• 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 cooling system (2) for a circuit (100) of a first fluid of a turbomachine, the cooling system comprising a refrigerant circuit (4) comprising a first heat exchanger (6). for exchanging heat between the refrigerant and the air, a second heat exchanger (8) for exchanging heat between the refrigerant and the first fluid, an expander (10) mounted downstream of the first exchanger, and upstream of the second exchanger, in the direction of circulation of the refrigerant and a compressor (12) mounted downstream of the second exchanger and upstream of the first exchanger; the cooling system further comprises a third exchanger (14) of the first fluid / air type.
    公开号:FR3056641A1
    申请号:FR1658961
    申请日:2016-09-23
    公开日:2018-03-30
    发明作者:Samer MAALOUF；Nawal Jaljal；Pierre Dumoulin；Nicolas Tauveron
    申请人:Commissariat a lEnergie Atomique CEA；Safran SA；Commissariat a lEnergie Atomique et aux Energies Alternatives CEA；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN Public limited company, ATOMIC AND ALTERNATIVE ENERGY COMMISSIONER Public establishment.
    Extension request (s)
    Agent (s): CABINET BEAU DE LOMENIE.
    (54) SYSTEM FOR COOLING A CIRCUIT OF A FIRST FLUID OF A TURBOMACHINE.
    FR 3,056,641 - A1 (57) The invention relates to a cooling system (2) of a circuit (100) of a first fluid of a turbomachine, the cooling system comprising a refrigerant circuit (4) comprising a first heat exchanger (6) for exchanging heat between the refrigerant and air, a second heat exchanger (8) for exchanging heat between the refrigerant and the first fluid, a pressure reducer (10 ) mounted downstream of the first exchanger and upstream of the second exchanger, in the direction of circulation of the refrigerant and a compressor (12) mounted downstream of the second exchanger and upstream of the first exchanger; the cooling system further comprises a third exchanger (14), of the first fluid / air type.
    FIELD OF THE INVENTION The present invention relates to the general field of the dissipation of thermal powers generated in a turbomachine. It relates in particular to the cooling of a fluid contained in a circuit, such as an oil circuit, of an aircraft turbomachine.
    STATE OF THE PRIOR ART [0002] In known manner, a turbomachine comprises an oil circuit for the lubrication and / or cooling of equipment, such as in particular rolling bearings or gear members.
    The cooling of the oil circulating in the engine oil circuit is typically provided by air-oil type heat exchangers (called in English ACOC for "Air Cooled Oil Cooler").
    These heat exchangers operate thanks to an air flow which is usually taken from the flow stream of the secondary flow of the turbomachine and which is guided along an exchange surface with the oil circuit . These heat exchangers can be of the "surface" type, where they are in the form of a metal surface piece allowing the passage of oil through channels machined in its center. The extraction of calories is then carried out using fins in contact with the sampled air flow. To ensure significant heat exchange, such an exchanger must have a large surface area, and therefore also a large mass and bulk. Air-oil type heat exchangers can alternatively be of the “brick” type. However, these heat exchangers are relatively heavy and have the disadvantage of disturbing the air flow. This disturbance has the effect of increasing the aerodynamic drag formed by the turbomachine and, consequently, of increasing the energy consumption of the turbomachine; it therefore penalizes the overall efficiency of the turbomachine (with an increase in specific SFC fuel consumption for “Specifies Fuel Consumption”).
    Whatever the technology used for the air-oil heat exchangers, the latter therefore induce pressure losses on the flow stream of the secondary flow from which the air is taken, and therefore a drop in the efficiency of the turbomachine with an increase in specific SFC fuel consumption. In addition, future architectures of turbomachines with very high dilution rates (called UHBR in English for “Ultra High By Pass Ratio”) could integrate reducers which would require oil cooling, and therefore increased cooling needs for oil. of the turbomachine oil circuit.
