• 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:FR3017656A1
    申请号:FR1451235
    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 108 and supplies the regulation valve 110 and the non-return valve 106 prevents the return of air into the turbojet engine 10, the controller 114 controls 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 consumption d 'energy. An object of the present invention is to provide a turbojet comprising a sampling system and which does not have the disadvantages of the prior art and which in particular allows a reduction in consumption. For this purpose, is proposed a turbojet comprising a high pressure compressor with several compression stages where the pressure increases, from upstream to downstream in a direction of movement of the air, from a low pressure to a high pressure passing through a succession of intermediate pressures, and a sampling system for withdrawing air from said turbojet engine and delivering it to an air system, characterized in that the sampling system comprises: - a first intake of air for drawing air in the high-pressure compressor at low pressure; - a second air intake for taking air in the high-pressure compressor at an intermediate pressure; -Return whose input is fluidly connected to the first air intake and which prevents air from moving towards the first air intake, - a first valve whose input is fluidly connected to the outlet of the v non-return valve, - a second valve whose inlet is fluidly connected to the outlet of the non-return valve, - a compressor whose inlet is fluidly connected to the outlet of the second valve, - a connected high-pressure valve fluidly to the second air intake, - a cooler for cooling the air passing therethrough, the outlet of the high pressure valve being fluidly connected to an inlet of the cooler, and the outlet of the cooler being fluidly connected to the inlets of the first valve and the second valve, fo - a regulating valve for regulating the pressure of the air flow therethrough, the outlet of the first valve and the outlet of the compressor being fluidly connected to the same inlet of the valve of control, and an outlet of the control valve being fluidly connected to the air system, - a low 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, - an intermediate pressure sensor for sensing the value of the pressure at the level of the second intake, and to transmit information relating to this pressure to the controller, and 20 - a controller for controlling, in opening and closing, the high pressure valve, the first valve, the second valve and the regulation valve, depending on the pressure at the first intake and pressure at the second air intake. This particular arrangement makes it possible to reduce the fuel consumption, moreover, this arrangement makes it possible to reduce the thermal stresses that are exerted on the cooler because the air passing through it is no longer high pressure air, but intermediate pressure air. 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 accompanying 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.
    [0005] 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 last stage passing through a succession of intermediate pressures at each of the intermediate stages.
    [0006] The sampling system 200 of FIG. 2 comprises: - a first air intake 202 for taking, in the high-pressure compressor 18, air at low pressure, - a second air intake 204 for taking, in the high-pressure compressor 18, the air at an intermediate pressure; a non-return valve 206 whose inlet is fluidly connected to the first air intake 202 and which prevents the air from being directed towards the first air intake 202; first valve 215 whose inlet is fluidly connected to the outlet of the non-return valve 206, and alternately controlled in opening or closing, a second valve 216 whose inlet is fluidly connected to the outlet of the anti-return valve; -return 206, and alternately controlled opening or closing, - a compressor 218 whose input is fluidly connected to the outlet of the second valve 216, - a high pressure valve 208 fluidly connected to the second intake 204 and ordered alternately opening or 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, and the outlet of the cooler 212 being fluidly connected to the inlets of the the first valve 215 and the second valve 216, - a regulation valve 210 intended to regulate the pressure of the air flow therethrough, the outlet of the first valve 215 and the outlet of the compressor 218 being fluidly connected to the same inlet of the regulating valve 210, and an output of the regulating valve 210 being fluidly connected to the air system 60 of the aircraft, and a controller 214 for controlling the high pressure valve 208 in opening and closing mode, the first valve 215, the second valve 216 and the regulation valve 210 as a function of the pressure at the first air intake 202 and the pressure at the second intake of air. 204. The second air intake 204 is located on a stage located upstream with respect to the last stage of the high-pressure compressor 18. The air necessary for the cooling carried out in the cooler 212 is taken here through a pipe 116 arranged downstream of the blower 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 that 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 intermediate pressure, oscillates around 103421.36 Pa (15psia). 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, when the pressure at the first intake 202 is lower than the second threshold and that the pressure at the second air intake 204 is greater than the first threshold, the air necessary for the operation of the sampling system 200 is taken at the second air intake 204, and when the pressure at the level of the second take of a ir 204 is less than the first threshold and greater than the second threshold, the air necessary for the operation of the sampling system 200 is taken at the second intake 204 and compressed by the compressor 218.
    [0007] More particularly, the outlet pressure of the sampling system 200 must be equal to or greater than 137895.14 Pa (20 psia) and according to the pressure values at the first air intake 202 and at the second intake. In air 204, air from either air intake 202, 204 will be withdrawn with or without compression to at least 137895.14 Pa (20 psia).
    [0008] The position of the second air intake 204 is chosen so that the air pressure at the outlet of the compressor 218 can always be greater than the first threshold. A low pressure sensor 203 senses the pressure value at the first air intake 202 and an intermediate pressure sensor 205 senses the pressure value at the second air intake 204, and each of the sensors 203 and 205 transmits the information relating to the pressure it measures to the controller 214 so that it controls the openings and closures of the appropriate valves. 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. A control method of the turbojet engine 10 thus comprises: a first control step during which the controller 214 controls the opening of the first valve 215, the closing of the second valve 216, and the closing of the high valve; pressure 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 closure of the high pressure valve 208, when the pressure at the first air intake 202 is lower than the first threshold and greater than a second threshold, - a third step of control in which the controller 214 controls the opening 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 202 is below the second threshold and the pressure at the second air intake 204 is greater than the first threshold, and a fourth control step in which the controller 214 controls the closing of the first valve 215, the opening of the second valve 216, and the opening of the high pressure valve 208, when the pressure at the second intake 204 is lower than the first threshold and greater than the second threshold. These four steps are alternative and the controller 214 performs one or the other after comparing the value of the pressure measured by the low pressure sensor 203 and the value of the pressure measured by the intermediate pressure sensor 205 with respect to first threshold and second threshold. The air coming from the first air intake 202 then passes successively through the non-return valve 206, the first valve 215, the regulation valve 210 and is led to the air system 60.
