• 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 notifying a complete shutdown authorization of an aircraft gas turbine engine, comprising, following the detection (E10) of a passage of the engine at an idle speed: a) a step (E20) of evaluating, from a value of a first operating parameter of the engine, a value of a second parameter T45MG characterizing a thermal behavior of a part of the engine subject to coking ; (b) a step (E30) of comparing the value of the second parameter T45MG with a predefined threshold value T45threshold corresponding to a value of the second parameter that does not generate coking of said part; and (c) an engine stop enable notification (E50) step if the value of the second T45MG parameter is less than the predefined T45 threshold threshold value, with steps (a) through (c) being repeated otherwise. The invention also relates to a device implementing such a method.
    公开号:FR3027061A1
    申请号:FR1459756
    申请日:2014-10-10
    公开日:2016-04-15
    发明作者:Olivier Pierre Descubes；Jean-Michel Pierre Claude Py
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of aircraft gas turbine engines for which it is necessary to maintain a ground idle time prior to controlling a complete stopping of the engine. In the aeronautical field, it is customary to indicate in the operating manuals intended for the pilots of an aircraft to respect a certain duration at a speed of operation of the so-called "idling" engine 10 before ordering a complete engine stop. . This period of so-called "engine stabilization" is mainly related to the risk that the engine oil or fuel will coke at the hot parts of the engine (for example at the fuel injectors in the combustion chamber of the engine) . To avoid too much coking of these hot parts of the engine, it is thus recommended to let the engine run idle for a certain period of time before it is completely shut down. The duration of this engine stabilization phase is generally predefined according to the type of engine and is typically between 30 seconds and 2 minutes. However, imposing a fixed stabilization period has many disadvantages. Indeed, if one chooses to cover the worst possible thermal situation for the engine, the stabilization time is necessarily high, which imposes a waiting time penalizing the crew of the aircraft before being able to stop completely. engine. On the other hand, if one chooses to minimize this constraint for the crew, the stabilization time should be as short as possible, which can expose the engine to important phenomena of coking eventually leading to significant costs and maintenance times. .
    [0002] There is therefore a need for a method of determining an idling time of an aircraft gas turbine engine prior to its complete shutdown which does not have the aforementioned drawbacks relating to the establishment of a fixed duration of stabilization.
    [0003] SUMMARY OF THE INVENTION The present invention responds in particular to this need by proposing a method of notifying a complete shutdown authorization of an aircraft gas turbine engine, comprising, following detection. a passage of the engine at an idle speed: (a) a step of evaluating, from a value of a first operating parameter of the engine, a value of a second parameter characterizing a thermal behavior a part of the engine subject to coking, this evaluation being carried out by means of a model of thermal behavior of said part; (b) a step of comparing the value of the second parameter with a predefined threshold value corresponding to a value of the second parameter that does not generate coking of said part; and (c) a motor full stop enable notification step if the value of the second parameter is less than the predefined threshold value, steps (a) through (c) being repeated otherwise. Correlatively, the invention also relates to a device for notifying a complete shutdown authorization of an aircraft gas turbine engine, comprising: evaluation means, from a value of a first engine operating parameter, a value of a second parameter characterizing a thermal behavior of a part of the engine subject to coking, this evaluation being carried out by means of a model of thermal behavior of said part; means for comparing the value of the second parameter with a predefined threshold value corresponding to a value of the second parameter that does not generate coking of said part; and means of notification of authorization of complete shutdown of the engine. The invention thus proposes a judicious mechanism that makes it possible to adapt the stabilization time of the engine as a function of the actual operation of the latter. From a model of thermal behavior of a part of the engine subject to coking, and thanks to the simple knowledge of an operating parameter of the engine, this mechanism, which can be integrated directly into the computer 3027061 3 electronic of the engine, allows to determine in an effective way the necessary duration that the pilot will have to respect before completely stopping the motor. This mechanism is simple to implement (it does not require any particular tools or measuring instruments, the operating parameter that it uses being a parameter already monitored for other monitoring functions of the motor) and makes it possible to calculate just as much time as necessary to avoid excessive coking of the hot parts of the engine. By avoiding any risk of excessive coking, the mechanism according to the invention thus reduces the costs and the engine maintenance time. In addition, this mechanism makes it possible to optimize flight and flight control procedures by making this engine stabilization phase simpler for the pilot. Finally, it is possible, with such a mechanism, to anticipate the maintenance operations according to the non respect of the stabilization periods on the ground and the counting of the number of stabilization phases whose duration has been high. Advantageously, the evaluation of a value of the second parameter may include calculating an average value of the first operating parameter of the engine over a sliding time window. Advantageously also, the method may further comprise triggering a stopwatch following the detection of a passage of the engine at an idle speed, and the notification of authorization to stop the engine completely when the time has elapsed. since the start of the stopwatch exceeds a predetermined threshold duration. Typically, a predetermined duration of threshold will be chosen, a duration of which it is known from experience that it covers the worst possible thermal situation for the engine. For example, this threshold duration may be equal to 2mn. Thus, this additional step makes it possible to reduce the stabilization time if the average value of the engine operating parameter takes time to go back down to pass below the predefined threshold value.
