• 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:
    An aircraft turbomachine (100) comprising a first channel (200) communicating a high pressure compressor (30) and a high pressure turbine (50), a second channel (400) communicating the high pressure compressor and a low pressure turbine (60), the first channel being provided with a valve (600), a third channel (700) being in selective communication with the first channel via the valve, the third channel being in communication with the low pressure turbine, the valve having a first configuration in which the air flow in the first channel is allowed and prohibited in the third channel, and a second configuration in which the air circulation of the first channel is first channel is diverted to the third channel, a controller (800) being configured to determine a low pressure turbine air pressure and control according to the determined pressure. e the valve to move it from the first configuration to the second configuration.
    公开号:FR3072414A1
    申请号:FR1759692
    申请日:2017-10-16
    公开日:2019-04-19
    发明作者:Yolande Chantal Ohouan Ekra Devalere；Daniel Bernava；Michael Alain Eric Sauve
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Invention background
    The invention relates to the field of turbomachinery. More specifically, the invention relates to the cooling of a low pressure turbine in an aircraft turbomachine.
    It is common in a turbomachine to take air from a high pressure compressor to cool parts in stages with a warmer environment. The cooling air taken from the high pressure compressor is for example routed to the high pressure and low pressure turbines of the turbomachine. The air supplied then purges the hot air and ventilates the attachment parts (eg discs, moving blades) of these turbines. Such cooling thus makes it possible to guard against any risk of overheating of the moving parts of the turbines, which could lead in the worst case to a rupture of these parts.
    In order to guarantee the compliance of the cooling devices with aeronautical standards, it is also common to oversize these devices.
    For example, even if three air circulation channels taking air from the high pressure compressor appear to be sufficient to cool the low pressure turbine, a fourth air circulation channel to the turbine will be systematically implemented. artwork. The realization of this additional channel ensures that the air flow taken from the high pressure compressor remains sufficient in the event of a channel rupture. Such oversizing thus makes it possible to ensure that any failure of an air circulation channel remains without effect and does not affect the flight safety of the aircraft.
    Although reliable, such oversizing results in taking more air than actually necessary from the high pressure compressor in a nominal operating situation of the turbomachine, for example in the absence of failure of an air circulation channel. Such an air intake significantly impacts the specific fuel consumption (SFC) of the aircraft.
    It is therefore desirable to improve the performance of the turbomachine, in particular to limit the impact of the cooling systems on the fuel consumption of the aircraft.
    Subject and summary of the invention
    The object of the present invention is to remedy the aforementioned drawbacks and to overcome, in particular, the oversizing of the cooling systems.
    To this end, the invention proposes an aircraft turbomachine comprising at least:
    - a high pressure compressor,
    - a high pressure turbine,
    - a low pressure turbine,
    - a first cooling air circulation channel connecting the high pressure compressor and the high pressure turbine,
    a second cooling air circulation channel putting the high pressure compressor and the low pressure turbine in communication, the first channel being provided with a valve, the turbomachine further comprising a third cooling air circulation channel in selective communication with the first channel via the valve, the third channel also being in communication with the low pressure turbine, the valve having a first configuration in which the circulation of air in the first channel is authorized and the circulation air in the third channel is prohibited, and a second configuration in which the flow of air from the first channel is diverted to the third channel.
    Advantageously, it thus becomes possible to dispense with any oversizing for the cooling of the low pressure turbine. While usually a cooling device for a low pressure turbine requires an additional air circulation channel to guarantee good cooling of the turbine, a minimum number of channels for cooling the low pressure turbine is used here. In other words, the low-pressure turbine is cooled to just the right amount by the second channel. During nominal operation of the turbomachine, the air taken from the high-pressure compressor can be both routed to the low-pressure turbine by the second channel with a view to cooling it when necessary and, for example, towards a device for optimizing the performance of the turbomachine via the first channel. The specific fuel consumption of the turbomachine is therefore optimized under nominal operating conditions, these conditions corresponding to the first configuration of the valve.