    [0009] Thus, 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 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 non-return valve 206, the second valve 216, the compressor 218, the regulation valve 210 and is led to the control system. Thus, when the pressure at the first air intake 202 is lower than the second threshold and the pressure at the second air intake 204 is greater than the first threshold, the controller 214 controls the closure. the second valve 216, the opening of the first valve 215, and the opening of the high pressure valve 208. The air from the second air intake 204 then passes successively through the high pressure valve 208, the cooler 212 , the first the check valve 210 and it is led to the air system 60. The non-return valve 206 then prevents the air from the cooler 212 to return to the first air intake 202. Thus, when the pressure at the second air intake 204 is less 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 opening of the valve 208. The air coming from the second air intake 204 then passes successively through the high pressure valve 208, the cooler 212, the second valve 216, the compressor 218, the regulation valve 210 and is led to the control system. The anti-return valve 206 then prevents the air from the cooler 212 from returning to the first air intake 202. The displacement of the second air intake from the high pressure to the intermediate pressure makes it possible to save fuel when e the descent and slow motion. Thus, for each displacement upstream of the second air intake 204 of a compression stage, the economy can be up to 0.3%. 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. 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 compression valve 302 and which is intended to drive the compressor 218. 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 lower than the second threshold and that the pressure at the second intake 204 is greater than the first threshold. The controller 214 then controls the closing of the compression valve 302.
    [0010] 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 or when the pressure at the second air intake 204 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, the opening of the compression valve 302, and, as the case may be, the closing or opening of the high-pressure valve 208. In in either case, the air from the first air intake 202 or the second air intake 204 passes through the second valve 216 and the compressor 218 as described above, while part of the air is taken at the outlet of the second valve 216 to pass through the compression valve 302 and thus feed the turbine 304. During the second control step and during the fourth control step, the controller 214 also controls the opening of the valv 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 pass through the compressor 218 and 33% pass through the turbine 304.
    权利要求:
    Claims (7)
    [0001]
    CLAIMS1) Turbojet engine (10) comprising 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), a low pressure at a high pressure passing through a succession of intermediate pressures, and a sampling system (200, 300) for withdrawing air from said turbojet engine (10) and delivering it to an air system (60), characterized in that the sampling system (200, 300) comprises: - a first air intake (202) for taking, in the high-pressure compressor (18), air at low pressure, - a second intake air plenum (204) for withdrawing air at an intermediate pressure from the high-pressure compressor (18); a non-return valve (206) whose inlet is fluidly connected to the first outlet; air (202) and which prevents air from reaching the first air intake (202), first valve (215) whose inlet is fluidly connected to the outlet of the non-return valve (206), - a second valve (216) whose inlet is fluidly connected to the outlet of the non-return valve (206) a compressor (218) whose inlet is fluidly connected to the outlet of the second valve (216), 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), and the outlet of the cooler (212) being fluidly connected to the inlets of the first valve (215) and the second valve (216), - a regulation valve (210) for regulating the pressure of the air flow therethrough, the outlet of the first valve (215) and the outlet of the compressor (218) being fluidly connected to one and the same inlet of the regulating valve (210), and e of the regulating valve (210) being fluidly connected to the air system (60), - a low pressure sensor (203) for sensing the pressure value at the first air intake (202) and transmitting information relating to this pressure to the controller (214), - an intermediate pressure sensor (205) for sensing the pressure value at the second air intake (204), and transmitting information relating to this pressure to the controller (214), 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 control valve (210), depending on the pressure at the first air intake (202) and the pressure at the second air intake (204).
    [0002]
    2) Turbojet engine according to claim 1, characterized in that it 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 to drive the compressor (218), - the controller (214) being provided to further control the opening or closing of the compression valve (302).
    [0003]
    3) Aircraft (400) comprising at least one turbojet engine (10) according to one of the preceding claims.
    [0004]
    4) A method of controlling a turbojet engine (10) according to one of claims 1 or 2, 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, - a third control step in which the controller (214) controls the opening of the first valve (215), closing the second valve (216), and opening the valve a high pressure alve (208), when the pressure at the first air intake (202) is less than the second threshold and the pressure at the second air intake (204) is greater than the first threshold, and a fourth control step during which the controller (214) controls the closing of the first valve (215), the opening of the second valve (216), and the opening of the high pressure valve (208), when the pressure at the second intake (204) is less than the first threshold and greater than the second threshold.
    [0005]
    5) A control method according to claim 4, 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 and during the fourth control step.
    [0006]
    6) A control method according to one of claims 4 or 5, characterized in that the first threshold is of the order of 137895.14 Pa (20 psia).
    [0007]
    7) A control method according to one of claims 4 to 6, characterized in that the second threshold is of the order of 103421.36 Pa (15 psia).
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    法律状态:
    2015-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    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
    FR1451235A|FR3017656B1|2014-02-17|2014-02-17|TURBOREACTOR COMPRISING A SAMPLING SYSTEM FOR TAKING AIR INTO THE TURBOREACTOR|FR1451235A| FR3017656B1|2014-02-17|2014-02-17|TURBOREACTOR COMPRISING A SAMPLING SYSTEM FOR TAKING AIR INTO THE TURBOREACTOR|
    US14/623,037| US9885284B2|2014-02-17|2015-02-16|Turbojet comprising a bleeding system for bleeding air in said turbojet|
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