• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for detecting a failure of a first turbine engine, said engine (4) out of order, a twin engine helicopter and control of a second turbine engine, said engine (5) healthy, each engine ( 4, 5) comprising protection stops regulated by a control device which define a maximum power regime, characterized in that it comprises: a step (10) for detecting a failure index of said motor (4) in breakdown ; a step (11) of modifying said protective stops of said sound motor (5) into protective stops corresponding to a single engine speed of maximum power, in case of detected failure index; a step (12) of confirmation of a failure of said engine (4) failed; a step (13) for controlling an increase in the fuel supply rate of said engine (5) healthy in case of confirmed failure.
    公开号:FR3019225A1
    申请号:FR1452642
    申请日:2014-03-27
    公开日:2015-10-02
    发明作者:Fabien Lescher；Jean Philippe Jacques Marin；Philippe Etchepare
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] METHOD FOR DETECTING A FAILURE OF A FIRST TURBOMOTOR OF A BIMOTOR HELICOPTER AND OF CONTROLLING THE SECOND TURBOMOTOR, AND CORRESPONDING DEVICE 1. TECHNICAL FIELD OF THE INVENTION The invention relates to a method for regulating the turboshaft engines of a twin-engine helicopter . In particular, the invention relates to a method for detecting a failure of a first turbine engine, said engine failed, a twin-engine helicopter and control of the second turbine engine, said engine sound. The invention also relates to a device for detecting a failure of a first turbine engine and control of a second turbine engine of a twin-engine helicopter. 2. Technological background A twin-engine helicopter is equipped with two turboshaft engines operating at speeds that depend on the flight conditions of the helicopter. It is known that a twin-engine helicopter can have two main regimes, a regime known as AEO (Ail Engines Operative) in which both engines normally operate at predetermined speeds, and a regime known as OEI. (One Engine Inoperative) in which one of the turboshaft engines is down. This OEI regime occurs following the loss of an engine. When this event occurs, it is necessary for the valid engine to accelerate rapidly so that it can provide its maximum allowable power in an emergency situation, thereby allowing the helicopter to cope with the perilous situation, and then to be able to continue his flight.
    [0002] Throughout the following text, the failed turbine engine will be designated by the words "turboshaft failed" and the valid turbine engine will be designated by the words "turbine engine healthy". It therefore raises the technical problem of minimizing the time that separates the detection of the sudden power loss of the failed turbine engine and obtaining the maximum power in emergency mode of the healthy turbine engine. Indeed, the shorter the duration, the safer the flight. In addition, the shorter the duration, the greater the helicopter's mass at take-off. The minimization of the time which separates the detection of the power loss of the failed engine from the obtaining of the full power of the healthy engine thus presents a double interest. It is known today to detect the power loss of the engine failure by a comparison of the operating speeds of the two turboshaft engines. If a predetermined difference between the two operating modes 10 is detected, the turbine engine with the worst speed is declared faulty. This loss of power is detected by revealing a difference between the speeds of the gas turbines greater than a predetermined threshold or a difference between the pairs of the two engines greater than a predetermined threshold. Once the power loss is detected, the healthy engine is controlled to reach its maximum speed in emergency mode, which consists of increasing the maximum torque and speed limits of the gas turbine to the maximum permitted stops. Subsequently, the fall in the rotational speed of the rotary wing of the helicopter following the loss of the engine failure will result, via the regulation of the speed of the rotary wing by the sound engine, an increase in the fuel flow instruction. There is the technical problem of providing a better solution to further minimize the time between the detection of the sudden power loss of the failed turbine engine and obtaining the maximum power in emergency mode of the healthy turbine engine. 3. OBJECTIVES OF THE INVENTION The invention aims to provide an effective and economical solution to this technical problem. In particular, the invention aims to provide, in at least one embodiment of the invention, a method of detecting a failure of a first turbine engine, said engine inoperative, of a twin engine and control helicopter. the second turbine engine, known as the healthy engine, which minimizes the time between the detection of the failed engine failure and the achievement of the full power of the sound engine. The invention also aims to provide a device for detecting a failure of a first turbine engine failure of a twin-engine helicopter and control of the second turbine engine sound. The invention also aims to provide a twin-engine helicopter equipped with such a device. 