    If a failure occurs in the turbomachine, for example a rupture of the second duct, the cooling air initially dedicated to the device for optimizing the performance of the turbomachine is diverted towards the low pressure turbine so as to guarantee good cooling of the latter. this. Thus, the performance of the turbomachine in nominal operation, that is to say in the absence of failure, is optimized, in particular in terms of specific fuel consumption.
    In an exemplary embodiment, the turbomachine comprises a control device configured to determine a cooling air pressure of the low pressure turbine and to control the valve as a function of the determined air pressure to cause it to pass from the first configuration to the second configuration.
    In an exemplary embodiment, one end of the second channel and one end of the third channel are connected to a cooling air manifold, the cooling air manifold being further connected to a hollow distributor of the low pressure turbine.
    In an exemplary embodiment, the turbomachine comprises a plurality of second cooling air circulation channels each putting the high pressure compressor and the low pressure turbine in communication.
    In an exemplary embodiment, the control device is configured to determine the cooling air pressure of the low pressure turbine from at least one measurement of a pressure sensor associated with the cooling air manifold.
    In another exemplary embodiment, the control device is configured to determine the value of the cooling air pressure of the low-pressure turbine from at least one measurement of a pressure sensor placed in an enclosure of the turbine low pressure.
    In another exemplary embodiment, the control device is configured to determine the cooling air pressure of the low pressure turbine from a difference in pressure measurements from pressure sensors associated with the plurality of second channels.
    In an exemplary embodiment, the turbomachine further comprises a device for controlling a clearance between the tips of blades of a rotor of the high pressure turbine and a turbine ring of a casing surrounding the blades of the high turbine pressure, one end of the first cooling air circulation channel being in communication with the clearance control device of the high pressure turbine so as to supply it with air when the valve is in the first configuration.
    In an exemplary embodiment, the device for controlling the clearance of the high pressure turbine is a device internal to the turbine ring.
    The invention also proposes, according to another aspect, a method of cooling a low pressure turbine in an aircraft turbomachine produced as summarized above, this method comprising:
    - a sample of air circulating in the high pressure compressor,
    in an initial situation corresponding to the first configuration of the valve, a distribution of the air taken from the high pressure turbine through the first channel and from the low pressure turbine through the second channel,
    the determination of a cooling air pressure of the low pressure turbine and a comparison of the value of the pressure determined at a threshold by the control device, and
    - when the cooling air pressure of the low pressure turbine is below the threshold, the control by the valve control device according to the second configuration, so as to distribute the cooling air from the first channel to the low turbine pressure.
    In an exemplary embodiment of this method, the threshold is predetermined as a function of a failure condition of the second channel.
    Brief description of the drawings
    Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of nonlimiting examples, with reference to the appended drawings, in which:
    FIG. 1 is a view in longitudinal section of a turbomachine equipped with a cooling device according to the invention,
    - Figure 2 is a longitudinal and partial sectional view of a low pressure turbine in a turbomachine according to the invention.
    Detailed description of embodiments
    The terms “upstream” and “downstream” are subsequently defined with respect to the direction of flow of the gases through a turbomachine, indicated by the arrow F in FIGS. 1 and 2.
    FIG. 1 illustrates a turbomachine 100 with double flow comprising in known manner from upstream to downstream successively at least one fan 10, an engine part successively comprising at least one stage of low pressure compressor 20, of high pressure compressor 30, a combustion 40, at least one stage of high pressure turbine 50 and low pressure turbine 60.
    Rotors, rotating around the main axis X of the turbomachine 100 and which can be coupled together by different transmission and gear systems, correspond to these different elements.
    In a known manner, air A is taken from the high pressure compressor 30 with a view to cooling hotter zones of the turbomachine 100, in particular the high pressure 50 and low pressure 60 turbines.
    FIG. 2 is an enlargement of a zone of the turbomachine 100, illustrating in a simplified manner the downstream part of the high pressure turbine 50 and upstream of the low pressure turbine 60.
    The downstream part of the high pressure turbine 50 shown here illustrates a stage 51 comprising at least one movable blade 52 assembled on a movable disc 53 integral in rotation with a high pressure shaft 101.