    [0004] The first parameter may be selected from the following engine operating parameters: a temperature measured in a flow channel of a gas stream between two turbine stages, a measured ambient temperature at the inlet of the engine, engine, an engine oil temperature, an engine fuel temperature, and an engine operating speed.
    [0005] 5 In addition, the notification of authorization to stop the complete engine may consist of a visual display indicating to the pilot one or more of the following information: authorization to stop the engine, complete engine shutdown with risk of coking, display of the engine a necessary waiting time previously estimated before authorization for complete shutdown of the engine. The passage of the engine at an idle speed may be detected following the actuation by the pilot of the aircraft of a switch or following the detection of an operating speed of the engine which corresponds to an idling speed, or of a assimilated thermal state.
    [0006] In a particular embodiment, the various steps of the method are determined by computer program instructions. Accordingly, the invention also relates to a computer program on an information medium, this program being capable of being implemented in a notification device or more generally in a computer, this program comprising instructions adapted to the implementing the steps of a method as described above. This program can use any programming language, and be in the form of source code, object code, or intermediate code between source code and object code, such as in a partially compiled form, or in any other form desirable shape. The invention also relates to a computer-readable information medium, comprising instructions of a computer program as mentioned above. The information carrier may be any entity or device capable of storing the program. For example, the medium may comprise storage means, such as a ROM, for example a CD ROM or a microelectronic circuit ROM, or a magnetic recording medium, for example a floppy disk. or a hard drive. On the other hand, the information medium may be a transmissible medium such as an electrical or optical signal, which may be conveyed via an electrical or optical cable, by radio or by other means. The program according to the invention can be downloaded in particular on an Internet type network. Alternatively, the information carrier may be an integrated circuit in which the program is incorporated, the circuit being adapted to execute or to be used in the execution of the method in question. The invention also relates to an aircraft gas turbine engine comprising a device as defined above.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will become apparent from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures: FIG. 1 represents, in the form of a flow chart, the main steps of a method for determining an idling stabilization time according to the invention; and FIG. 2 is a graph showing an exemplary implementation of the method according to the invention.
    [0008] DETAILED DESCRIPTION OF THE INVENTION FIG. 1 represents, in the form of a flow chart, the main steps of a method for notifying a complete shutdown authorization of an aircraft gas turbine engine according to the invention. .
    [0009] The authorization for a complete shutdown of an aircraft gas turbine engine, for example a commercial jet engine, follows the landing and taxiing phases of an aircraft after a flight. . This authorization of complete stop aims to enforce a certain duration of operation at idle speed before ordering a complete stop of the engine in order to avoid any risk of coking of oil 3027061 6 or fuel of the hot parts of the engine, such as for example the fuel injectors in the combustion chamber. The method according to the invention aims to define an operating time at idle before complete shutdown of the engine which is variable according to certain operating parameters of the engine characterizing a thermal behavior of a part of the engine subject to coking. For this purpose, as shown in FIG. 1, the method according to the invention comprises a first step E10 which consists of detecting whether the engine has been at idling speed. This changeover to the idling speed can be detected following the actuation by the pilot of the aircraft of a switch or following the detection of an operating speed of the engine which corresponds to an idling speed, such detection being achievable from one of the 15 parameters seen by the computer as indication of collective pitch, gas generator speed, turbine outlet temperature, etc. Once it has been detected that the engine is operating at idle speed, the method according to the invention provides, during a step E20, of evaluating, from a value of a first operating parameter. 20 of the engine, a value of a second parameter characterizing a thermal behavior of a part of the engine subject to coking. The value of the first parameter can be calculated continuously or on an event indicating that the engine will be put into a stopping condition.
    [0010] The first engine operating parameter used in this evaluation step E20 typically corresponds to a temperature measured in the engine in the vicinity of the coking part. For example, this first operating parameter may be chosen from the following parameters: a temperature measured in a flow channel of a gas flow between two turbine stages (hereinafter referred to as T45), an ambient temperature measured at a temperature of motor input, engine oil temperature, engine fuel temperature, engine operating speed, etc.
    [0011] These examples have the advantage of being parameters that are already monitored during the mission of the aircraft. Typically, the measured values for these parameters are sent continuously during the mission to the computer of the engine control device for analysis. From a model of thermal behavior of the part 5 for which the first parameter is measured, it is then evaluated a value of a second parameter characterizing a thermal behavior of said part. This thermal behavior model is a function (also called integral operator) which, starting from an input value of an operating parameter (such as a temperature measured in the engine in the vicinity of the part), to model the thermal behavior of the room. In an exemplary embodiment of the applied invention in which the first operating parameter is the temperature T45 measured in a flow channel of a gas flow between two turbine stages of the engine, the thermal behavior model may be a calculating the T45MG average of the values of the temperature T45 measured over a sliding time window of a predetermined duration (for example of the order of a few minutes).
