• 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 device for starting a gas turbine, comprising a launch system capable of driving on command said gas turbine in rotation. The starting device comprises means for receiving information representative of the speed of rotation of the gas turbine, means for calculating a torque setpoint as a function of said information representative of the speed of rotation of the turbine. gas, and means for transmitting said torque setpoint to the launching system.
    公开号:FR3025252A1
    申请号:FR1458114
    申请日:2014-08-29
    公开日:2016-03-04
    发明作者:Stephane Chevalier；Fabien Silet；Alexis Renotte
    申请人:Safran Power Units SAS；Labinal Power Systems SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD OF THE INVENTION 1. Field of the Invention The invention relates to a device for initiating a gas turbine, a method for regulating the speed of rotation of a gas turbine, and a gas turbine and a turbomachiner. starting a gas turbine, a method of starting a gas turbine and a method of regulating the speed of rotation of a gas turbine. In particular, the invention relates to a starting device, a starting method and a method for regulating the speed of rotation of a gas turbine of a turbine engine of an aircraft. 2. Background technology On aircraft, the power required to start a gas turbine (TAG) is provided either by batteries or by an external auxiliary group (ground carriage or airport supply network) or by the electrical generation of another gas turbine of the aircraft (typically an auxiliary power unit). In the start-up phase, the acceleration of the gas turbine depends both on the torque applied by the starting device of the gas turbine and on the resistant torques generated for example by the accessory box, the rotors, the equipment driven via the accessory box or mechanical power recoveries on the rotor or rotors. These resistant pairs fluctuate significantly depending on the environment in which the gas turbine is located, in particular the temperature and the altitude of the aircraft. Obtaining a reproducible and reliable starting profile under these conditions is complex because the resistant torque information presented by the gas turbine is generally not available. In addition, the torque applied by the starting device is sometimes difficult to measure, either because of the design of the device or the turbine, or because the measurement of this torque would cause disturbances of the rotation of the turbine, resulting in loss of reliability. Such a torque measurement also requires measuring means generally having a bulk and an additional mass in the gas turbine. Objectives of the Invention The invention aims to overcome at least some of the disadvantages of known gas turbine start devices and methods.
    [0002] In particular, the invention aims to provide, in at least one embodiment of the invention, a device and a start-up method which makes it possible to control the start-up of a gas turbine without requiring a direct measurement of the torque. the turbine. The invention also aims to provide, in at least one embodiment, a starting device which ensures a robust start of the gas turbine. The invention also aims to provide, in at least one embodiment, a starting device that allows to apply to the turbine a startup profile in several phases. The invention also aims to provide, in at least one embodiment, a starting device that allows good management of the transient startup phases. The invention also aims to provide, in at least one embodiment, a starting device for a gain in performance. The invention also aims to provide, in at least one embodiment, a starting device for reducing the starting time. The invention also aims to provide, in at least one embodiment, a method for regulating the speed of rotation of a gas turbine. 4. DESCRIPTION OF THE INVENTION To this end, the invention relates to a device for starting a gas turbine, comprising a launching system capable of driving on command said gas turbine in rotation, characterized in that it comprises: means for receiving information representative of the speed of rotation of the gas turbine, means for calculating a torque setpoint as a function of said information representative of the speed of rotation of the gas turbine, means for transmitting said torque setpoint to the launch system. A starting device according to the invention therefore allows the turbine to be started according to information representative of the speed of the gas turbine by applying a starting torque setpoint via the launching system. Unlike the torque of the turbine, and particularly the resistant torques of the turbine, the speed of rotation of the gas turbine is measurable, for example by a speed sensor which transmits information representative of the speed of rotation to the receiving means of the turbine. this information, for example in the form of a digital data carried by an electrical signal. The torque setpoint makes it possible to regulate very precisely the rotation of the turbine according to a rotational speed profile of the gas turbine during start-up, and thus allows a more robust start. Advantageously and according to the invention, the device comprises: a fuel metering device adapted to inject fuel into a combustion chamber of said gas turbine, means for calculating a fuel metering setpoint according to said representative information speed, and means for transmitting the fuel metering setpoint to said fuel metering device. According to this aspect of the invention, the device makes it possible to manage the injection of the fuel into the combustion chamber of the gas turbine during the start-up of the gas turbine to provide additional torque to the turbine which adds to the torque brought by the launch system. Thus, the device manages, according to the information representative of the speed, the rotation of the gas turbine by the launching system and the fuel metering device to better control different starting phases. In particular, the transitions between phases where the rotation is due solely to the launch system, or only to the fuel injection or a combination of both, are more robust.