    The low pressure turbine 60 illustrated here comprises a plurality of turbine stages 61, 62. A first stage 61, as well as the stages 62 situated downstream thereof comprise respectively a set of fixed distributors 70 and 65. Each stage 61, 62 further comprises a movable disc 63 on which is mounted a set of vanes 64 rotated by the movable disc 63. The first stage 61 of the low pressure turbine 60 comprises at least one movable blade 64, as well as at least one hollow distributor 70, in which cooling air circulates. In the example illustrated in FIG. 2, the distributor 70 forms a single piece with a casing 66 constituting this turbine and is hollow to allow cooling air to pass inside, exiting via injectors 72 associated with the distributor 70. The following stages 62, located downstream of the low pressure turbine 60, each comprise at least one movable blade 64 and a distributor 65 in the form of a fixed blade. The movable disc 63 is integral in rotation with a low pressure shaft 102 extending along the axis XX, while each stator 65 is connected to the casing 66. Each turbine stage 61, 62 further comprises a turbine ring 67 located opposite the movable blades 64, and which is integral with the housing 66. Similarly, the stage 51 of the high pressure turbine 50 comprises a housing, here the housing 66, which surrounds the mobile blades 52 (rotors) of the turbine high pressure 50 and comprises a turbine ring (abradable) 54 located opposite the blades 52.
    The blades 52, 64, the stators 65 and the turbine rings 54, 67 are made of CMC material. The casing 66 and the distributor 70 are in turn made of a material having a coefficient of thermal expansion strictly greater than that of the CMC material, for example a metallic material. The moving discs 53, 63 are made of a metallic material.
    According to the invention, the low pressure turbine 60 comprises a cooling device making it possible to convey the air A taken from the high pressure compressor 30. This air A is conveyed through the hollow distributor 70 and is distributed via the injectors 72 in the low pressure turbine 60. In the example illustrated, the injectors 72 open downstream of the stage 51 of the high pressure turbine 50 and upstream of the first stage 61 of the low pressure turbine 60. The air A circulates ( arrows 71) therefore through the hollow distributor 70 and is directed via the injectors 72 to the discs 53, 63 of the high pressure turbines 50 and low pressure 60. The air distributed thus makes it possible to cool the discs 53, 63 of these turbines and bleed the hot air outwards from the casing 66 (arrows 73, 74), thereby limiting any risk of overheating of the rotors of the high pressure 50 and low pressure 60 turbines.
    The air A taken from the high pressure compressor 30 is in particular intended to supply air to one or more devices controlling the performance of the turbomachine 100, to ventilate the stages 61, 62 of the low pressure turbine 60 and to purge the hot air from stages 51, 61, 62 of the high pressure 50 and low pressure 60 turbines.
    Thus, in known manner, at least a first cooling air circulation channel 200 takes air from the high pressure compressor 30. The air taken off can then be routed to at least one device controlling the performance of the turbomachine. 100.
    This device is for example a device for controlling a clearance between, on the one hand, the tops of the blades 52, 64 of the rotor of the high pressure 50 or low pressure 60 turbines and, on the other hand, the rings turbine 54, 67 of the casing 66 surrounding these blades 52, 64. Thus, in the example illustrated, the first channel 200 routes, in a nominal configuration, the air A taken from the high pressure compressor 30 to a device 300 for clearance control J of the high pressure turbine 50. Such a device 300 is commonly known to those skilled in the art under the name HPTACC (“High Pressure Turbine Active Clearance Controi”).
    In another example not illustrated, the first channel 200, or another channel, can convey the air A sampled to a clearance control device of the low pressure turbine 60, that is to say to an LPTACC device (“ Low Pressure Turbine Active Clearance · ”).
    Still in known manner, at least a second cooling air circulation channel 400 draws air from the high pressure compressor 30 to purge the hot air from stages 51, 61, 62 of the high pressure and low pressure turbines. 60, and cooling the low pressure turbine 60. One end 400a of each second channel 400 is connected as an air inlet to a collector 500 for cooling air. The outlet of the cooling air collector 500 is connected to the hollow distributor 70 of the low pressure turbine 60.