4. DISCLOSURE OF THE INVENTION To this end, the invention relates to a method for detecting a failure of a first turbine engine, said engine inoperative, of a twin-engine helicopter and of a second turbine engine, said engine sound, each motor comprising protection stops regulated by a control device which define a maximum power regime, characterized in that it comprises: a step of detecting a failure index of said engine failure, a modification step said protective stops of said sound engine in protective stops corresponding to a single-engine speed, in case of detected failure index, a step of confirmation of a failure of said engine failure, a step of controlling an increase in the flow rate fueling said healthy engine in case of confirmed failure. A method according to the invention thus makes it possible to switch the sound engine from a twin-engine configuration to a single-engine configuration as soon as a failure index is detected. This configuration change step is performed by modifying the motor protection stops in protective stops corresponding to the single engine speed. A subsequent fault confirmation step is then implemented and conditions the control of increasing the fuel flow rate of the sound engine. This failure confirmation step ensures that the helicopter is effectively coping with a real loss of power, which avoids controlling inadvertent acceleration of the healthy engine, which could otherwise cause overspeed of the rotor. If the failure is confirmed, the fuel flow of the healthy engine is immediately increased, which allows to accelerate quickly the healthy engine, without waiting for automatic regulation following the fall of the rotational speed of the rotary wing of the helicopter . A method according to the invention thus makes it possible to quickly detect a failure of an engine and to reach the full power of the sound engine quickly after the detection of the failure. As soon as a fault index is detected, the protections of the sound engine are modified and increased towards the protective stops corresponding to the single-engine speed. If the fault is confirmed, the fuel setpoint is changed. The healthy engine is already in full acceleration, because the increase of the protective stops, the full power in single-engine speed is quickly reached. A method according to the invention has phases of detection of engine failure and sound engine control which are nested one inside the other, which allows to shorten the time between the detection of the failure of said engine broken down and obtaining the full power of said sound engine. In known manner, each turbine engine comprises a gas generator provided with a combustion chamber, a free turbine supplied with gas by the gas generator, and an output shaft driven in rotation by the free turbine. The protection stops of each motor, which define the maximum power speed of this engine, typically correspond to the speed levels of the gas generator, engine torque and / or temperature of the combustion chamber. These protective stops are regulated by a control device known by the acronym FADEC for Full Authority Digital Engine Control. The step of modifying the protective stops makes it possible to modify, and in practice to increase, the maximum authorized limits of these various parameters - gas generator speed, engine torque, combustion chamber temperature -. These stops go from their levels corresponding to a twin engine operation at their levels corresponding to a single-engine operation. Advantageously and according to the invention, the step of detecting a failure index consists in: recovering, for each engine, at least one measurement of at least one parameter representative of the operating speed of the motors, detecting a difference between said measurements greater, in absolute value, at a predetermined threshold. This step makes it possible to recover measurements of at least one parameter representative of the operating speed of each motor and to detect a difference between these measurements which is greater, in absolute value, than a predetermined threshold. Such a parameter representative of the operating speed of the motors may be a measured parameter or an estimated parameter. It can for example be the rotational speed of the gas turbine of each engine, or the torque exerted by an output shaft of each turbine engine setting in motion a power transmission, or the temperature of the gases to the inlet of the free turbine of each turbine engine, or the estimation of the quantity of metered flow, etc. Advantageously and according to this variant, each detection of a difference between said measurements is modulated by at least one variable, called modulation variable, representative of normal variations of said measurements during a nominal engine operating speed. According to this advantageous variant, each measurement of a difference is modulated by a modulation variable which makes it possible to take into account the normal variations of the measurements during a nominal operating regime. This thus makes it possible to avoid untimely detections of failure due in fact to normal variations of the measurements. These modulation variables thus make it possible to integrate the normal variations of the measurements and thus to reduce the threshold at which a difference must be considered as a failure index. Advantageously and according to this variant, at least one modulation variable is chosen from the following group: type of engine speeds; type of effective balancing of engines; proximity of engine speed and torque measurements of the maximum permissible values for these engines; engine acceleration and deceleration rate; transmission time of said measurements of each parameter representative of the operating speed of the engines.