    [0003] Advantageously and according to the invention, the means for receiving an information representative of the speed of rotation of the gas turbine, the means for calculating the torque setpoint, the means for calculating the fuel metering setpoint. , the transmission means of the torque setpoint and the transmission means of the fuel metering setpoint are embedded in a control unit driving said gas turbine. The control unit used is for example an engine control unit (or ECU for Engine Control Unit in English) for controlling a multitude of elements of the turbine through a multitude of actuators, or a FADEC (for Full Authority Digital Engine Control).
    [0004] According to this aspect of the invention, the control unit makes it possible to pool the means for calculating and transmitting the torque setpoint and the fuel metering setpoint in a single device. The control unit can also control other features of the gas turbine.
    [0005] Advantageously and according to the invention, the launching system is able to drive the gas turbine in rotation by means of a relay box. According to this aspect of the invention, the relay box allows transmission of the torque of the launch system to the gas turbine, optionally modulated by a reduction coefficient.
    [0006] Advantageously and according to the invention, the launching system comprises an electric machine capable of rotating said gas turbine, and a control system of the electric machine configured to receive said torque setpoint and to control the supply of said electric machine according to the 25 torque instruction. According to this aspect of the invention, the control system of the electrical machine receives the torque setpoint for example by means of its control electronics, and translates it into control on the electric machine, which applies the torque to the gas turbine.
    [0007] The invention also relates to a method for regulating the speed of rotation of a gas turbine configured to be driven by a launching system, characterized in that it comprises: a step of receiving a representative piece of information the speed of rotation of the gas turbine, a step of calculating a torque setpoint as a function of said information representative of the speed of rotation of the gas turbine, a step of transmitting said torque setpoint to the system launch. A control method according to the invention thus makes it possible to create a loop for regulating the speed of rotation of the turbine in order to allow efficient control of said speed. Advantageously and according to the invention, the control method comprises: a step of calculating a fuel metering setpoint as a function of said information representative of the speed, a step of transmitting the fuel metering setpoint to a metering device fuel adapted to inject fuel into a combustion chamber of the gas turbine according to said fuel metering instruction.
    [0008] Advantageously, the regulation method according to the invention is implemented by the starting device according to the invention. Advantageously, the starting device according to the invention implements the regulation method according to the invention.
    [0009] The invention also relates to a method of starting a gas turbine, characterized in that the speed of rotation of the gas turbine is regulated according to a control method according to the invention, and in that it comprises successively and in this order: a step of launching the gas turbine by the launching system, during which the torque setpoint is calculated so that the speed of rotation of the gas turbine varies by a speed at a speed called ignition speed, a step of ignition of the gas turbine, a step of starting up the gas turbine, during which the torque setpoint and the fuel metering setpoint are calculated so to increase the speed of rotation of the gas turbine to a speed called transition speed, a transition step, during which the torque setpoint is fixed and the fuel metering setpoint is calculated so as to increase the flow rate; rotational speed of the gas turbine, a step of normal operation, during which the torque setpoint is zero and the fuel metering setpoint is calculated so as to vary the speed of rotation of the gas turbine. A starting method according to the invention thus allows a robust and efficient starting of the gas turbine by regulating the speed according to the control method. The speed is regulated according to several start-up phases in order to allow a fast and efficient start. The transitions between the phases are improved by calculating the torque setpoints of the launching system and the fuel metering setpoint of the fuel metering device according to the information representative of the speed of rotation of the gas turbine. In addition, the starting method of the invention is reproducible on several starts of the gas turbine because it depends on the speed of rotation of the gas turbine and is insensitive to changes in external conditions. Preferably, at the ignition stage of the gas turbine, the torque setpoint is calculated so as to maintain the speed of rotation of the gas turbine at the ignition speed until combustion of the fuel injected by the fuel metering device according to the fuel metering instruction. Stabilization of the speed at the ignition rate during the ignition step enables ignition of the optimized gas turbine and reduces the number of aborted starts due to too low or too high a firing rate.