    According to the invention, the number of second channels 400 intended to convey the air taken from the high pressure compressor 30 to the low pressure turbine 60 is chosen to meet the just need for cooling of the turbine. In other words, the number of channels 400 is not oversized and corresponds to the minimum number of channels necessary for the ventilation of the discs 63 of the low pressure turbine 60.
    In the example illustrated in FIG. 1, a single channel 400 draws air intended solely for cooling the air of the low pressure turbine 60 under nominal conditions, that is to say in the absence of failure of this channel 400. A single air intake channel A is therefore here sufficient to cool the low pressure turbine 60 under nominal conditions. However, in other examples not illustrated, the low pressure turbine 60 can be cooled using a plurality of channels 400. The number of channels 400 is then chosen so as to meet the just need for cooling the low pressure turbine 60, that is to say chosen to convey the minimum air flow necessary for cooling the low pressure turbine 60 and ensure uniform cooling over the entire circumference of the parts.
    The first channel 200 is further provided with a valve 600 authorizing the connection of a third channel 700 for cooling air circulation. An air inlet of the third channel 700 is connected to the valve 600 and is in selective communication with the first channel 200 by means of the latter. An end 700a, corresponding to an air outlet of the third channel 700 is connected as an air inlet to the collector 500 for cooling air.
    The valve 600 can be controlled in two configurations from a control device 800. In a first configuration, corresponding to a default configuration of the valve 600, the valve 600 authorizes the circulation of air withdrawn only in the first channel 200. In this first configuration, the circulation of air through the third channel 700 is prohibited by the valve 600. In a second configuration, the valve 600 is controlled by the control device 800 so as to deflect the air circulation from the first channel 200 to the third channel 700, allowing the circulation of air in the latter.
    The control device 800 controls the configuration of the valve 600 as a function of a cooling air pressure determined for the low pressure turbine 60. This cooling air pressure is determined by the control device 800 from measurements from at least one data sensor C1, C2, C3.
    In a first example, illustrated in FIG. 2, the data sensor C1 is a pressure sensor placed in an enclosure 68 of the low pressure turbine 60. This arrangement of the sensor C1 makes it possible to measure the pressure in the enclosure 68, and to detect a possible drop in pressure, which may for example result from a failure of a labyrinth seal 69 ensuring the pressure isolation of enclosure 68, or even from a rupture of a air circulation channel. Thus, if the control device 800 detects a pressure drop in the enclosure 68, the latter can control the passage of the valve 600 from the first configuration to the second configuration. The air A taken from the high pressure compressor 30 and circulating in the first channel 200 is then diverted to the third channel 700 by means of the valve 600. This second configuration thus makes it possible to guarantee a flow of cooling air sufficient for cooling the low-pressure turbine 60, as well as for bleeding hot air from stages 51, 61, 62 of the high-pressure 50 and low-pressure turbines 60. The deflected air flow therefore complements the air cooling channeled by the 20 or the second channels 400 in the event of a rupture of the labyrinth seal 69, or an air flow replacing that of the second channel 400 in the event of the latter breaking.
    In a second example illustrated in FIG. 1, the data sensor C2 is a pressure sensor associated with the collector 500 for cooling air. The sensor C2 makes it possible to measure the pressure in the manifold 500 at any time, and to allow the detection of a possible pressure drop, reflecting a failure of the second channel 400. Thus, if the control device 800 detects a pressure drop in the cooling air collector 500, this can control the passage of the valve 600 from the first configuration to the second configuration. The air taken from the high pressure compressor 30 and circulating in the first channel 200 is deflected by the valve 600 so as to circulate in the third channel 700. This second configuration then allows, via the deflection of the cooling air circulating in the first channel 200, to supply an air flow sufficient to cool the low pressure turbine 60 and ensure the purging of the hot air from the stages 51,
    61, 62 of the high pressure 50 and low pressure 60 turbines despite the failure of the second channel 400.
    In a third example, when the turbomachine 100 has a plurality of second channels 400, the failure of a channel can be identified by the control device 800 on the basis of a pressure difference measured between the different channels 400. Each second channel 400 is then instrumented by a pressure sensor C3. Once again, when the control device 800 detects a pressure drop, corresponding to a failure of one of the channels 400, the device controls the passage of the valve 600 from the first configuration to the second configuration. Thus, the deviation by the valve 600 of the air circulating in the first channel 200 towards the third channel 700 makes it possible to compensate for the loss of the cooling air due to the failure of one of the second channels 400.
