法国专利FR3028291A1 MOTOR ASSEMBLY PROVIDED WITH A TWO STAGE COOLING DEVICE FOR THE INTAKE AIR OF A TURBOMOTEUR

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专利摘要:
The present invention relates to a power plant (1) comprising at least one compressor (21), at least one heat engine (20) and a cooling device (10) for the intake air of said heat engine (20), said a heat engine (20) having a combustion chamber (22). Said cooling device (10) consists of a "trithermal" thermal machine arranged between two stages (25,26) of compression of said compressor (21) and comprising a refrigerant and two evaporators (12,14). Said intake air circulates successively in said two evaporators (12, 14) between said two stages (25, 26) of compression in order firstly to cool said intake air between said two stages (25, 26) of compression before being injected into said combustion chamber (22) and secondly vaporizing said refrigerant.
公开号:FR3028291A1
申请号:FR1402533
申请日:2014-11-07
公开日:2016-05-13
发明作者:Vincent Pomme
申请人:Airbus Helicopters SAS；
IPC主号:

专利说明:

[0001] Power plant provided with a two-stage cooling device for the intake air of a turbine engine. The present invention is in the field of motor installations and more particularly heat exchange devices for motor installations. The present invention relates in particular to a power plant provided with a two-stage cooling device of the intake air of at least one engine of this power plant. The present invention also relates to a two-stage cooling process of the intake air of at least one engine of such a power plant. This power plant is particularly intended to equip a rotary wing aircraft and allows the cooling of the intake air of at least one gas turbine of this power plant between two stages of compression of this intake air, upstream a combustion chamber of each gas turbine. Indeed, it is known that increasing the intake air pressure before injection into the combustion chamber of a heat engine increases the efficiency of the engine and the power it can provide. On the other hand, this compression of the intake air is accompanied by an increase in its temperature and, consequently, by a decrease in its density. Cooling this intake air after compression again improves the efficiency of the engine and increase its efficiency and power output. For example, on combustion engines used in cars, an air-air heat exchanger is often used to cool the intake air leaving a turbocharger and before entering the combustion chamber of the engine. Similarly, in a known manner in the field of turbine engines, an air-air heat exchanger can be used to cool the intake air at the outlet of an intermediate stage of a compressor before it is reinjected into the next stage. of this compressor, upstream of the combustion chamber of the turbine engine. In these two examples, the cooling of the intake air makes it possible to have, at the end of the compression phase, intake air at a lower temperature which makes it possible to increase the power supplied by the heat engine or the engine. turbine engine. This type of exchanger for cooling air is generally referred to as "intercooler" in English. Such an intercooler is often an air-to-air exchanger, but can also be an air-liquid exchanger. US8813503 discloses a method and a system for managing the cooling temperature of the intake air of a turbine engine in order to limit the condensation of this intake air during its passage into the engine. an intercooler located between two compression stages of a gas turbine. This system controls in particular the temperature of the air in an intake air cooler located upstream of the two compression stages and the intercooler.
[0002] On the other hand, the use of such an intercooler on board a rotary wing aircraft in order to increase the power supplied by the turbine engine or turboshafts of this aircraft is difficult and, consequently, not applied today.
[0003] Firstly, the integration of an intercooler, which is usually an air / air exchanger, in the vicinity of the turbine engine of an aircraft and in particular near the zone of its compressors is difficult. Indeed, the dimensions of the intercooler can be important to have a significant power gain of the turbine engine obtained through this intercooler. Its dimensions are then unfavorable to the implementation of the intercooler in an aircraft. In addition, the mass of the intercooler can also be large and the ratio between the power gain obtained and the increase in the mass of the aircraft is reduced, or even close to zero. In fact, the dimensions of the intercooler must be limited so that this intercooler can be implanted in a rotary wing aircraft. But the increase in the power of the turbine engine of the aircraft is then low and the interest of this implementation is limited. Finally, it is generally complex, when it is installed in a rotary wing aircraft, to convey cooling air to this intercooler, which can limit its efficiency and, consequently, the gain in efficiency. power obtained at the turbine engine of the aircraft. On the other hand, an intercooler and generally a heat exchanger are thermal machines using a single source of heat. This source of heat is generally ambient air in the case of an air / air exchanger. We can then speak of "monothermal" thermal machine. These monothermal thermal machines are limited to a heat exchange between two fluids.