    To overcome the drawbacks of air-oil type heat exchangers, document WO 2014/013170 proposes replacing the air-oil heat exchanger of the oil cooling system of the oil circuit by a device heat pump type thermodynamics. The advantage of such a device is that it makes it possible to reduce the surface area of the heat exchangers (and therefore to reduce the pressure losses induced by these exchangers as well as the effects of a disturbance of the air flow) by a increase in the temperature difference between the hot source (in this case, the oil from the turbomachine oil circuit) and the cold source (in this case, the air coming, for example, from a vein secondary flow of the turbomachine). Indeed, with this thermodynamic device, it is possible to bring the refrigerant used to temperatures much higher than that of the oil, so as to obtain a temperature difference with the air which can be much higher than 50 ° C., which increases the efficiency of the cooling system and makes it possible to limit the size of the latter to reduce the impact of the cooling system on the overall performance of the turbomachine as well as on the fuel consumption by the turbomachine.
    Usually, by refrigerant, we designate a working fluid used in a refrigeration cycle to promote heat exchange between two sources; the refrigerant can be pure or a mixture of pure fluids, such as acetone, ethanol, n-pentane, ...
    The gains obtained by this thermodynamic device in terms of reduction in pressure losses induced by the heat exchangers are however to be qualified in view of the energy cost associated with the supply of power necessary for the operation of the compressor equipping the thermodynamic device, thus than with regard to the energy cost associated with the mass added by the various components of the heat pump.
    PRESENTATION OF THE INVENTION The aim of the present invention is therefore to propose a cooling system which does not have such drawbacks.
    According to the invention, this object is achieved by a cooling system of a circuit of a first fluid of a turbomachine, the cooling system comprising a refrigerant circuit comprising:
    - a first heat exchanger configured to exchange heat between the refrigerant and air,
    - a second heat exchanger configured to exchange heat between the refrigerant and the first fluid,
    a regulator mounted downstream of the first exchanger and upstream of the second exchanger, in the direction of circulation of the refrigerant, and
    - a compressor mounted downstream of the second exchanger and upstream of the first exchanger.
    The cooling system also includes a third exchanger, of the first fluid / air type.
    By heat exchanger is understood, in the usual manner, a device configured to allow the transfer of calories from a first fluid to a second fluid; thus, the first exchanger is configured to transfer calories from the refrigerant to air, while the second exchanger is configured to transfer calories from the first fluid to the refrigerant, and the third exchanger is configured to transfer calories from the first fluid to the air. In some embodiments, the first fluid includes oil.
    The present invention is not limited to the case where the refrigerant is in a thermodynamic state below its critical point, and also covers the embodiments in which the heat exchanges carried out by one and / or the other of the first and second heat exchangers is not accompanied by a change of phase of the refrigerant, when the refrigerant is in a thermodynamic state beyond its critical point.
    In the event that the heat exchange between the refrigerant and air is carried out at a pressure less than or equal to the critical pressure of the refrigerant, the first heat exchanger forms condenser. Alternatively, if the heat exchange is carried out at a pressure higher than the critical pressure, the first exchanger forms a cooler.
    In the event that the heat exchange between the refrigerant and the first fluid is carried out at a pressure less than or equal to the critical pressure of the refrigerant, the second heat exchanger forms an evaporator. Alternatively, if the heat exchange is carried out at a pressure higher than the critical pressure, the second exchanger forms a heater.
    The present invention is obviously not limited to one embodiment in which the heat exchanges carried out by the first and second heat exchangers are carried out at a pressure less than or equal to the critical pressure (subcritical cycle); the invention also covers the case of a transcritical cycle of the refrigerant, in which the heat exchange by the second heat exchanger takes place at a pressure less than or equal to the critical pressure and the heat exchange by the first heat exchanger is done at a pressure higher than the critical pressure of the refrigerant, as well as the case of a supercritical cycle of the refrigerant in which the exchanges carried out by the first and second heat exchangers are both made at a higher pressure at critical pressure.
    The cooling system according to the present invention, which comprises a passive cooling system, constituted by the third exchanger, and an active cooling system, constituted by the refrigerant circuit, is remarkable in that it is suitable for different cooling needs. Thus, when the cooling needs are relatively low, only the third exchanger is used to cool the first fluid in the circuit, while when the cooling needs are greater, the third exchanger is used in combination with the refrigerant circuit to cool the first fluid.
