• 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:

    公开号:FR3017655A1
    申请号:FR1451234
    申请日:2014-02-17
    公开日:2015-08-21
    发明作者:Olivier Pelagatti；Thomas Deguin；Ronan Bodet
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aircraft turbojet engine comprising an air sampling system of said turbojet engine, an aircraft comprising at least one such turbojet engine, and a method for controlling such a turbojet engine. Fig. 1 shows an aircraft turbofan engine 10 equipped with a sampling system 100 of the state of the art which is intended to draw air into the turbojet engine 10 and to deliver it to an air system 60 , for example, the air conditioning system 60 of the cabin of the aircraft. The turbojet engine 10 comprises: a fan 12 intended to generate an air flow in the turbojet engine 10 in a direction of displacement 50 of the air in the turbojet engine, where in a known manner, the air flow then moves downstream the blower in a primary vein of the turbojet engine 10 or in a secondary vein thereof, - a compressor 14 which comprises a low-pressure compressor 16 downstream of the fan 12 and a high-pressure compressor 18 disposed downstream of the low pressure compressor 16, a turbine 20 which comprises a high-pressure turbine 22 downstream of the high-pressure compressor 18, and a low-pressure turbine 24 downstream of the high-pressure turbine 22. The air pushed by the fan and passing through the primary vein passes successively through the low pressure compressor 16, the high pressure compressor 18, the high pressure turbine 22, and the low pressure turbine 24 to be ejected to the outside. Between the high-pressure compressor 18 and the high-pressure turbine 22, the air passes through a combustion chamber 26.
    [0002] The high-pressure compressor 18 comprises several compression stages where the pressure increases, from upstream to downstream in the direction of displacement 50, from a low pressure at the level of the first stage to a high pressure at the level of the last stage. passing through an intermediate pressure in the vicinity of the middle stage.
    [0003] The sampling system 100 comprises: - a first air intake 102 intended to take, in the high-pressure compressor 18, air at the intermediate pressure, - a second air intake 104 intended to take, in the compressor high pressure 18, air at high pressure, - a non-return valve 106 fluidly connected to the first air intake 102 and which prevents air from moving towards said first air intake 102, - a valve high pressure 108 fluidly connected to the second air intake 104 and alternately controlled opening or closing, - a control valve 110 for regulating the pressure of the air flow therethrough, the outlet of the high pressure valve 108 and the outlet of the non-return valve 106 being fluidly connected to the same inlet of the regulating valve 110, a cooler 112 intended to cool the air passing through it, the outlet of the regulating valve 110 being fluidly connected. t to an inlet of the cooler 112 and an outlet of the cooler 112 being fluidly connected to the air system 60 of the aircraft, - a controller 114 for controlling the high pressure valve 108 and the regulating valve 110. The necessary air the cooling carried out in the cooler 112 is taken through a pipe 116 arranged downstream of the fan 12 in the secondary air stream of the turbojet engine 10. The air pressure at the outlet of the cooler 112 must be compatible with the pressure of air to be injected into the air system 60. Typically, in the case of a pressurized booth, the air pressure must be between 137895.14 Pa (20 psia) and 206842.72 Pa (30 psig). psia).
    [0004] Thus, when the pressure at the first air intake 102 is greater than a first threshold, typically 275790.29 Pa (40 psia), the air necessary for operation of the sampling system 100 is taken at the first level. air intake 102, and when the pressure in the sampling system 100 is less than a second threshold, typically 206842.72 Pa (30 psia), the air necessary for the operation of the sampling system 100 is taken at the level of second air intake 104. For this purpose, a pressure sensor senses the value of the pressure at the first air intake 102 and another pressure sensor 111 captures the value of the pressure in the sampling system 100 Such a pressure sensor 111 is for example installed downstream of the junction between the outlet of the non-return valve 106 and the outlet of the high pressure valve 108. The operation of the sampling system 100 is then as follows: the pressure at the first air intake 102 is greater than a first threshold, the controller 114 controls the closing of the high pressure valve 108, - the air is then taken at the first intake 102, through the non-return valve 106 and feeds the regulation valve 110, - when the pressure in the sampling system 100 is lower than the second threshold, the controller 114 controls the opening of the high pressure valve 108, - the air is then taken at the level of the second air intake 104, passes through the high pressure valve fo 108 and supplies the regulation valve 110 and the non-return valve 106 prevents the return of air into the turbojet engine 10, the control controller 114 the regulation valve 110 according to the air pressure to be obtained, the air at the outlet of the