    Furthermore, it is understood that the failure (eg rupture) of an air circulation channel can be detected by means other than pressure sensors, for example by detecting currents or vibrations.
    More generally, the cooling of the low pressure turbine 60, as well as the purging of the stages 51, 61, 62 are carried out as follows.
    For nominal operation of the turbomachine 100, for example in the absence of failure of the labyrinth seal 69 or of a cooling air circulation channel 400, the valve 600 is initially in the first configuration. Air A circulating in the turbomachine 100 is sampled on the high pressure compressor 30. The sampled air is then routed both through the first channel 200 to a device for optimizing the performance of the turbomachine, for example to the device 300 for controlling clearance J of the high pressure turbine 50, and towards the low pressure turbine 60 via the second channel or channels 400 with a view to cooling the latter.
    In parallel, the control device 800 determines the cooling air pressure of the low pressure turbine 60, from measurements of one or more data sensors C1, C2, C3, and compares the pressure determined with a threshold. This threshold is, for example, predetermined as a function of a failure condition of a second channel 400 and / or of a failure of an insulation joint of the enclosure 68 of the low pressure turbine 60 .
    When the cooling air pressure of the low pressure turbine 60 is identified by the control device 800 as lower than said threshold, the control device 800 deduces a failure likely to impact the proper cooling of the low pressure turbine 60. The control device 800 then controls the valve 600 to pass from the first configuration to the second configuration. The cooling air from the first channel 200 is then diverted to the third channel 700 so as to distribute this cooling air to the low pressure turbine 60.
    Preferably, the first channel 200 is a channel distributing air to the device 300 for controlling the clearance J of the high pressure turbine 50 when the turbomachine 100 operates in nominal fashion, that is to say in the first configuration of the valve 600 .
    Still preferably, the control device 300 is a device internal to the turbine ring 54 of the high pressure turbine 50.
    These preferred configurations have the advantage of providing maximum cooling air flows flowing in the first channel 200. Thus, when the valve 600 is controlled in the second configuration, the cooling of the low pressure turbine 60 as well as the bleeding of the the hot air of stages 51, 61, 62 of the high pressure 50 and low pressure 60 turbines are maximized. Other configurations can however be envisaged, for example the connection of the first channel 200 to the clearance control device of the low pressure turbine 60, or even the use of a clearance control device external to the high pressure turbine 50.
    Furthermore, as illustrated in FIG. 1, diaphragms 201a, 401a can be arranged at the respective inputs of the first channel 200 and of the second channel (s). Non-return valves 401b, 701b are then arranged at the respective outputs of the one or more second channels 400 and third channel 700. The diaphragms 201a, 401a and non-return valves 401b, 701b have the function of minimizing the effects on the air intake of the high pressure compressor 30 in the event of a failure of one of the channels 200 , 400, 700. The risk of loss of cooling air is thus limited. Thus, in the event of a channel rupture, it is not necessary to detect the damaged channel, the latter being automatically isolated by its respective diaphragm and valve.
    Advantageously, the embodiments described above make it possible to dispense with any oversizing to cool the low pressure turbine 60. While usually cooling the low pressure turbine requires an additional air circulation channel to guarantee good cooling the turbine and being in compliance with aeronautical safety standards, the embodiments described above only require the minimum number of channels required to cool this turbine. In other words, the low pressure turbine 60 is here cooled to the just need by the second channel (s) 400.
    During nominal operation of the turbomachine 100, the air taken from the high pressure compressor 30 can be both routed to the low pressure turbine 60, with a view to cooling it when necessary and, by way of example , towards the device 300 for controlling the clearance of the high pressure turbine 50. The specific fuel consumption of the turbomachine 100 is therefore optimized under nominal operating conditions, these conditions corresponding to the first configuration of the valve 600.