    The refrigerant circuit can thus be reduced in size compared to a cooling system of the first fluid circuit which would only include a refrigerant circuit, which reduces the impact of the mass added by the various components of the refrigerant circuit.
    In addition, in the phases in which only the third exchanger is used for cooling the first fluid, the cost associated with the supply of power necessary for the operation of the compressor of the refrigerant circuit is significantly reduced.
    Furthermore, the duration of use of the refrigerant circuit can be reduced, which thereby reduces the risk of malfunctions related to its wear.
    In addition, the possibility of using a combined refrigerant circuit with the third exchanger reduces the severity of the situation in which the user would be in the event that one of the elements of the circuit refrigerant would not work.
    The heat pump constituted by the refrigerant circuit is thus integrated into the cooling system so that the gain in terms of performance by the presence of the refrigerant circuit compensates for, or even exceeds, the cost inherent in the 'addition of the components of said circuit, and the drawbacks associated with such an addition.
    The third exchanger is, for example and without limitation, of the "surface" type or of the "brick" type.
    The invention is declined below in a series of alternative embodiments, which can be considered alone or in combination with one or more of the preceding.
    In some embodiments, the third exchanger is mounted downstream of the refrigerant circuit, in the direction of circulation of the first fluid.
    Generally, the temperature difference between the first fluid and the air is greater than the temperature difference between the refrigerant and the first fluid; thus, the heat exchanges between the air and the first fluid are optimized by passing the first fluid first through the refrigerant circuit, and more particularly through the second exchanger of said refrigerant circuit, then by passing the first fluid in the third exchanger.
    In some embodiments, the cooling system further comprises a fuel-type heat exchanger - first fluid (called FCOC for "Fuel Cooled Oil Coder"; in known manner, such exchangers have the dual function to ensure that the fuel is heated before it is injected into the combustion chamber and to cool the first fluid heated by the heat dissipations of the engine.
    In some embodiments, the cooling system further includes actuation means configured to interrupt the operation of the refrigerant circuit.
    By this arrangement, the cooling system can easily pass from a first operating mode, in which the refrigerant circuit and the third exchanger are successively traversed by the first fluid so as to cool it, to a second mode in which only the third exchanger is used to cool the first fluid.
    In some embodiments, the air comes from a secondary flow stream of the turbomachine.
    In some embodiments, at least one of the first and third exchangers is configured to be arranged in said secondary flow flow stream of the turbomachine.
    In some embodiments, at least one of the elements taken from the second exchanger, the regulator and the compressor is configured to be arranged in a nacelle of the turbomachine.
    In some embodiments, the cooling system is used to cool the oil in a circuit of a turbomachine.
    The invention also relates to a turbomachine, comprising an oil circuit and a cooling system according to the present invention, the cooling system being configured to dissipate the thermal power generated by the oil from the oil circuit .
    In certain embodiments, the turbomachine is configured to equip an aircraft, and the means for actuating the cooling system are configured to interrupt the operation of the refrigerant circuit when the aircraft is in the flight phase of the cruise type.
    In some embodiments, the actuation means of the cooling system are configured to actuate the refrigerant circuit when the power of the turbomachine is greater than a predetermined threshold.
    The cooling system according to the present invention is thus configured to meet the cooling needs of the oil circuit of the turbomachine during the various flight phases of the aircraft it equips.
    Thus, the third exchanger of the cooling system is dimensioned so that, in the cruising regime of the aircraft, the third exchanger alone dissipates the calories from the oil in the circuit; insofar as the cruising regime has a significant duration compared to the other flight phases, the cruising regime being generally the longest part of a flight, the energy gains obtained due to the non-solicitation of the circuit of refrigerant are significant.