    [0003] Each of these modulation variables makes it possible to take into account, when determining a difference between the measurements of a parameter representative of the operating speed of the engines, the conditions under which the measurement was made, and thus to modulate the measure of the gap. Advantageously, as a variant or in combination, a method according to the invention also comprises a step of learning nominal deviations between said measurements of at least one parameter representative of the operating speed of the engines, during stabilized speeds of said engines. , said nominal deviations thus determined constituting a modulation variable. Such a learning step makes it possible to create a learning base that provides discrepancies between the measurements of a parameter representative of the operating speed of the engines, which are not representative of a failure of one of the engines. Also, this learning base provides normal deviations under normal operating conditions. In other words, this learning base makes it possible to refine the detection threshold from which a deviation must be considered as a failure index. Advantageously and according to the invention, at least one parameter representative of the operating speed of an engine is a rotational speed of said gas generator or a torque exerted by said output shaft of this engine. According to this advantageous variant, the step of detecting a failure index consists in comparing the values of the gas turbine speeds and / or the torques exerted by the output shafts. Advantageously and according to the invention, the step of modifying the protective stops of said sound motor to protective stops corresponding to a single-engine speed is to increase the torque exerted by said output shaft and to increase the rotational speed of said generator. gas, to reach predetermined nominal values corresponding to a single-engine regime of full power. Advantageously and according to the invention, the step of confirming a failure of said first motor consists in verifying that a plurality of predetermined conditions representative of a real loss of power is verified.
    [0004] Advantageously and according to this variant, said predetermined conditions are as follows: a signed discrepancy between the speed of rotation of said gas generator of said engine inoperative and the rotational speed of said gas generator of said sound engine is greater than the difference measured in said step of detecting an index for this parameter, a signed discrepancy between the torque of said output shaft of said failed motor and the torque of said output shaft of said sound motor is greater than the difference measured in said step of detecting a index, a rotational speed of said free turbine of said failed engine is less than a predetermined set value removed from a predetermined offset, a time drift of the rotational speed of said gas generator of said sound engine is greater than a predetermined threshold , a time drift of the rotational speed of said gas generator of said engine failure is less than n predetermined threshold. The set of predetermined conditions mentioned above makes it possible to confirm the breakdown of said failed engine. In other words, it makes it possible to discriminate a real loss of power on the engine that has failed from another cause that may have led to the detection of a failure index by highlighting a difference greater than a threshold predetermined. Advantageously and according to the invention, said step of controlling an increase in the fuel supply flow rate of said sound engine consists in switching a power anticipation law, connecting a measurement of the collective pitch of the blades of said helicopter to a speed setpoint of said gas generator, in two-engine configuration in anticipation law in single-engine configuration. According to this variant, the increase of the fuel flow in the sound engine consists of switching a power anticipation law in two-engine configuration to an anticipation law in single-engine configuration. The invention also relates to a device for detecting a failure of a first turbine engine, said engine inoperative, a twin-engine helicopter and control of a second turbine engine, each engine comprising protective stops regulated by a safety device. regulation which define a maximum power regime, said sound engine comprising: a module for detecting a failure index of said engine inoperative, a module for modifying said stops for protecting said sound engine in protective stops corresponding to a regime single engine, in the event of a detected failure index, a module for confirming a failure of said engine inoperative, a control module for increasing the fuel supply flow rate of said sound engine in the event of confirmed failure. A device according to the invention advantageously implements a method according to the invention and a method according to the invention is advantageously implemented by a device according to the invention.