    If a failure occurs in the turbomachine 100, for example a rupture of a second duct 200 or of a labyrinth seal 69, the cooling air initially dedicated, for example, to the device 300 for controlling the clearance of the high pressure turbine 50 is deflected towards the low pressure turbine 60 so as to guarantee good cooling thereof. In this situation, corresponding to the second configuration of the valve 600, the overall performance of the turbomachine 100 is degraded in favor of the cooling of the low pressure turbine 60. However, such a reduction in the performance of the turbomachine 100 remains infrequent, because it is only ordered in the event of a fault detected therein. Conversely, the oversizing of the state-of-the-art cooling circuits imply air samples from the high pressure compressor during the entire nominal operation of the turbomachine. These over-withdrawals then lead to a deterioration in the overall performance of the turbomachine in the absence of failure therein.
    The proposed embodiments thus make it possible to obtain an efficient standby functionality for cooling the low pressure turbine 60 and purging the stages 51, 61, 62 of the high pressure turbines 50 and low pressure 60. This functionality of 5 cooling also perfectly meets aeronautical safety requirements.
    On the basis of these embodiments, it has been evaluated, for all operating phases of the turbomachine 100, that it is possible to obtain a gain in mass flow rate of fuel W25 at the inlet of the high pressure compressor 30 of l '' of 0.25% and a gain of 15% in specific fuel consumption.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Aircraft turbomachine (100) comprising at least:
    - a high pressure compressor (30),
    - a high pressure turbine (50),
    - a low pressure turbine (60),
    - a first cooling air circulation channel (200) connecting the high pressure compressor (30) and the high pressure turbine (50),
    - a second cooling air circulation channel (400) connecting the high pressure compressor (30) and the low pressure turbine (60),
    - The turbomachine (100) being characterized in that the first channel (200) is provided with a valve (600), and in that it further comprises a third channel (700) for circulating cooling air in selective communication with the first channel (200) via the valve (600), the third channel (700) being further in communication with the low pressure turbine (60), the valve (600) having a first configuration in which the circulation of air in the first channel (200) is authorized and the circulation of air in the third channel (700) is prohibited, and a second configuration in which the circulation of air from the first channel (200) is diverted to the third channel (700).
    [2" id="c-fr-0002]
    2. Turbomachine (100) according to claim 1, further comprising a control device (800) configured to determine a cooling air pressure of the low pressure turbine (60) and control as a function of the determined air pressure the valve (600) for passing it from the first configuration to the second configuration.
    [3" id="c-fr-0003]
    3. Turbomachine (100) according to claim 2, in which one end (400a) of the second channel (400) and one end (700a) of the third channel (700) are connected to a collector (500) of cooling air, the cooling air manifold (500) being further connected to a hollow distributor (70) of the low pressure turbine (60).
    [4" id="c-fr-0004]
    4. Turbomachine (100) according to claims 2 or 3, comprising a plurality of second channels (400) for circulating cooling air each bringing the high pressure compressor (30) and the low pressure turbine (60) into communication.
    [5" id="c-fr-0005]
    5. Turbomachine (100) according to claims 3 or 4, in which the control device (800) is configured to determine the pressure of cooling air of the low pressure turbine (60) from at least one measurement d '' a pressure sensor (C2) associated with the cooling air collector (500).
    [6" id="c-fr-0006]
    6. Turbomachine (100) according to claims 3 or 4, in which the control device (800) is configured to determine the value of the cooling air pressure of the low pressure turbine (60) from at least one measurement of a pressure sensor (C1) placed in an enclosure (68) of the low pressure turbine (60).
    [7" id="c-fr-0007]
    7. A turbomachine (100) according to claim 4, in which the control device (800) is configured to determine the cooling air pressure of the low pressure turbine (60) from a difference in pressure measurements from pressure sensors (C3) associated with the plurality of second channels (400).
    [8" id="c-fr-0008]
    8. Turbomachine (100) according to any one of claims 2 to 7, further comprising a device (300) for controlling a clearance (J) between the tips of blades (52) of a rotor of the turbine high pressure (50) and a turbine ring (54) of a casing (66) surrounding the blades (52) of the high pressure turbine (50), one end of the first cooling air circulation channel (200) being in communication with the device (300) for controlling the clearance of the high pressure turbine (50) so as to supply it with air when the valve (600) is in the first configuration.