    In the flight phases in which the power of the turbomachine is greater than a predetermined threshold, and in particular when the power of the turbomachine is greater than the power of the turbomachine during cruising speed, for example during the takeoff or ascent of the aircraft, the refrigerant circuit is used in combination with the third exchanger to cool the oil in the oil circuit. In these phases, in the usual way, the refrigerant is heated and vaporized by the evaporator thanks to the heat taken from the oil in the oil circuit, then it is compressed at high temperature and high pressure by the compressor. The refrigerant is then condensed in contact with air by the condenser, to be finally expanded by passing through the expansion valve.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the detailed description given below of an embodiment of the invention given by way of non-limiting example. This description refers to the pages of attached figures, on which:
    - Figure 1 schematically shows a cooling system according to the present invention; and
    FIG. 2 schematically represents a cross section of a turbomachine showing the location of the elements of the cooling system of FIG. 1.
    DETAILED DESCRIPTION OF EXAMPLES OF EMBODIMENT The invention applies to the dissipation of any type of thermal power generated in a turbomachine and which it is necessary to evacuate.
    The example described below relates more particularly to the heat dissipation of the thermal power generated by heating the oil in an oil circuit 100 of a turbomachine 200. However, the system according to the invention could also apply to the dissipation of thermal powers from the heating of various electrical components of any other gas turbine engine, such as for example batteries or electric power generators.
    In known manner, the oil circuit 100 of a turbomachine comprises a set of equipment 102 using cooling and / or lubricating oil, such as rolling bearings (in particular for the turbine shafts and compressors), gearboxes (such as the accessory drive housing), electric generators, etc.
    The oil circuit also includes recovery pumps allowing the recirculation of oil from the equipment to an oil tank, feed pumps and one or more filters.
    The turbomachine 200 also includes a cooling system 2 according to the present invention.
    As shown in FIG. 1, the cooling system 2 comprises a pump 13 for circulating the oil in the circuit, and a thermodynamic device comprising a refrigerant circuit 4.
    For example and without limitation, the refrigerant of circuit 4 is in a thermodynamic state below its critical point, but the present invention obviously also covers embodiments in which the refrigerant is in a thermodynamic state beyond the critical point.
    The refrigerant circuit 4 is equipped with a first heat exchanger 6 which forms, for example and without limitation, condenser, this first heat exchanger being configured to exchange heat between the refrigerant and the air ; for example and without limitation, air is taken from the secondary flow stream of the turbomachine. The first heat exchanger 6 is thus configured to dissipate the thermal power of the refrigerant towards the air.
    The refrigerant circuit 4 further includes a second heat exchanger 8 which forms, for example and without limitation, evaporator, which is configured to provide heat exchange between the refrigerant and the oil from the oil circuit, transferring the heat from the hot oil from the oil circuit 100 to the refrigerant.
    Downstream of the first exchanger 6 and upstream of the second exchanger 8, considered in the direction of circulation of the refrigerant, the refrigerant circuit 4 also comprises a pressure reducer 10.
    Downstream of the second exchanger 8 and upstream of the first exchanger 6, still considered in the direction of circulation of the refrigerant, the refrigerant circuit 4 also includes a compressor 12.
    In operation, when it is necessary to cool the oil in the oil circuit 100, the compressor 12 is started. The second heat exchanger 8 forming an evaporator then makes it possible to vaporize the refrigerant by taking heat from the oil. The compressor 12 makes it possible to increase the pressure and the temperature of the refrigerant in the vapor phase before the latter crosses the first heat exchanger 6 forming a condenser, where it releases heat into the air, by passing from the state gaseous in the liquid state. The refrigerant, then in the liquid phase, then passes through the expansion valve 10 which has the function of reducing its pressure and lowering its temperature, before the refrigerant again crosses the second exchanger 8 forming an evaporator.
    The cooling system 2 according to the present invention also comprises a third exchanger 14, of the oil / air type.
    For example and without limitation, the air from the third exchanger 14 is also taken from the flow stream of the secondary flow of the turbomachine For example and without limitation, the third exchanger 14 is mounted downstream of the refrigerant circuit 4, in the direction of circulation of the oil in the oil circuit 1OO. This arrangement is particularly advantageous and makes it possible to optimize the heat exchanges between, on the one hand, the oil of the oil circuit 1OO and, on the other hand, the refrigerant of the refrigerant circuit 2 and the air of the third exchanger 14, insofar as the temperature difference between the oil and the air is greater than the temperature difference between the oil and the refrigerant.