    [0010] Advantageously, the starting method according to the invention is implemented by the starting device according to the invention. Advantageously, the starting device according to the invention implements the starting method according to the invention.
    [0011] The invention also relates to a gas turbine comprising a starting device according to the invention. The invention also relates to a turbine engine comprising a gas turbine according to the invention. The invention also relates to a starting device, a start-up method, a control method, a gas turbine and a turbine engine characterized in combination by all or some of the characteristics mentioned above or below. 5. BRIEF DESCRIPTION OF THE DRAWINGS Other objects, features and advantages of the invention will become apparent on reading the following description given solely by way of nonlimiting example and which refers to the appended figures in which: FIG. 1 is a diagrammatic representation of FIG. 2 is a schematic representation of a control method according to one embodiment of the invention, FIG. 3 is a velocity profile of one embodiment of the invention. FIG. gas turbine started according to a starting method according to one embodiment of the invention. 6. Detailed Description of an Embodiment of the Invention The following embodiments are examples. Although the description refers to one or more embodiments, this does not necessarily mean that each reference relates to the same embodiment, or that the features apply only to a single embodiment. Simple features of different embodiments may also be combined to provide other embodiments.
    [0012] Figure 1 schematically shows a device 10 for starting a gas turbine 12 according to one embodiment of the invention. The purpose of the starting device 10 is to allow the turbine 12 to start when it is not rotating. In the absence of rotation, the gas in the turbine 12 can not be burned to cause rotation of the turbine 12. Thus, to allow the turbine 12 to start, a launching system 14 is connected to the turbine in order to to be able to activate its rotation. According to the embodiment shown in FIG. 1, the launching system 14 is composed of an electric machine 18, for example an alternator, and a control system 16 for the electric machine, for example an inverter. The control system 16 of the electric machine brings electrical energy to the electric machine 18 so that the latter can cause the rotation of the gas turbine 12 through a relay box 20. To control the system 14 the starting device 10 comprises means for applying a predefined speed profile to the turbine 12. An example of such a speed profile is described later in the description with reference to FIG. are in particular: means 22 for receiving information representative of the speed of rotation of the gas turbine 12. This information is for example transmitted by a turbine speed sensor 24 of the turbine 12. means 26 for calculating a torque setpoint as a function of said information representative of the speed of rotation of the gas turbine 12. These calculation means 26 make it possible to determine the torque setpoint that must be applied to the gas turbine 12 by the launch system 14. means 28 for transmitting said torque setpoint to the launching system 14, and more particularly to the control system 16 of the electric machine. The control system 16 of the electric machine is then responsible for controlling the electrical machine 18 by its power supply, in order to apply to the gas turbine 12 the torque corresponding to the transmitted torque setpoint. In this embodiment, the starting device 10 further comprises a fuel metering device 30 which allows the injection of fuel into a combustion chamber 32 of the gas turbine 12. A type of fuel metering device 30 is, for example, an FM U for Fuel Metering Unit in English. The fuel metering device 30 injects the fuel into the combustion chamber 32 of the gas turbine 12 so that it is burned, this combustion allowing the rotation of the gas turbine 12, in particular under normal operating conditions, at the following the 5 start. To allow a suitable fuel metering, the starting device 10 comprises means 34 for calculating a fuel metering setpoint as a function of the information representative of the speed of rotation of the gas turbine 12 and the transmission means 36. from the fuel metering setpoint to the fuel metering device. The fuel dosing setpoint is calculated as a function of the rotational speed of the turbine and the fuel injection allows combustion of the latter in the turbine to provide additional torque to the gas turbine, which adds to the torque brought by the launching system 14. In this embodiment, the means 22 for receiving the information 15 representative of the speed, the means 26 for calculating the torque setpoint, the means 34 for calculating the fuel metering setpoint, the means 28 for transmitting the the torque setpoint and the transmission means 36 of the fuel metering instruction are embedded in a single equipment, called control unit 38. This control unit 38 makes it possible to simultaneously manage the launching system 14 and the fuel metering device 30 to allow a more robust start. This control unit 38 may also have more features related to the gas turbine 12, not described here. The equipment that can act as a control unit 38 is, for example, an ECU for an Engine Control Unit in English, in particular a FADEC for Full Authority Digital Engine Control in English, which is a piece of equipment regularly used in the field of electronic control. aeronautics for use of the gas turbine 12 as the turbine of a turbine engine. In addition, in this embodiment, the means 26 for calculating the torque setpoint and the means 34 for calculating the fuel metering setpoint are combined in the same computing device 40. This allows adjustment between the two set points 30 to obtain the desired gas turbine torque 12 by combining the effects of the launch system 14 and the fuel metering device 30.