regulation valve 110 passes through the cooler 112 and then supplies the air system 60. Such an implantation does not always give satisfaction in terms of of consumption energy. An object of the present invention is to provide a turbojet having a sampling system and which does not have the drawbacks of the prior art and which in particular allows a reduction in consumption. For this purpose, is proposed a turbojet engine comprising a low pressure compressor, a high pressure compressor with several compression stages where the pressure increases, from upstream to downstream in a direction of movement of the air, a low pressure at a high pressure, and a sampling system for withdrawing air from the turbojet engine and delivering it to an air system, the sampling system having a second air intake for sampling, in the high pressure air compressor, high pressure air, said sampling system further comprising - a first air intake for drawing air at low pressure, - a first valve whose inlet is fluidly connected to the first air intake, - a second valve whose input is fluidly connected to the first air intake, - a compressor whose input is fluidly connected to the outlet of the second valve, - a valve a return valve whose inlet is fluidly connected to the outlet of the first valve and at the outlet of the compressor, and which prevents air from moving towards the compressor and the first valve, - a high pressure valve fluidly connected to the second air intake, - a cooler for cooling the air flowing through it, the outlet of the high pressure valve being fluidly connected to an inlet of the cooler, - a control valve for regulating the pressure of the air flow which passes therethrough, the outlet of the cooler and the outlet of the nonreturn valve being fluidly connected to the same inlet of the regulating valve, and an outlet of the regulating valve being fluidly connected to the air system, - a controller for controlling, in opening and closing, the high pressure valve, the first valve, the second valve and the regulating valve, and - a pressure sensor for sensing the pressure value at the level of the first air intake and to transmit information relating to this pressure to the controller. This particular arrangement reduces fuel consumption. The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in connection with the attached drawings, among which: FIG. . 1 shows an aircraft turbofan engine equipped with a sampling system according to the state of the art, FIG. 2 shows an aircraft turbofan engine equipped with a sampling system according to a first embodiment of the invention, FIG. 3 shows an aircraft turbofan engine equipped with a sampling system according to a second embodiment of the invention, and FIG. 4 shows an aircraft comprising a turbofan engine according to the invention. Fig. 4 shows an aircraft 400 equipped with a turbofan engine 10. Fig. 2 and FIG. 3 show the turbojet engine 10 equipped with a sampling system 200, 300 according to the invention which is intended to take air from the turbojet engine 10 and to deliver it to an air system 60, such as, for example, the system air conditioning 60 of the cabin of the aircraft. The turbojet engine 10 comprises the same elements as that of FIG. 1, in particular a low-pressure compressor 16 and a high-pressure compressor 18. These elements have the same references. The high-pressure compressor 18 comprises several compression stages where the pressure increases, from upstream to downstream in a direction of displacement of the air 50 in the turbojet engine, from a low pressure at the level of the first stage, to a high pressure at the top floor.
    [0005] The sampling system 200 of FIG. 2 comprises: - a first air intake 202 for withdrawing air at low pressure, - a second air intake 204 for taking, in the high pressure compressor 18, air at high pressure, - a first valve 215 whose inlet is fluidly connected to the first air intake 202, and alternately controlled in opening or closing, - a second valve 216 whose inlet is fluidly connected to the first air intake 202, and alternately controlled in opening or closing, - a compressor 218 whose inlet is fluidly connected to the outlet of the second valve 216, - a non-return valve 206 whose inlet is fluidly connected to the outlet of the first valve 215 and at the outlet of the compressor 218, and which prevents the air from moving towards the compressor 218 and the first valve 215, - a high pressure valve 208 fluidly connected to the second air intake 204 and alternately controlled in opening o u closing, - a cooler 212 for cooling the air passing therethrough, the outlet of the high pressure valve 208 being fluidly connected to an inlet of the cooler 212, - a regulation valve 210 intended to regulate the pressure of the flow of the air passing therethrough, the outlet of the cooler 212 and the outlet of the non-return valve 206 being fluidly connected to the same inlet of the regulating valve 210, and an outlet of the regulating valve 210 being fluidly connected to the control system 210. air 60 of the aircraft, and a controller 214 for controlling, in opening and closing, the high-pressure valve 208, the first valve 215, the second valve 216 and the regulation valve 210 as a function of the pressure at the level of the first air intake 202.