    [9" id="c-fr-0009]
    9. A turbomachine (100) according to claim 8, in which the device (300) for controlling the clearance of the high pressure turbine (50) is a device internal to the turbine ring (54).
    [10" id="c-fr-0010]
    10. Method for cooling a low pressure turbine (60) in an aircraft turbomachine (100) produced according to any one of claims 1 to 9, this method comprising:
    - a sample of air circulating in the high pressure compressor (30),
    - In an initial situation corresponding to the first configuration of the valve (600), a distribution of the air taken from the high pressure turbine (50) via the first channel (200) and the low pressure turbine (60 ) via the second channel (400),
    the determination of a cooling air pressure of the low pressure turbine (60) and a comparison of the value of the pressure determined at a threshold by the control device (800), and
    - when the cooling air pressure of the low pressure turbine (60) is below the threshold, control by the control device (800) of the valve (600) according to the second configuration, so as to distribute the air cooling the first channel (200) to the low pressure turbine (60).
    [11" id="c-fr-0011]
    11. The cooling method according to claim 10, wherein the threshold is predetermined as a function of a failure condition of the second channel (400).
    类似技术:
    公开号 | 公开日 | 专利标题
    CA2772763C|2017-05-16|Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine
    EP3698022A1|2020-08-26|Device and method for cooling a low pressure turbine in a turbomachine
    EP1916391B1|2018-02-21|Method and device for reducing speed in the event of breakage of the turbine shaft of a gas-turbine engine
    FR2938293A1|2010-05-14|AIR FLOW CONTROL DEVICE SUPPLYING A TURBINE VENTILATION CAVITY OF A TURBOMACHINE TURBINE SECTION
    US9890645B2|2018-02-13|Coolant flow redirection component
    WO2021191523A1|2021-09-30|Turbomachine with device for cooling and pressurising a turbine
    FR3084907A1|2020-02-14|DEVICE AND METHOD FOR COOLING A TURBINE IN A TURBOMACHINE
    FR2999226A1|2014-06-13|Control device for controlling clearance between tips of rotor blades of low pressure turbine in e.g. turbojet, has control unit controlling air flow supply to cooling circuit according to information about worn thickness of abradable layer
    FR3081514A1|2019-11-29|PROPELLANT AIRCRAFT ASSEMBLY AND METHOD FOR REDUCING VENTILATION AIR FLOW IN THE AIRCRAFT PROPELLANT ASSEMBLY
    FR3095231A1|2020-10-23|Improved cooling air injection device for aircraft turbines
    FR3078362A1|2019-08-30|METHOD AND CONTROL UNIT FOR STEERING THE GAME OF A HIGH PRESSURE TURBINE
    EP3237737B1|2019-02-06|Method for detecting a fluid leak in a turbomachine and fluid distribution system
    FR3105980A1|2021-07-09|PROCESS AND CONTROL UNIT FOR CONTROL OF THE SET OF A HIGH PRESSURE TURBINE FOR REDUCTION OF THE EGT OVERRIDE EFFECT
    FR3106624A1|2021-07-30|improved aircraft turbine engine cooling anomaly detection device
    FR3088964A1|2020-05-29|Control of a compressor air sampling valve
    CA3137701A1|2020-11-19|Turbomachine comprising a system for deicing the upstream cone, and associated method
    FR3092134A1|2020-07-31|turbine with improved balancing device
    FR3108362A1|2021-09-24|Variable orientation blade stage for an axial turbomachine comprising a member for regulating the air flow depending on the orientation of the blades
    FR3074849A1|2019-06-14|AIRCRAFT TURBOMACHINE HAVING AT LEAST TWO BODIES COMPRISING COMPRESSED GAS DERIVATION MEANS
    FR3097898A1|2021-01-01|DISCHARGE OF A VEIN FROM A PROPELLENT ASSEMBLY TO REDUCE THE BLOWER BEAT OF A BLOWER