    [0013] FIG. 2 diagrammatically represents a method 42 of regulation according to one embodiment of the invention. The control method 42 is advantageously implemented by the device 10 described in connection with FIG. 1. The control method 42 comprises a step 44 for receiving information representative of the speed of rotation of the gas turbine 12 . This information is compared with a predetermined speed profile 46, such as for example described with reference to FIG. 3. This comparison, represented by the reference 48, then makes it possible, during a step 50 of calculating the torque setpoint and a step 52 for calculating the fuel dosing setpoint, determining the torque setpoint and the fuel metering setpoint as a function of the actual rotation speed and the desired rotation speed of the turbine 12, and possibly according to a phase In this embodiment, the two calculation steps 50, 52 are combined in a single step 54, in order to allow a more robust regulation by using both the launching system 14. and fuel injection by the fuel metering device to provide the torque necessary for speed regulation. The torque setpoint is transmitted to the control system of the electric machine during a step 56 for transmitting the torque setpoint. The control system 16 of the electric machine controls the electrical machine 18 according to this setpoint, which then applies a torque to the turbine 12 during a step 58 for applying the torque of the launching system. The resulting torque is represented by the arrow 60. Moreover, the fuel metering setpoint is transmitted to the fuel metering device during a step 62 of transmission of the fuel metering set point, which allows the injection of fuel into the chamber combustion of the gas turbine. The combustion of the gas makes it possible to apply torque to the turbine 12 during a step 64 for applying the torque of the fuel metering device. The resulting torque is represented by the arrow 66. The total torque applied to the turbine, represented by the arrow 68, is therefore the addition of the two couples coming from the launch system 14 and the fuel metering device 30. This total torque makes it possible to cause rotation of the turbine 12 at a certain speed, represented by step 69, of which representative information 3025252 11 is received during the step 44 of receiving information representative of the speed: the The control method thus constitutes a closed control loop. FIG. 3 shows a speed profile of a gas turbine engine started according to a starting method according to one embodiment of the invention. The profile represents the speed V of rotation as a function of time t, according to two curves, a curve 72 of speed reference, representing the speed of rotation that the turbine must theoretically follow, and the measured speed curve 74, representing the speed of rotation. rotation of the turbine 12 actually measured.
    [0014] The velocity profile 70 makes it possible to distinguish the various steps of a start-up process of the gas turbine 12: In the launching step A, the launching system 14 only drives the rotation of the gas turbine 12, the combustion of the gas in the turbine 12 has not started. The ignition step B makes it possible to ignite the gas injected into the combustion chamber 32 of the gas turbine 12 by the fuel metering device 30 in order to cause the combustion of the gas and to cause the rotation of the gas. 12 gas turbine. To ensure ignition in good conditions, the rotational speed of the gas turbine 12 is maintained at a speed called ignition speed Va. In step C of start-up of the gas turbine 12, the speed of rotation of the turbine 12 increases progressively mainly due to the action of the launching system 14 and partly thanks to the combustion of the injected fuel. The torque setpoint and the dosing setpoint are calculated so that the action of the launching system 14 and the combustion of the fuel injected with the air sucked by the gas turbine apply the desired torque to the gas turbine 12 .