    One could however design, without departing from the scope of the present invention, a cooling system 2 in which the third exchanger 14 would be mounted upstream of the refrigerant circuit 4, in the direction of circulation of the oil in the oil circuit 100.
    A bypass line 20 is further mounted in the oil circuit 100 in bypass on the refrigerant circuit 4 and includes an inlet 22 arranged between the outlet of the set of equipment 102 of the oil circuit 100 and the inlet of the second exchanger 8 forming an evaporator. The pipe also comprises an outlet 24 arranged between the outlet of the second exchanger 8 forming an evaporator and the inlet of the third exchanger 14.
    A means of closing the conduit leading to the inlet of the second exchanger 8 forming an evaporator, such as a hydraulic valve 26, is mounted between the inlet 22 of the bypass pipe 20 and the inlet of the second exchanger 8 forming an evaporator, said closure means being configured to allow the flow of oil from the oil circuit 100 alternately into the second exchanger 8 of the refrigerant circuit 4, or through the bypass line
    20.
    The closure means could be mounted on the bypass line 20, after entering 22, without departing from the scope of the present invention.
    The cooling system 2 also includes actuation means which are configured to interrupt the operation of the refrigerant circuit 4. The actuation means are thus configured, for example, to cooperate with the hydraulic valve 26, so that the oil in the oil circuit 100 circulates alternately in the refrigerant circuit 4, to be cooled by said refrigerant before being cooled by the third exchanger 14, or in the bypass line 20, so as to only be cooled by the third exchanger 14.
    One could conceive, without departing from the scope of the present invention, a cooling system 2, the actuating means of which would be configured to cooperate with the compressor 12, so as to alternately start or stop the operation of the compressor 12, and consequently alternatively start or stop the operation of the refrigerant circuit 4. In this embodiment, it would then no longer be necessary to provide a bypass line 20 configured to allow the cooling of the oil in the circuit only by the third exchanger 14: the oil in the oil circuit 100, which then circulates in the refrigerant circuit 4 whose operation of the compressor 12 is interrupted, is then in fact not cooled by said refrigerant.
    FIG. 2 schematically represents, in cross section, the turbomachine 200 comprising the oil circuit 100 and the cooling system 2 according to the present invention, the section being carried out along a plane transverse to the longitudinal axis 201 of the turbomachine 200.
    The turbomachine 200 comprises a gas generator 202 and a nacelle 204, both centered on the longitudinal axis 201 of the turbomachine 200, an annular secondary flow stream 206 being delimited between the nacelle 204 and the gas generator 202.
    For example and without limitation, the air used by the cooling system 2 according to the present invention, in particular by the first exchanger 6 forming a condenser and by the third exchanger 14, is air coming from the flow stream of the secondary flow 206 of the turbomachine 200. For this purpose, the first and third exchangers 6, 14 of the cooling system 2 are positioned in the flow flow of the secondary flow 206, for example against an internal surface of nacelle 204.
    So as to limit the pressure drops on the flow stream of the secondary flow 206 caused by the presence of the first exchanger 6, when the operation of the refrigerant circuit 4 is interrupted, for example when the aircraft equipped with the turbomachine 200 is in a cruise-type flight phase, it is conceivable the presence of a mobile covering means, configured to alternately cover the first exchanger 6 when the operation of the refrigerant circuit 4 is interrupted, and to expose the first exchanger 6, when the refrigerant circuit 4 is activated.
    The actuation means described above and which are configured to cooperate, for example, with the hydraulic valve 26, are, for example and without limitation, configured to cooperate with said movable covering means.
    For example and without limitation, the second exchanger 8, the regulator 10 and the compressor 12 are positioned directly on the nacelle 204.
    The third exchanger 14 is thus dimensioned so that it allows the dissipation of calories from the oil in the oil circuit 100 in the cruising phase of the aircraft equipped with the turbomachine 200, without having to use the refrigerant circuit 4. Beyond the power required during such a cruising phase, the heat pump constituted by the refrigerant circuit 4 will be used in order to limit the dimensioning of the third exchanger 14, and thus limit the pressure losses induced by the third exchanger 14 on the flow stream of the secondary flow 206.
