second line 92.
    [0022] In addition, if the manufacturer sets up a high constant threshold illustrated by the second vertical straight line 96, the stopping of the engine may be delayed if the overspeed occurs following a flight phase inducing a relatively low speed of rotation N2, for example during a turn made according to the first line 91.
    [0023] The curve 100 illustrating the law according to the invention aims to avoid an undue stop, while optimizing the stopping of the engine 10 in case of overspeed. According to the schematized law, the limit derivative decreases linearly along a segment 102 between: an intermediate value 302 reached for a rotation speed called "intermediate speed 201", of the order of 110% of the nominal speed, for example and a minimum value 301 attained for a rotation speed called "maximum allowable speed 202", of the order of 130% of the nominal speed, for example. This minimum value 301 is for example zero. In addition, the intermediate value 302 is of the order of 40% of the nominal speed for example. It is recalled that, the lift rotor is rotated at a nominal speed, this nominal speed inducing a nominal rotation speed of the power assembly known to those skilled in the art.
    [0024] By way of example, the law then takes the following form where "DL" represents said limit derivative and "N2" represents the speed of rotation: DL = -325N2 + 325 for N2 between 110% and 130% of the 130 nominal speed. However, the law can take other forms, possibly non-linear. For example, the segment 102 may be curved. The curve 100 also has the shape of a half-line 101 extending parallel to the ordinate axis from the intermediate value, away from the abscissa axis. Similarly, the curve 100 takes the form of a half-line 103 extending parallel to the ordinate axis from the intermediate value, away from the abscissa axis. With reference to FIG. 1, in addition to an electronic system, the overspeed safety system may comprise a mechanical "blade shedding" type system. Therefore, each blade 51 of the power turbine 15 can be fixed to a hub by a fuse member 52. This fuse member 20 is sized to break in case of overspeed. According to the example shown, each blade is attached to the power shaft by a fuse member. In addition, the overspeed safety system includes a shielding ring 50 for containing the vanes within the motor 10.
    [0025] The invention applies to a rotorcraft equipped with a single motor 10 according to the embodiment of FIG. 1. Nevertheless, the invention also applies to a rotorcraft comprising several engines 10 in accordance with the embodiment of FIG. at least one motor 10 is provided with an over-speed safety system 20. Preferably, each motor 10 comprises this overspeed safety system 20. Naturally, the present invention is subject to numerous variations as to its implementation. artwork. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention. For example, the processing unit may be independent of the FADEC, possibly being arranged in parallel with this FADEC.
    权利要求:
    Claims (17)
    [0001]
    REVENDICATIONS1. A method for stopping an overspeeded rotorcraft engine (1), said rotorcraft (1) comprising at least one engine (10), said engine (10) comprising a gas generator (11) and a power unit (19) ), said power unit (19) having at least one power turbine (15) rotated by gases from the gas generator (11), said power unit (19) having at least one power shaft (16). ) rotatably connected to the power turbine (15), said power unit (19) rotating about a longitudinal axis (AX) at a speed called "speed of rotation (N2)", characterized in that - prior to a flight, a law (100) is determined which provides a so-called "derivative derivative" derivative with respect to the time of said rotational speed over at least one range of speeds of rotation, the limit derivative being according to said law a function of the speed rotation and varying according to this speed of rotation, during a flight: the speed of rotation known as the "current speed" reached by the power unit is measured, where the derivative with respect to the time of said so-called "current derivative" rotation speed is determined, where the current speed is located in a said range provided by said law, said motor (10) is automatically stopped when the limit derivative corresponding to the current speed according to said law (100) is less than or equal to the current derivative
    [0002]
    2. Method according to claim 1, characterized in that, said gas generator (11) being fed by a fuel metering device (7), said metering device being adjustable between a minimum stop inducing a minimum flow of fuel and a maximum stop inducing a maximum fuel flow, said engine (10) is automatically stopped by setting said fuel metering device (7) of the engine (10) to its minimum stop.
    [0003]
    3. Method according to any one of claims 1 to 2, characterized in that at least one motor (10) comprising a valve (100) on a fuel pipe, said engine is automatically shut off by closing said valve (100). ).
    [0004]
    4. Method according to any one of claims 1 to 3, characterized in that each motor (10) being supplied with fuel by at least one pump (5), said pump (5) is cut off following an automatic shutdown of the pump (5). engine.
    [0005]
    5. Method according to any one of claims 1 to 4, characterized in that said limit derivative decreases between: an intermediate value (302) reached for a rotation speed called "intermediate speed (201)", and 20 - a value minimum (301) reached for a rotational speed called "maximum allowable speed (202)" of said power unit (19), said maximum allowable speed (202) being greater than the intermediate speed (201), the minimum value (301) being less than the intermediate value (302).
    [0006]
    6. Method according to claim 5, characterized in that said minimum value (301) is zero.
    [0007]
    7. Method according to any one of claims 5 to 6, characterized in that the motor is not stopped automatically for a speed of rotation lower than a lower threshold regardless of the current derivative.