    [0015] Once a so-called transition speed velocity Vt has been reached, the starting method goes into the transition step D, during which the torque set point is fixed, and the fuel metering setpoint is calculated so as to increase the rotation speed. Thus, it is the fuel that regulates the speed of the turbine 12 so as to follow the speed profile, the launching system 14 applying only a fixed torque. Finally, in step E of normal operation, the start is finished and the turbine 12
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device for starting a gas turbine (12), comprising a launching system (14) adapted to drive on command said turbine (12) with rotating gas, characterized in that it comprises: means (22) for receiving information representative of the rotational speed of the gas turbine (12), means (26) for calculating a torque setpoint as a function of said information representative of the speed of rotation of the turbine (12) gas, means (28) for transmitting said torque setpoint to the launching system (14).
    [0002]
    2. Starting device according to claim 1, characterized in that it comprises: - a fuel metering device (30) adapted to inject fuel into a combustion chamber (32) of said gas turbine (12); means (34) for calculating a fuel metering setpoint as a function of said information representative of the speed, and - means (36) for transmitting the fuel metering setpoint to said fuel metering device (30).
    [0003]
    3. Starting device according to claim 2, characterized in that the means (22) for receiving information representative of the rotational speed of the gas turbine (12), the means (26) for calculating the setpoint. the means (34) for calculating the fuel metering setpoint, the means (28) for transmitting the torque setpoint and the means (36) for transmitting the fuel metering setpoint are embedded in a unit (38). ) controlling said gas turbine (12).
    [0004]
    4. Starting device according to one of the preceding claims, characterized in that the launching system (14) is adapted to drive in rotation the gas turbine (12) through a relay box (20). .
    [0005]
    5. Starting device according to one of the preceding claims, characterized in that said system (14) for launching comprises an electric machine (18) adapted to rotate said gas turbine (12), and a system (16). ) driving the electric machine (18) configured to receive said torque setpoint and to control the supply of said electrical machine (18) according to the torque setpoint. 10
    [0006]
    6. A method for regulating the speed of rotation of a gas turbine (12) configured to be driven by a launching system (14), characterized in that it comprises: a step (44) for receiving a information representative of the speed of rotation of the gas turbine (12), a step (50) for calculating a torque setpoint as a function of said information representative of the speed of rotation of the gas turbine (12), a step (56) of transmitting said torque setpoint to the launching system (14).
    [0007]
    7. Control method according to claim 6, characterized in that it comprises: a step (52) for calculating a fuel metering setpoint as a function of said information representative of the speed, a step (62) transmission of the fuel dosing setpoint to a fuel metering device (30) adapted to inject fuel into a combustion chamber (32) of the gas turbine according to said fuel metering instruction. 30
    [0008]
    8. A method of starting a gas turbine, characterized in that the speed of rotation of the gas turbine (12) is regulated according to a control method according to claim 7, and in that it comprises successively and in this order: a step (A) of launching the gas turbine (12) by the launching system (14), during which the torque setpoint is calculated so that the speed of rotation of the turbine (12) gas varies from a zero speed to a so-called ignition speed (Va), a stage (B) ignition of the gas turbine, during which the torque setpoint is calculated so as to maintain the the speed of rotation of the gas turbine (12) at the ignition speed until the combustion of the fuel injected by the fuel metering device (30) according to the fuel metering instruction, a step (C) of setting gas turbine road (12), during which the torque setpoint and the AC dosing setpoint fuel are calculated so as to increase the speed of rotation of the gas turbine (12) to a so-called transition speed (Vt), a transition step (D), during which the torque setpoint is fixed and the fuel metering setpoint is calculated so as to increase the speed of rotation of the gas turbine (12), a step (E) of normal speed, during which the torque setpoint 20 is zero and the fuel metering setpoint is calculated so as to vary the rotational speed of the gas turbine (12).