    [0005] Throughout the text, the term "module" denotes a software element, a subset of a software program that can be compiled separately, either for independent use, or to be assembled with other modules of a program, or a hardware element, or a combination of a hardware element and a software subprogram. Such a hardware element may include an application-specific integrated circuit (ASIC) or a programmable logic circuit or equivalent hardware. In general, a module is an element (software and / or hardware) that ensures a function.
    [0006] The invention also relates to a helicopter comprising at least two turboshaft engines, characterized in that it comprises a device according to the invention.
    [0007] The invention also relates to a method for detecting a failure of a first turbine engine of a twin engine helicopter, and control of a second turbine engine, a corresponding device, and a helicopter comprising such a device, characterized in combination by any or some of the features mentioned above or below. 5. List of Figures Other objects, features and advantages of the invention will become apparent on reading the following description given solely by way of non-limiting example and which refers to the appended figures in which: FIG. 1 is a diagrammatic view of a two-engine architecture for implementing the method according to one embodiment of the invention, Figure 2 is a schematic view of a method according to one embodiment of the invention. 6. DETAILED DESCRIPTION OF ONE EMBODIMENT OF THE INVENTION FIG. 1 schematically illustrates an exemplary architecture 100 of a twin-engine helicopter adapted to the implementation of a method according to the invention. Each turbine engine 4, 5 comprises respectively and conventionally a generator 41, 51 of gas and a free turbine 42, 52, powered by the generator 41, 51 of gas to provide power. The output of the turbomachines is connected to a transmission transmission box 9. Each generator 41, 51 of gas further comprises a combustion chamber 40, 50 fed with fuel by a fuel distribution circuit not shown in the figure for the sake of clarity.
    [0008] Each turbine engine 4, 5 is coupled to drive means E1, E2 and emergency assistance devices U1, U2. Each drive means E1, E2 in rotation of the respective gas generator 41, 51 may be constituted by a starter respectively powered by a starter / generator device equipping the other turbine engine.
    [0009] The drive means E1, E2, the emergency assistance devices U1, U2 and the controls of the turbomachines 4, 5 are managed by a control device 8. This control device is adapted to regulate the protective stops which define the maximum power regime of each engine. Figure 2 is a schematic representation of a method according to one embodiment of the invention. A method according to this embodiment of the invention comprises a step 10 of detecting a failure index of the first turbine engine 4, said engine failure, by measuring a difference greater than a predetermined threshold between values provided by this turboshaft 4 failed and the turbine engine 5 sound, for at least one parameter representative of the operating speed of the engines 4, 5. Throughout the text, the terms "engine" and "turbine engine" are synonymous and are therefore used to designate a power supply device for a helicopter. The blocks 4, 5 of FIG. 2 respectively represent the failed turbine engine and the sound turbine engine, including the power and control members. Figure 2 is intended only to present the sequencing of the process steps and the main interactions with the two turboshaft engines. The method further comprises a step 11 of modifying and increasing the protective stops of the sound turbine engine 5 to protective stops corresponding to a full power single engine speed. This modification of the stops is carried out in the event of a failure index detected in step 10. These protective stops are the rotational speed of the gas generator, the torque on the output shaft and the temperature of the combustion chamber. . The method further comprises a step 12 of confirming the failure of the turbine engine 4 failed by the measurement of a difference greater than a predetermined threshold between the values provided by the turboshaft 4 failed and the turbine engine 5 healthy for a plurality of parameters representative of the operating speed of the engines. Finally, the method comprises a step 13 of controlling an increase in the fuel supply rate of the healthy turbine engine 5 in case of confirmed failure.