    [0006] The first air intake 202 is arranged to take low-pressure air at the low pressure stages of the high-pressure compressor 18 or at the low-pressure compressor 16. The air required for cooling in the cooler 212 is taken here through a pipe 116 arranged downstream of the fan 12 in the secondary air stream of the turbojet engine 10. The air pressure at the outlet of the regulation valve 210 must be compatible with the air pressure which must be injected into the air system 60. Typically, in the case of a pressurized booth, the air pressure must be between 137895.14 Pa (20 psia) and 206842.72 Pa (30 psia). The controller 214 then controls the opening of the regulation valve 210 according to the pressure to be delivered. Typically, in a turbojet engine 10 in the take-off mode, the air pressure at the first intake air 202, that is to say the low pressure, is of the order of 206842.72 Pa ( 30 psia), and at idle, the air pressure at the second air intake 204, i.e. the high pressure, is in the range of 137895.14 Pa (20 psia) . Thus, when the pressure at the first air intake 202 is greater than a first threshold, typically of the order of 137895.14 Pa (20 psia), the air necessary for the operation of the sampling system 200 is taken from the level of the first air intake 202, when the pressure at the first air intake 202 is lower than the first threshold and greater than a second threshold, typically of the order of 103421.36 Pa (15 psia), the air necessary for the operation of the sampling system 200 is taken at the first intake 202 and compressed by the compressor 218, and when the pressure at the first intake 202 is lower than the second threshold, the air necessary for the operation of the sampling system 200 is taken from the second intake 204. For this purpose, a pressure sensor 203 senses the value of the pressure at the first intake 202 and transmit the relative information this pressure to the controller 214 so that the latter controls the opening and closing of appropriate valves 30. Thus, when the pressure at the first air intake 202 is greater than the first threshold, the controller 214 controls the opening of the first valve 215, the closing of the second valve 216, and the closure of the high pressure valve. 208.
    [0007] The air from the first air intake 202 then passes successively through the first valve 215, the non-return valve 206, the control valve 210 and is conducted to the air system 60. Thus, when the pressure at of the first air intake 202 is lower than the first threshold and greater than the second threshold, the controller 214 controls the closing of the first valve 215, the opening of the second valve 216, and the closing of the high pressure valve 208. The air coming from the first air intake 202 then passes successively through the second valve 216, the compressor 218, the non-return valve 206, the regulation valve 210 and is led to the air system 60. the pressure at the first air intake 202 is lower than the second threshold, the controller 214 controls the closing of the first valve 215, the closing of the second valve 216, and the opening of the high pressure valve 208. L air from the second intake The airway 204 then passes successively through the high pressure valve 208, the cooler 212, the control valve 210 and is conducted to the air system 60. The non-return valve 206 then prevents the air from the cooler 212 from return to the first air intake 202. A control method of the turbojet engine 10 comprises: - a first control step during which the controller 214 controls the opening of the first valve 215, the closure of the second valve 216 and closing the high pressure valve 208, when the pressure at the first air intake 202 is greater than the first threshold, - a second control step in which the controller 214 controls the closing of the first valve 215, the opening of the second valve 216, and the closing of the high-pressure valve 208, when the pressure at the first air intake 202 is lower than the first threshold and greater than the second threshold, and a third control step in which the controller 214 controls the closing of the first valve 215, the closing of the second valve 216, and the opening of the high pressure valve 208, when the pressure at the first intake of air 202 is less than the second threshold. These three steps are alternative and the controller 214 performs one or the other after comparing the value of the pressure measured by the pressure sensor 203 with respect to the first threshold and the second threshold.
    [0008] Moving the air intake from the intermediate pressure to the low pressure saves fuel during take-off, climb and cruise flight. According to the architecture of the turbojet engine 10, the economy can range from 0.7% to 1.7%.
    [0009] In the embodiment of the invention of FIG. 2, the compressor 218 is driven by an electrical power source of the aircraft. Fig. 3 shows a sampling system 300, in which the compressor 218 is driven by means of an air sample taken within said sampling system 300.
    [0010] The sampling system 300 then also comprises: a compression valve 302 whose inlet is fluidly connected to the outlet of the second valve 216, and a turbine 304 whose inlet is fluidly connected to the outlet of the valve compression 302 and which is intended to drive the compressor 218.
    [0011] The controller 214 is then also provided to control the compression valve 302 in opening and closing. The operation of the sampling system 300 is then identical to that of the first embodiment when the pressure at the first intake 202 is greater than the first threshold and when the pressure at the first intake 202 is less than the second threshold. The controller 214 then controls the closing of the compression valve 302. On the other hand, when the pressure at the first air intake 202 is lower than the first threshold and greater than the second threshold, the controller 214 controls the closure of the first threshold. valve 215, the opening of the second valve 216, the closing of the high pressure valve 208 and the opening of the compression valve 302. During the second control step, the controller 214 also controls the opening of the compression valve 302. The air coming from the first air intake 202 then passes successively through the second valve 216, the compressor 218, the non-return valve 206, the regulation valve 210 and is led to the system air 60, while a portion of the air is taken at the outlet of the second valve 216 to pass through the compression valve 302 and thus supply the turbine 304.