    [0009]
    9. Gas turbine, characterized in that it comprises a device (10) for starting according to one of claims 1 to 5. 25
    [0010]
    10. Turbomotor, characterized in that it comprises a gas turbine (12) according to claim 9.
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    同族专利:
    公开号 | 公开日
    EP3186489A1|2017-07-05|
    US20170248080A1|2017-08-31|
    EP3186489B1|2019-10-30|
    CN106795814A|2017-05-31|
    CN106795814B|2019-05-17|
    FR3025252B1|2021-10-29|
    WO2016030616A1|2016-03-03|
    RU2017107451A3|2018-12-17|
    RU2017107451A|2018-10-01|
    RU2690600C2|2019-06-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6836086B1|2002-03-08|2004-12-28|Hamilton Sundstrand Corporation|Controlled starting system for a gas turbine engine|
    US20070132245A1|2005-09-15|2007-06-14|Hamilton Sundstrand Corporation|Electrical starter generator system for a gas turbine engine|
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    WO2014037649A1|2012-09-10|2014-03-13|Turbomeca|Method and system for starting an aircraft turboengine|WO2019129952A1|2017-12-29|2019-07-04|Safran Aircraft Engines|Method for starting a turbine engine in cold weather and system for starting a turbine engine|
    US11131211B2|2017-05-10|2021-09-28|Pratt & Whitney Canada Corp.|Method and system for setting an acceleration schedule for engine start|
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    RU2628008C1|2016-04-22|2017-08-14|Открытое Акционерное Общество "Российские Железные Дороги"|Method for regulating power of gas turbine - generator system|
    CN108757186B|2018-05-11|2019-08-27|中国航发动力股份有限公司|A kind of digital revolution speed control system of gas turbine and method|
    FR3101918A1|2019-10-15|2021-04-16|Safran Aircraft Engines|Method of starting a turbine engine, Device, turbine engine, AERONEF and computer program product|
    法律状态:
    2015-08-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-04| PLSC| Publication of the preliminary search report|Effective date: 20160304 |
    2016-06-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-04| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-04| CD| Change of name or company name|Owner name: LABINAL POWER SYSTEMS, FR Effective date: 20170703 Owner name: SAFRAN POWER UNITS, FR Effective date: 20170703 |
    2017-11-03| CA| Change of address|Effective date: 20171002 |
    2018-01-19| CA| Change of address|Effective date: 20171218 |
    2018-01-19| CD| Change of name or company name|Owner name: SAFRAN ELECTRICAL & POWER, FR Effective date: 20171218 Owner name: SAFRAN POWER UNITS, FR Effective date: 20171218 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458114A|FR3025252B1|2014-08-29|2014-08-29|DEVICE AND METHOD FOR STARTING A GAS TURBINE, METHOD FOR REGULATING THE ROTATION SPEED OF A GAS TURBINE, AND ASSOCIATED GAS TURBINE AND TURBOMOTOR|FR1458114A| FR3025252B1|2014-08-29|2014-08-29|DEVICE AND METHOD FOR STARTING A GAS TURBINE, METHOD FOR REGULATING THE ROTATION SPEED OF A GAS TURBINE, AND ASSOCIATED GAS TURBINE AND TURBOMOTOR|
    PCT/FR2015/052247| WO2016030616A1|2014-08-29|2015-08-21|Device and method for starting a gas turbine, method for regulating the rotational speed of a gas turbine, and associated gas turbine and turbine engine|
    RU2017107451A| RU2690600C2|2014-08-29|2015-08-21|Gas turbine start-up device and method, gas turbine rotation speed control method and corresponding gas turbine and gas turbine engine|
    CN201580045475.5A| CN106795814B|2014-08-29|2015-08-21|For starting the device and method of gas turbine, the method for regulating gas secondary speed and relevant gas turbine and turbogenerator|
    US15/506,147| US20170248080A1|2014-08-29|2015-08-21|Device and method for starting a gas turbine, method for regulating the rotation speed of a gas turbine, and associated gas turbine and turbine engine|
    EP15759914.3A| EP3186489B1|2014-08-29|2015-08-21|Device and method for starting a gas turbine, method for regulating the rotational speed of a gas turbine, and associated gas turbine and turbine engine|
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