    [0012] The evaluation step E20 can be carried out during the entire mission, from start to complete shut down of the engine. It can be performed by means of a calculation software embedded in the engine computer and thus makes it possible to obtain continuously a value for the second parameter characterizing a thermal behavior of the part 25 subject to coking (in the illustrated example: T45MG). In parallel with this evaluation step E20, the method can provide, in a step E20 ', to trigger a stopwatch CM from the moment when the passage of the engine at an idle speed is detected. The next step E30 consists in comparing the value of the second parameter obtained in step E20 (here the average T45MG) with a predefined threshold value (here T45 threshold). This comparison step is performed by a calculation software embedded in the engine computer. The threshold value T45seuil corresponds to a value of the second parameter for which it has been previously established that it does not generate coking of the part.
    [0013] 3027061 8 This threshold value T45seuil is pre-established from a multi-input table (for example with the temperature and the engine inlet pressure, the oil temperature, the fuel temperature, etc.) and according to the engine measurements at the time of detection of the passage of the engine at an idle speed. This table is typically developed by feedback from data from previous missions for engines of the same family as the one in question. At the end of this comparison step E30, if it is established, during a step E40, that the value of the second parameter T45MG is less than the predefined threshold value T45 threshold, the engine computer notifies the pilot a permission to stop the engine completely (step E50). On the other hand, if the value of the second parameter T45MG is greater than the predefined threshold value T45 threshold, steps E30 and E40 are repeated. In other words, if the value of the second parameter T45MG is greater than the predefined threshold value T45threshold, the engine calculator will make a new comparison between the calculation of the average T45MG from the new values of the temperature T45 measured on the sliding time window and compare this value with the predefined threshold value (T45 threshold), the latter being able to vary as a function of time. This process of evaluating the average T45MG and comparing it with the predefined threshold value T45seuil is repeated until the value of the average T45MG becomes lower than the predefined threshold value T45seuil, in which case the calculator notify the pilot of an authorization to stop the engine completely. On the other hand, when a chronometer CM has been triggered during the step E20 ', the method provides, during the step E40, to check whether the elapsed time since the start of the stopwatch has exceeded a threshold duration predetermined (typically of the order of 2 minutes) at which the engine computer notifies the pilot authorization to stop the engine (step E50). On the other hand, if the elapsed time is less than the predetermined threshold duration, steps E20 to E40 are repeated as previously described.
    [0014] Step E50 of notifying the pilot of a full engine stop permission can take many forms. It may in particular 3027061 9 consist of a visual display indicating to the pilot one or more of the following information: authorization for complete shutdown of the engine, complete shutdown of the engine with risk of coking (the risk is reported as the stabilization before stopping n is not sufficient), display of a waiting time required previously estimated before authorization of complete shutdown of the engine. In connection with Figure 2, we will now describe an example of implementation of the process steps E20 and E30 as described above.
    [0015] In this example, the first operating parameter of the engine is the temperature T45 measured in a flow channel of a gas flow between two turbine stages of the engine and the second parameter characterizing a thermal behavior of a part of the engine subject. The coking rate is a T45MG average of the values of the T45 temperature measured over a sliding time window of a predetermined duration. Figure 2 shows temperature curves as a function of time. In this example, the temperature curve T45 measured continuously is shown. From this temperature T45, the computer 20 of the engine calculates a mean value T45MG of the temperature on a sliding window, corresponding for example here to the last 5 temperature measurements performed. The curve of this average value T45MG is also shown in FIG. 2 (this average value T45MG is calculated continuously from start to stop of the motor).
    [0016] The average value T45MG is then compared to a threshold temperature T45 threshold which is constant here over the entire duration of the engine stopping phase and which is equal to about 940 °. As soon as the average value T45MG becomes lower than this threshold temperature T45threshold, here at a stop time of about 4300 seconds, the engine computer 30 sends the pilot notification of authorization to stop the engine completely. Thus, the period of stabilization of the engine before stopping the engine will taret duration "is about 25 seconds.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of notifying a complete shutdown authorization of an aircraft gas turbine engine, comprising, following the detection (E10) of a passage of the engine at an idle speed: (a) a step ( E20) for evaluating, from a value of a first engine operating parameter (T45), a value of a second parameter (T45MG) characterizing a thermal behavior of a part of the engine subject to coking. this evaluation being carried out by means of a model of thermal behavior of said part; (b) a step (E30) of comparing the value of the second parameter (T45MG) with a predefined threshold value (T45seuil) corresponding to a value of the second parameter that does not generate coking of said piece; and (c) a step (E50) of notification of authorization of complete stop of the engine if the value of the second parameter (T45MG) is lower than the predefined threshold value (T45seuil), the steps (a) to (c) being repeated otherwise.