    [0012] The controller 214 regulates the opening of the compression valve 302 to distribute the air between the compressor 218 and the turbine 304. According to a particular embodiment, 66% of the air coming from the second valve 216 passes through the compressor 218 and 33% pass through the 304.5 turbine
    权利要求:
    Claims (9)
    [0001]
    CLAIMS1) Turbojet engine (10) comprising a low-pressure compressor (16), a high-pressure compressor (18) with several compression stages where the pressure increases, from upstream to downstream in a direction of movement of the air ( 50), from a low pressure to a high pressure, and a sampling system (200, 300) for taking air from the turbojet engine (10) and delivering it to an air system (60), the sampling system (200, 300) comprising a second air intake (204) for taking high pressure air from the high-pressure compressor (18), characterized in that said sampling system (200) , 300) further comprises - a first air intake (202) for drawing air at low pressure, - a first valve (215) whose inlet is fluidly connected to the first air intake (202). a second valve (216) whose inlet is fluidly connected to the first air intake (202), - a compressor (218) whose input is fluidly connected to the output of the second valve (216), - a non-return valve (206) whose input is fluidly connected to the outlet of the first valve (215) and at the outlet of the compressor (218), which prevents air from being directed to the compressor (218) and the first valve (215), - a high pressure valve (208) fluidly connected to the second air intake (204), - a cooler (212) for cooling the air passing therethrough, the outlet of the high pressure valve (208) being fluidly connected to an inlet of the cooler (212), - a control valve (210) for regulating the pressure of the air flow therethrough, the outlet of the cooler (212) and the outlet of the nonreturn valve (206) being fluidly connected to the same inlet of the regulating valve (210), and an outlet of the regulating valve (210) being fluidly connected to the air system (60), - a controller (214) for controlling, in opening and closing, the high pressure valve (208), the first valve (215), the second valve (216) and the regulating valve (210), and- a pressure sensor (203) for sensing the pressure value at the first air intake (202) and transmitting information relating to that pressure to the controller (214).
    [0002]
    2) turbojet engine (10) according to claim 1, characterized in that the first air intake (202) is arranged to take low pressure air at the low pressure stages of the high pressure compressor (18).
    [0003]
    3) turbojet engine (10) according to claim 1, characterized in that the first air intake (202) is arranged to take low pressure air at the low pressure compressor (16).
    [0004]
    4) turbojet engine (10) according to one of claims 1 to 3, characterized in that the sampling system further comprises: - a compression valve (302) whose input is fluidly connected to the outlet of the second valve (216), and which is controlled in opening and closing by the controller (214), and - a turbine (304) whose input is fluidly connected to the output of the compression valve (302) and which is intended for driving the compressor (218), - the controller (214) being provided to further control the opening or closing of the compression valve (302).
    [0005]
    5) Aircraft (400) comprising at least one turbojet engine (10) according to one of the preceding claims.
    [0006]
    6) A method of controlling a turbojet engine (10) according to one of claims 1 to 4, the control method comprising: - a first control step in which the controller (214) controls the opening of the first valve (215), closing the second valve (216), and closing the high pressure valve (208), when the pressure at the first air intake (202) is greater than a first threshold, - a second control step in which the controller (214) controls the closing of the first valve (215), the opening of the second valve (216), and the closing of the high pressure valve (208), when the pressure at the first air intake (202) is less than the first threshold and greater than a second threshold, and - a third control step in which the controller (214) controls the closing of the first valve (215) , closing the second valve (216), and opening the valve high pressure (208), when the pressure at the first air intake (202) is lower than the second threshold.
    [0007]
    7) A control method according to claim 6, characterized in that when the turbojet engine (10) comprises a compression valve (302) and a turbine (304), the controller (214) controls the opening of the compression valve ( 302) during the second control step.
    [0008]
    8) A control method according to one of claims 6 or 7, characterized in that the first threshold is of the order of 137895.14 Pa (20 psia).
    [0009]
    9) A control method according to one of claims 6 to 8, characterized in that the second threshold is of the order of 103421.36 Pa (15 psia). 15
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    引用文献:
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    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-23| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1451234|2014-02-17|
    FR1451234A|FR3017655B1|2014-02-17|2014-02-17|TURBOREACTOR COMPRISING A SAMPLING SYSTEM FOR TAKING AIR INTO THE TURBOREACTOR|FR1451234A| FR3017655B1|2014-02-17|2014-02-17|TURBOREACTOR COMPRISING A SAMPLING SYSTEM FOR TAKING AIR INTO THE TURBOREACTOR|
    US14/623,152| US10012146B2|2014-02-17|2015-02-16|Turbojet comprising a bleeding system for bleeding air in said turbojet|
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