    [0010] Each step will now be described in more detail. The step 10 of detecting a failure index consists in recovering, for each engine 4, 5, a measurement of at least one parameter representative of the operating speed of the motors and detecting a difference between said upper measurements, in value absolute, at a predetermined threshold. This parameter is for example the speed of rotation of the generator 41, 51 of gas of each motor or the torque of the output shaft. The measurement of the difference between the values is modulated by at least one modulation variable representative of normal variations of the measurements during a nominal operating regime of the motors 4, 5. This variable 20 is for example representative of the type of speed motors, the type of effective motor balancing, the proximity of the engine speed and torque measurements of the maximum permissible values for those engines, the acceleration and deceleration rate of the engines or the transmission delay of the engines measurements of each parameter representative of the operating speed of the engines. In step 10 of detection of an index, the difference between the values provided by the motors is calculated and modulated by the modulation variable 20. If a difference greater than a predetermined threshold is detected, then a failure index of the motor 4 is detected. For example, if we consider the rotation speed of the gas generator and according to one embodiment, the predetermined threshold from which a deviation is considered sufficiently significant to characterize a failure, is 1%. If we consider the motor torque, the predetermined threshold is set at 7%.
    [0011] Step 11 then consists in controlling the full power of the motor 5 so that it reaches nominal values of single-engine operation, to overcome the failure of the engine 4. In a conventional manner, this control aims at increasing the speed of rotation of the engine. the gas turbine and the output torque of the turbine engine.
    [0012] Step 12 is to check that the motor 4 is down. To do this, the following tests are performed. It is verified that a signed discrepancy between the rotational speed of the failed gas engine generator 4 and the rotational speed of the healthy engine gas generator 51 is greater than the difference measured in step 10 of FIG. detection of an index when the parameter representative of the operating speed of the engines is the speed of rotation of the gas generators of the engines. It is also verified that the signed discrepancy between the output shaft torque of the failed motor 4 and the output shaft torque of the sound motor 5 is greater than the difference measured during the step of detection of an index when the parameter representative of the operating speed of the motors is the engine torque. It is also verified that the rotational speed of the free turbine 4 of the failed motor 4 is less than a predetermined set value subtracted from a predetermined offset (for example, this offset is set at 0.75% of the speed of rotation). the free turbine and the setpoint is the nominal speed of the free turbine). It is also verified that the time drift of the speed of rotation of the gas generator 51 of the sound engine 5 is greater than a predetermined threshold (for example, the predetermined threshold for the time drift of the sound engine is set at 1% of the speed of the gas generator per second). Finally, it is verified that the time drift of the rotational speed of the gas generator 41 of the engine 4 that has failed is less than a predetermined threshold (for example, the predetermined threshold for the time drift of the engine inoperative is set at 5% of the speed of the gas generator per second). If all of the above conditions are verified, the failure of the engine 4 is confirmed and a drive to the healthy engine is initiated to increase the fuel flow of the healthy engine. According to one embodiment of the invention, this increase in fuel flow is obtained by switching a power anticipation law, connecting a measurement of the collective pitch of the blades of the twin-engine helicopter to a speed reference of the engine. generator 51 of gas, in twin-engine configuration in anticipation law in single-engine configuration. This switching of anticipation laws generates a flow setpoint jump suddenly accelerating the engine 5 healthy, while ensuring the protections of the engine 5 (maximum speed, maximum torque, maximum temperature, no pumping, etc.). A method according to the invention is advantageously implemented by a device for detecting a failure of the first failed turbine engine, a twin-engine helicopter and control of the second healthy turbine engine comprising: a module for detecting an index of failure of said engine failure, a module for modifying said protective stops of said sound engine in protective stops corresponding to a single-engine speed, in the event of a detected failure index, a module for confirming a failure of said engine failure, a control module of a fuel supply flow increase of said sound engine in case of confirmed failure. According to an advantageous embodiment, this device is housed in the regulating device 8 and this regulating device 8 acts as a detection module, a module for modifying the stops, a fault confirmation module and a control module. According to an advantageous embodiment, the device comprises a computer program product downloadable from a communication network and / or recorded on a computer readable medium and / or executable by a processor, including program code instructions for setting implementation of the method according to the invention, when said program is executed on a computer. This computer program product is for example intended to be executed by the regulation device.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A method of detecting a failure of a first turbine engine, said engine (4) down, a twin engine helicopter and control a second turbine engine, said engine (5) sound, each engine (4, 5) comprising protection stops regulated by a regulating device (8) which define a maximum power regime, characterized in that it comprises: a step (10) for detecting a failure index of said failed motor (4); a step (11) of modifying said protective stops of said sound motor (5) in protective stops corresponding to a single engine speed of maximum power, in case of detected failure index, - a confirmation step (12) a failure of said engine (4) failed, - a step (13) for controlling an increase in fuel delivery rate of said engine (5) healthy in case of confirmed failure.