    [0002]
    The method of claim 1, wherein evaluating a value of the second parameter includes computing an average value of the first operating parameter of the engine over a sliding time window.
    [0003]
    3. Method according to one of claims 1 and 2, further comprising: triggering (E20 ') a stopwatch (CM) following the detection of a passage of the engine at an idle speed; and the notification (E50) of authorization to stop the engine when the time elapsed since the start of the stopwatch exceeds a predetermined threshold duration.
    [0004]
    4. A method according to any one of claims 1 to 3, wherein the first parameter is selected from the following engine operating parameters: a temperature measured in a flow channel of a gaseous flow between two stages turbine, an ambient temperature measured at the engine inlet, an engine oil temperature, an engine fuel temperature, and an engine operating speed. 5
    [0005]
    5. A method according to any one of claims 1 to 4, wherein the notification of authorization for complete engine shutdown consists of a visual display indicating to the pilot one or more of the following information: authorization for complete shutdown of the engine, complete shutdown of the engine with risk of coking, display of a necessary waiting time previously estimated before authorization of complete shutdown of the engine.
    [0006]
    6. A method according to any one of claims 1 to 5, wherein the passage of the engine at an idle speed is detected following the actuation by the pilot of the aircraft of a switch or following the detection of an engine operating speed which corresponds to an idling speed. 20
    [0007]
    A computer program comprising instructions for performing the steps of the method according to any one of claims 1 to 6 when said program is executed by a computer. 25
    [0008]
    A computer-readable recording medium on which a computer program is recorded including instructions for executing the steps of the method according to any one of claims 1 to 6.
    [0009]
    9. Device for notification of a complete shutdown authorization of an aircraft gas turbine engine, comprising: evaluation means, based on a value of a first operating parameter of the engine, a value of a second parameter characterizing a thermal behavior of a part of the motor subject to coking, this evaluation being carried out by means of a model of thermal behavior of said part; Means for comparing the value of the second parameter with a predefined threshold value corresponding to a value of the second parameter that does not generate coking of said part; and means of notification of authorization of complete shutdown of the engine.
    [0010]
    An aircraft gas turbine engine comprising a device according to claim 9.
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    同族专利:
    公开号 | 公开日
    US10176648B2|2019-01-08|
    WO2016055738A1|2016-04-14|
    ES2689870T3|2018-11-16|
    RU2017115665A|2018-11-13|
    CN106795815A|2017-05-31|
    JP2017531130A|2017-10-19|
    EP3204618B1|2018-09-05|
    FR3027061B1|2019-10-25|
    EP3204618A1|2017-08-16|
    US20170301157A1|2017-10-19|
    PL3204618T3|2019-01-31|
    KR20170066631A|2017-06-14|
    RU2701928C2|2019-10-02|
    RU2017115665A3|2019-04-18|
    JP6636513B2|2020-01-29|
    CN106795815B|2019-12-06|
    CA2964024A1|2016-04-14|
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    法律状态:
    2015-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-15| PLSC| Search report ready|Effective date: 20160415 |
    2016-10-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-01| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1459756|2014-10-10|
    FR1459756A|FR3027061B1|2014-10-10|2014-10-10|METHOD AND DEVICE FOR NOTIFYING A COMPLETE STOP AUTHORIZATION OF AN AIRCRAFT GAS TURBINE ENGINE|FR1459756A| FR3027061B1|2014-10-10|2014-10-10|METHOD AND DEVICE FOR NOTIFYING A COMPLETE STOP AUTHORIZATION OF AN AIRCRAFT GAS TURBINE ENGINE|
    CN201580054865.9A| CN106795815B|2014-10-10|2015-10-08|Method and apparatus for notifying authorization to completely shut down an aircraft gas turbine engine|
    JP2017518891A| JP6636513B2|2014-10-10|2015-10-08|Method and apparatus for signaling permission to completely shut down an aircraft gas turbine engine|
    CA2964024A| CA2964024A1|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
    RU2017115665A| RU2701928C2|2014-10-10|2015-10-08|Method and device for notifying permission to completely shut off aircraft gas turbine engine|
    ES15788152.5T| ES2689870T3|2014-10-10|2015-10-08|Procedure and notification device for a complete stop authorization of an aircraft gas turbine engine|
    PCT/FR2015/052703| WO2016055738A1|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
    US15/517,713| US10176648B2|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
    PL15788152T| PL3204618T3|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
    EP15788152.5A| EP3204618B1|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
    KR1020177012659A| KR20170066631A|2014-10-10|2015-10-08|Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine|
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