    [0008]
    8. Method according to any one of claims 5 to 7, characterized in that the motor is automatically stopped for a rotation speed greater than a higher threshold regardless of the current derivative.
    [0009]
    9. A method according to claim 5, characterized in that said law is established for a speed of rotation between the intermediate speed and the maximum permissible speed, the motor is not stopped automatically for a speed of rotation lower than the intermediate speed whatever the current derivative, the motor being stopped automatically for a speed of rotation greater than the maximum permissible speed whatever the current derivative.
    [0010]
    10. Method according to any one of claims 1 to 9, characterized in that in a phase diagram (80) having the rotation speed in the abscissa and the derivative with respect to the time of said rotational speed on the ordinate, the law providing the limit derivative with respect to the speed of rotation takes the form of a curve (100) which is not parallel to the ordinate axis, said curve (100) sharing the plane of the phase diagram (80) in an authorized operating sector (81) which does not require stopping of the engine (10) and an unauthorized operating unit (82) requiring stopping of the engine (10), said unauthorized sector (82) being located downstream of said curve (100) with respect to the direction of increase of the abscissa, said motor (10) being stopped when an operating point (pt2) corresponding to the current derivative and the current speed is located in the unauthorized sector (82). ).
    [0011]
    11. The method of claim 5, characterized in that said limit derivative decreases linearly between said intermediate value (302) and said minimum value (301).
    [0012]
    An overspeed safety system (20) for a rotorcraft engine (10), said engine (10) comprising a gas generator (11) and a power assembly (19), said power unit (19). ) having at least one power turbine (15) rotated by said gas generator (11), said power unit (19) having at least one power shaft (16) integral in rotation with the power turbine (15). ), said overspeed safety system (20) comprising a shutdown system (40) for stopping the operation of said turbine engine (10), said overspeed safety system (20) comprising a processing unit (21) connected to the engine control system (20); cut-off (40), characterized in that said over-speed safety system (20) comprises a speed sensor (30) for measuring a rotational speed (N2) of said power unit (19), said processing unit (21) being connected to the speed sensor (30) to implement the process itself any one of claims 1 to 11 by automatically stopping said engine (10) when the value of the limit derivative corresponding to the current speed is less than the current derivative.
    [0013]
    13. Overspeed safety system according to claim 12, characterized in that said cut-off system (40) comprises a fuel metering device (7) conveying fuel towards the gas generator (11).
    [0014]
    14. Overspeed safety system according to any one of claims 12 to 13, characterized in that said cut-off system (40) comprises at least one pump (5) conveying fuel to said gas generator (11).
    [0015]
    An overspeed safety system according to any one of claims 12 to 14, characterized in that said overspeed safety system (20) comprises a shielding ring (50) surrounding said power turbine (15), said power turbine (15) having a plurality of blades (51), each blade (51) being attached to a fuse member (52).
    [0016]
    16. Overspeed safety system according to any one of claims 12 to 15, characterized in that said processing unit (21) is a FADEC of said engine (10).
    [0017]
    17. Giravion (1) comprising at least one rotor (2), said rotorcraft (1) comprising at least one motor (10), said motor (10) driving a power transmission chain (3) connected to said rotor (2) ), characterized in that said rotorcraft (1) comprises at least one overspeed safety system (20) according to any one of claims 12 to 16, each overspeed safety system (20) being connected to a motor (10) .
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    公开号 | 公开日
    US20160090187A1|2016-03-31|
    FR3026438B1|2019-03-15|
    US10150569B2|2018-12-11|
    引用文献:
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    US20140123663A1|2012-11-02|2014-05-08|Pratt & Whitney Canada Corp.|Rotor resonance disturbance rejection controller|EP3926146A1|2020-06-17|2021-12-22|Airbus Helicopters|Method for stopping an engine in overspeed, associated system and rotorcraft|US3899879A|1973-11-05|1975-08-19|Gen Motors Corp|Turbine engine fuel control|
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    FR2967213B1|2010-11-10|2012-10-26|Eurocopter France|CONTROL METHOD FOR AIRCRAFT ENGINE OPERATED SAFETY SYSTEM AND CONTROL CIRCUIT FOR CARRYING OUT SAID METHOD|
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    FR3034403B1|2015-03-31|2017-03-31|Airbus Helicopters|METHOD AND DEVICE FOR STOPPING A TURBOMOTER IN NOMINAL OPERATION|
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    法律状态:
    2015-08-27| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-01| PLSC| Search report ready|Effective date: 20160401 |
    2016-09-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-25| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-14| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1402172A|FR3026438B1|2014-09-26|2014-09-26|METHOD FOR STOPPING AN OVERSPEED RUNNING MOTOR, SYSTEM AND GIRAVION THEREFOR|FR1402172A| FR3026438B1|2014-09-26|2014-09-26|METHOD FOR STOPPING AN OVERSPEED RUNNING MOTOR, SYSTEM AND GIRAVION THEREFOR|
    US14/867,464| US10150569B2|2014-09-26|2015-09-28|Method of stopping a rotorcraft engine in overspeed, and a system and a rotorcraft associated therewith|
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