    [0002]
    2. Method according to claim 1, characterized in that said step (10) for detecting a failure index consists in: recovering, for each engine, at least one measurement of at least one parameter representative of the operating regime motors, - detecting a difference between said higher measurements, in absolute value, at a predetermined threshold.
    [0003]
    3. Method according to claim 2, characterized in that each detection of a difference between said measurements is modulated by at least one variable, said modulation variable (20), representative of normal variations of said measurements during an operating regime. rated motors (4, 5).
    [0004]
    4. Method according to claim 3, characterized in that at least one modulation variable (20) is chosen from the following group: type of engine regimes (4,
    [0005]
    5); type of effective balancing of the motors (4, 5); proximity of measurements of shaft speeds and engine torque (4, 5) of the maximum permissible values for these engines; engine acceleration and deceleration rate (4, 5); transmission time of said measurements of each parameter representative of the operating speed of the engines. 5. Method according to one of claims 3 or 4, characterized in that it further comprises a learning step nominal differences between said measurements of at least one parameter representative of the operating speed of the motors (4, 5), during stabilized speeds of said motors, said nominal deviations thus determined constituting a modulation variable (20).
    [0006]
    6. Method according to one of claims 2 to 5, wherein each engine comprises a gas generator supplying a free turbine which rotates an output shaft, characterized in that at least one parameter representative of the operating speed of a motor (4, 5) is a rotational speed of said gas generator or a torque exerted by said output shaft of said engine.
    [0007]
    7. Method according to claim 6, characterized in that said step (11) of modifying the protective stops of said motor (5) in stops corresponding to a single-engine speed is to increase the torque exerted by said output shaft and to increase the rotational speed of said gas generator (51), to reach predetermined nominal values corresponding to a single engine speed of maximum power.
    [0008]
    8. Method according to one of claims 1 to 7, characterized in that said step (12) for confirming a failure of said first motor is to verify that a plurality of predetermined conditions representative of a real loss of power is verified.
    [0009]
    9. A method according to claims 6 and 8 taken together, characterized in that said predetermined conditions are as follows: a signed difference between the rotational speed of said generator (41) of said gas engine (4) failed and the speed of rotation of said gas generator (51) of said sound motor (5) is greater than the difference in said step (10) for detecting an index for this parameter, - a signed difference between the torque of said output shaft of said motor (4) in failure and the torque of said output shaft of said sound motor (5) is greater than the difference measured in said step (10) of detection of an index, - a speed of rotation of said free turbine (42) of said motor ( 4) is less than a predetermined set value subtracted from a predetermined offset, - a time drift of the rotational speed of said gas generator (51) of said sound motor (5) is greater than a predetermined threshold, - a drift you The speed of rotation of said gas generator (41) of said failed motor (4) is less than a predetermined threshold.
    [0010]
    10. The method of claim 9, characterized in that said step (13) for controlling an increase in the fuel supply flow rate of said engine (5) healthy, is to switch a power anticipation law, connecting a measurement of the collective pitch of the blades of said helicopter to a speed setpoint of said gas generator, in two-engine configuration in anticipation law in single-engine configuration.
    [0011]
    11. Device for detecting a failure of a first turbine engine, said engine failure, a twin engine helicopter and control of a second turbine engine, said engine sound, each engine comprising protective stops regulated by a device. regulation which define a maximum power regime, comprising: a module for detecting a failure index of said engine inoperative, a module for increasing the stops for protecting said sound engine in stops corresponding to a single-engine speed, in the case of failure index detected, a confirmation module of a failure of said engine failure, - a control module of an increase in the flow of fuel supply of said healthy engine in case of failure confirmed.