    WO2021013957A1|2021-01-28|Axial turbine engine, and rectifier stage with variable orientation vanes for an axial turbine engine
    FR3075877A1|2019-06-28|SYSTEM FOR DETECTING A TEMPERATURE FAULT IN THE INTER-VEIN COMPARTMENT OF A DOUBLE FLOW TURBOREACTOR
    FR2953556A1|2011-06-10|High pressure turbine for turbomachine i.e. turbojet engine, of airplane, has variable obturator forming element installed in cavity and cooperating with internal openings of holes to form variable obturator of holes based on temperature
    FR3050760A1|2017-11-03|DISCHARGE VALVE SYSTEM FOR AN AIRCRAFT TURBOMACHINE
    FR3025835A1|2016-03-18|TURBOMACHINE TURBINE AUB COOLING AIR CIRCULATION SYSTEM
    同族专利:
    公开号 | 公开日
    WO2019077251A1|2019-04-25|
    US10914188B2|2021-02-09|
    FR3072414B1|2019-11-01|
    EP3698022A1|2020-08-26|
    CN111212959A|2020-05-29|
    US20200308977A1|2020-10-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0637683A1|1993-08-05|1995-02-08|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Cooling system for the turbine stator and rotor disks of a turbomachine|
    US20090104020A1|2007-10-22|2009-04-23|General Electric Company|System for delivering air from a multi-stage compressor to a turbine portion of a gas turbine engine|
    EP2305982A1|2009-09-25|2011-04-06|Nuovo Pignone S.p.A.|Cooling and tapping system for a gas turbine engine and corresponding operation method|WO2021191523A1|2020-03-24|2021-09-30|Safran Aircraft Engines|Turbomachine with device for cooling and pressurising a turbine|US5305616A|1992-03-23|1994-04-26|General Electric Company|Gas turbine engine cooling system|
    US6550253B2|2001-09-12|2003-04-22|General Electric Company|Apparatus and methods for controlling flow in turbomachinery|
    US7007488B2|2004-07-06|2006-03-07|General Electric Company|Modulated flow turbine nozzle|
    GB201200290D0|2012-01-10|2012-02-22|Rolls Royce Plc|Gas turbine engine buffer seals|
    US20130192251A1|2012-01-31|2013-08-01|Peter M. Munsell|Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine|
    US9482236B2|2013-03-13|2016-11-01|Rolls-Royce Corporation|Modulated cooling flow scheduling for both SFC improvement and stall margin increase|
    US9797259B2|2014-03-07|2017-10-24|Siemens Energy, Inc.|Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids|
    US9810158B2|2014-04-01|2017-11-07|The Boeing Company|Bleed air systems for use with aircraft and related methods|
    US10794290B2|2016-11-08|2020-10-06|Raytheon Technologies Corporation|Intercooled cooled cooling integrated air cycle machine|FR3095831A1|2019-05-10|2020-11-13|Safran Aircraft Engines|improved turbomachine module ventilation device|
    US11215074B2|2019-07-08|2022-01-04|General Electric Company|Oxidation activated cooling flow|
    法律状态:
    2018-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-04-19| PLSC| Search report ready|Effective date: 20190419 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 4 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1759692A|FR3072414B1|2017-10-16|2017-10-16|DEVICE AND METHOD FOR COOLING A LOW PRESSURE TURBINE IN A TURBOMACHINE|
    FR1759692|2017-10-16|FR1759692A| FR3072414B1|2017-10-16|2017-10-16|DEVICE AND METHOD FOR COOLING A LOW PRESSURE TURBINE IN A TURBOMACHINE|
    EP18796734.4A| EP3698022A1|2017-10-16|2018-10-15|Device and method for cooling a low pressure turbine in a turbomachine|
    US16/756,021| US10914188B2|2017-10-16|2018-10-15|Device and method for cooling a low pressure turbine in a turbomachine|
    CN201880066865.4A| CN111212959A|2017-10-16|2018-10-15|Device and method for cooling a low-pressure turbine in a turbomachine|
    PCT/FR2018/052559| WO2019077251A1|2017-10-16|2018-10-15|Device and method for cooling a low pressure turbine in a turbomachine|
    [返回顶部]