    Although the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the revendications. In particular, individual features of the various illustrated / mentioned embodiments can be combined in additional embodiments. Therefore, the description and the drawings should be considered in an illustrative rather than restrictive sense.
    It is also obvious that all the characteristics described with reference to a method can be transposed, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device can be transposed, alone or in combination, to a method.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Cooling system (2) of a circuit (100) of a first fluid of a turbomachine (200), the cooling system comprising a refrigerant circuit (4) comprising:
    - a first heat exchanger (6) configured to exchange heat between the refrigerant and air,
    a second heat exchanger (8) configured to exchange heat between the refrigerant and the first fluid,
    a regulator (10) mounted downstream of the first exchanger (6) and upstream of the second exchanger (8), in the direction of circulation of the refrigerant, and
    - A compressor (12) mounted downstream of the second exchanger and upstream of the first exchanger, the cooling system being characterized in that it further comprises a third exchanger (14), of the first fluid / air type.
    [2" id="c-fr-0002]
    2. Cooling system (2) according to claim 1, characterized in that the third exchanger is mounted downstream of the refrigerant circuit (4), in the direction of circulation of the first fluid in the circuit (100).
    [3" id="c-fr-0003]
    3. Cooling system (2) according to claim 1 or 2, characterized in that it further comprises actuating means configured to interrupt the operation of the refrigerant circuit.
    [4" id="c-fr-0004]
    4. Cooling system (2) according to any one of claims 1 to 3, characterized in that the air comes from a secondary flow flow stream (206) of the turbomachine.
    [5" id="c-fr-0005]
    5. Cooling system (2) according to claim 4, characterized in that at least one of the first (6) and third (14) exchangers is configured to be disposed in said secondary flow flow stream of the turbomachine.
    [6" id="c-fr-0006]
    6. Cooling system (2) according to any one of claims 1 to 5, characterized in that at least one of the elements taken from the second exchanger (8), the regulator (10) and the compressor (12 ) is configured to be placed in a nacelle (204) of the turbomachine.
    [7" id="c-fr-0007]
    7. Cooling system (2) according to any one of claims 1 to 6, characterized in that the first fluid comprises oil.
    [8" id="c-fr-0008]
    8. Turbomachine (200), comprising an oil circuit (100) and a cooling system (2) according to any one of claims 1 to 7, the cooling system being configured to dissipate the thermal power generated by the oil in the oil circuit.
    [9" id="c-fr-0009]
    9. Turbomachine (200) according to claim 8, comprising a cooling system according to claim 3, the turbomachine being configured to equip an aircraft, the actuation means being configured to interrupt the operation of the refrigerant circuit (4) when the aircraft is in a cruise type flight phase.
    [10" id="c-fr-0010]
    10. Turbomachine (200) according to claim 8 or 9, comprising a cooling system according to claim 3, the turbomachine being configured to equip an aircraft, the actuation means being configured to actuate the refrigerant circuit (4) when the power of the turbomachine is greater than a predetermined threshold.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US10954832B2|2021-03-23|
    FR3056641B1|2020-06-12|
    US20190309665A1|2019-10-10|
    WO2018055307A1|2018-03-29|
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    法律状态:
    2017-04-13| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-30| PLSC| Search report ready|Effective date: 20180330 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1658961|2016-09-23|
    FR1658961A|FR3056641B1|2016-09-23|2016-09-23|SYSTEM FOR COOLING A CIRCUIT OF A FIRST FLUID OF A TURBOMACHINE|FR1658961A| FR3056641B1|2016-09-23|2016-09-23|SYSTEM FOR COOLING A CIRCUIT OF A FIRST FLUID OF A TURBOMACHINE|
    US16/335,936| US10954832B2|2016-09-23|2017-09-22|System for cooling a circuit of a first fluid of a turbomachine|
    PCT/FR2017/052555| WO2018055307A1|2016-09-23|2017-09-22|System for cooling a circuit of a first fluid of a turbomachine|
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