    [0012]
    12. Helicopter comprising at least two turboshaft engines, characterized in that it comprises a device according to claim 11.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3123020B1|2019-01-30|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device
    EP3208429B1|2018-04-11|System andmethod for starting a twin motor aircraft
    CA2764719C|2016-11-29|Method for testing the protection chain of a turbine engine against overspeed upon starting
    FR2840955A1|2003-12-19|GAS TURBINE CONTROL SYSTEM
    EP3109156B1|2017-11-15|Method for controlling a three-engined power plant of a rotary-wing aircraft
    WO2014053752A1|2014-04-10|Method for monitoring a thrust fault of an aircraft turbofan
    EP3075662A1|2016-10-05|A method and a device for stopping a turboshaft engine in nominal operation
    EP2855900B1|2018-09-05|Turbomachine comprising a monitoring system comprising a module for engaging a protection function of the turbomachine and monitoring method
    CA2799712C|2014-09-02|Device and control method for a drive installation including at least one turbine engine, and aircraft
    FR3026438A1|2016-04-01|METHOD FOR STOPPING AN OVERSPEED RUNNING MOTOR, SYSTEM AND GIRAVION THEREFOR
    FR3019222A1|2015-10-02|TURBOMOTEUR, HELICOPTERE BIMOTEUR EQUIPPED WITH SUCH A TURBOMOTEUR AND METHOD FOR OPTIMIZATION OF THE SUPER-SLOWING SPEED WITH NULL POWER OF SUCH A BIMOTING HELICOPTER
    FR3019223A1|2015-10-02|TURBOMOTOR COMPRISING A CONTROLLED MECHANICAL COUPLING DEVICE, HELICOPTER EQUIPPED WITH SUCH A TURBOMOTOR, AND METHOD OF OPTIMIZING THE SUPER-SLOWING SYSTEM WITH NULL POWER OF SUCH A HELICOPTER
    EP3607190B1|2021-02-17|Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines
    WO2016193603A1|2016-12-08|Method for detecting a mechanical defect in an aircraft turbine engine gas generator, and corresponding device for implementing said method
    FR3095191A1|2020-10-23|HYBRID PROPULSION SYSTEM AND PROCESS FOR CONTROL OF SUCH A SYSTEM
    FR3019913A1|2015-10-16|METHOD FOR SYNCHRONIZING THE MOTORS OF A DOUBLE INTERMEDIATE AIRCRAFT
    FR3098254A1|2021-01-08|Turbogenerator with simplified control system for aircraft
    WO2020208318A1|2020-10-15|Hybrid propulsion installation and method for controlling such an installation
    FR2947300A1|2010-12-31|Protection chain test realizing method for e.g. turbojet engine of aircraft, involves transmitting information on defect of overspeed protection chain by electronic regulation system, if closing state check result is negative
    EP3947920A1|2022-02-09|Method and system for monitoring a system for actuating a component of a turbomachine
    FR2946092A1|2010-12-03|Fuel injection regulating system for turboshaft engine of helicopter, has actuation motor controlled by injected fuel flow control module for receiving value of parameter of engine in normal mode and another engine in back-up mode
    同族专利:
    公开号 | 公开日
    EP3123020B1|2019-01-30|
    US10578031B2|2020-03-03|
    FR3019225B1|2018-06-22|
    RU2016139109A|2018-04-27|
    EP3123020A1|2017-02-01|
    CA2943150A1|2015-10-01|
    RU2016139109A3|2018-10-10|
    CN106255814A|2016-12-21|
    WO2015145041A1|2015-10-01|
    JP6621757B2|2019-12-18|
    KR102339468B1|2021-12-15|
    PL3123020T3|2019-06-28|
    ES2712863T3|2019-05-16|
    KR20160140703A|2016-12-07|
    RU2674171C2|2018-12-05|
    JP2017521586A|2017-08-03|
    CN106255814B|2018-10-26|
    US20170101938A1|2017-04-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4500966A|1982-05-26|1985-02-19|Chandler Evans Inc.|Super contingency aircraft engine control|
    WO1994010619A1|1992-10-29|1994-05-11|United Technologies Corporation|Partial engine and driveshaft failure detection monitor for a multi-engine aircraft|
    US20130184903A1|2012-01-12|2013-07-18|Eurocopter|Aircraft power plant, an aircraft, and a method of piloting said aircraft|
    GB1519144A|1974-07-09|1978-07-26|Lucas Industries Ltd|Electronic fuel control for a gas turbine engine|
    US5265826A|1991-08-27|1993-11-30|United Technologies Corporation|Helicopter engine control having lateral cyclic pitch anticipation|
    US6873887B2|2001-11-13|2005-03-29|Goodrich Pump & Engine Control Systems, Inc.|Rotor torque anticipator|
    GB0317394D0|2003-07-25|2003-08-27|Goodrich Control Sys Ltd|Engine fuel control|
    WO2009040112A2|2007-09-25|2009-04-02|Eads Deutschland Gmbh|Method for operating a gas turbine engine, power supplying device for conducting such method and aircraft using such method|
    FR2967132B1|2010-11-04|2012-11-09|Turbomeca|METHOD OF OPTIMIZING THE SPECIFIC CONSUMPTION OF A BIMOTING HELICOPTER AND DISSYMMETRIC BIMOTOR ARCHITECTURE WITH A CONTROL SYSTEM FOR ITS IMPLEMENTATION|US10760484B2|2016-09-16|2020-09-01|Pratt & Whitney Canada Corp.|Multi-engine aircraft power plant with heat recuperation|
    FR3064680B1|2017-04-03|2019-04-05|Safran Helicopter Engines|METHOD FOR VERIFYING THE MAXIMUM POWER AVAILABLE FROM A TURBOMACHINE OF AN AIRCRAFT EQUIPPED WITH TWO TURBOMACHINES|
    US11247782B2|2018-09-21|2022-02-15|Textron Innovations Inc.|System and method for controlling rotorcraft|
    US11168621B2|2019-03-05|2021-11-09|Pratt & Whitney Canada Corp.|Method and system for operating an engine in a multi-engine aircraft|
    CN109854389B|2019-03-21|2020-07-31|南京航空航天大学|Double-engine torque matching control method and device for turboshaft engine|
    法律状态:
    2015-03-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-02| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 4 |
    2017-09-01| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452642|2014-03-27|
    FR1452642A|FR3019225B1|2014-03-27|2014-03-27|METHOD FOR DETECTING FAILURE OF A FIRST TURBOMOTOR OF A BIMOTOR HELICOPTER AND CONTROL OF THE SECOND TURBOMOTOR, AND CORRESPONDING DEVICE|FR1452642A| FR3019225B1|2014-03-27|2014-03-27|METHOD FOR DETECTING FAILURE OF A FIRST TURBOMOTOR OF A BIMOTOR HELICOPTER AND CONTROL OF THE SECOND TURBOMOTOR, AND CORRESPONDING DEVICE|
    US15/128,090| US10578031B2|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    PL15717551T| PL3123020T3|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    CN201580015758.5A| CN106255814B|2014-03-27|2015-03-20|For detecting pair failure of the first engine of hair helicopters and for operating the method for the second engine and corresponding equipment|
    KR1020167027526A| KR102339468B1|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    ES15717551T| ES2712863T3|2014-03-27|2015-03-20|Procedure for detecting a failure of a first turbo-engine of a twin-engine helicopter and control of the second turbo-engine, and corresponding device|
    EP15717551.4A| EP3123020B1|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    PCT/FR2015/050697| WO2015145041A1|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    CA2943150A| CA2943150A1|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device|
    JP2016558283A| JP6621757B2|2014-03-27|2015-03-20|Method of detecting a failure of a first turbine engine of a twin-engine helicopter and controlling a second turbine engine and corresponding apparatus|
    RU2016139109A| RU2674171C2|2014-03-27|2015-03-20|Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine and corresponding device|
    [返回顶部]