[0004] There are also thermal machines using several heat sources. Such thermal machines are capable of converting, when they are driving, thermal energy into mechanical energy or, when they are receivers, mechanical energy into thermal energy. Such thermal machines use a fluid which undergoes cyclic transformations during which this fluid exchanges with the outside of the energy in the form of work and with the heat sources of the energy in the form of heat. Thermal machines "dithermes" are known, that is to say using two thermal sources of different temperatures, such as a combustion engine, a steam generator or a refrigerating machine. Also known are thermal machines "tritherm", that is to say using three thermal sources. Such trithermal thermal machines are used in particular as refrigerating machines according to the known ejector refrigerating cycle. Such an ejector refrigerating cycle is as follows: at the outlet of a condenser, a refrigerant in liquid form is directed on the one hand to a driving loop and on the other hand to a refrigerating loop, the driving loop comprises a a pump which compresses a first portion of the refrigerant and a first evaporator in which a first portion of the refrigerant is converted into a gaseous form, the refrigerating loop comprises a pressure regulator which expands a second portion of the refrigerant and a second evaporator in which this second part of the refrigerant fluid is converted into gaseous form, the first part of the refrigerant is then used as the engine coolant in an ejector for compressing and driving the second part of the refrigerant and for the second part mix the two parts of the refrigerant before entering the condenser to transform this cooling fluid in liquid form, the cycle being thus looped. The three heat sources are used respectively at the two evaporators and the condenser to exchange thermal energy with the refrigerant. These thermal machines, whether dithermes or trithermes, use thermodynamic cycles such as the "Carnot" cycle or the "Rankine" cycle. The Rankine cycle is a thermodynamic cycle that is close to the Carnot cycle. It is distinguished by the substitution of the two isothermal transformations of the Carnot cycle by two isobaric transformations. The cycle is thus composed successively of four transformations: adiabatic compression, isobaric vaporization, adiabatic expansion and isobaric liquefaction. Industrial applications of the Rankine cycle are, for example, systems using heat lost by industrial processes to provide an additional power supply. The Rankine cycle is used in particular in steam plants including those equipping nuclear power plants. The Rankine cycle is also used with organic fluids whose vaporization temperature is lower than that of water. The temperatures of the heat sources used with this Rankine cycle can then be reduced. For example, US8438849 discloses a heat recovery system using two heat sources and comprising a high pressure turbine and a low pressure turbine. These two turbines operate according to the Rankine cycle and generate mechanical energy that is then transformed into electricity. Also known is US2010 / 0242479 which discloses a system for energy recovery using at least two heat sources of different temperatures and several cycles of Rankine in cascade. This energy recovery system makes it possible, on the one hand, to generate transformable mechanical energy into electricity and, on the other hand, thermal energy to cool and / or heat a complementary fluid through one or more exchangers. The present invention therefore aims to provide a device to overcome the limitations mentioned above, this device to make possible and interesting the integration of the principle of an intercooler on board a rotary wing aircraft to to gain power. According to the invention, a power plant comprises at least one compressor and at least one heat engine and a cooling device for the intake air of each heat engine, each heat engine being provided with a combustion chamber. Each compressor has at least two compression stages to compress the intake air prior to injection into the combustion chamber of each engine.
[0005] This cooling device is remarkable in that it forms a trithermal heat machine comprising in particular a refrigerant, first pipes and two evaporators. A first conduit connects a first compression stage of a compressor to a first evaporator of this cooling device. First pipes also connect the first evaporator to a second evaporator of this cooling device as well as this second evaporator to a second compression stage of the compressor. The intake air then circulates in the first ducts and successively in the two evaporators of this cooling device so as, on the one hand, to vaporize the refrigerant and, on the other hand, to cool the intake air between the two. compression stages. The cooling system is thus composed of two evaporator type heat exchangers in which the intake air of the heat engine and the refrigerant circulate. The refrigerant is circulated by means of a trithermal thermal machine whose principle is known in the state of the art, the intake air being circulated by the first compression stage of a compressor of the power plant. The first evaporator of the cooling device thus constitutes a first cooling stage of the intake air of the heat engine and the second evaporator 25 completes the cooling of this intake air, constituting a second stage of cooling of the air. 'admission. This cooling makes it possible to cool the intake air before it enters the second compression stage and, consequently, to have, at the end of the compression phase, an intake air entering the combustion chamber of the combustion engine. a lower temperature which allows to significantly increase the power delivered by the engine. The first and second evaporators of the cooling device also serve as gas generators of the refrigerant, transforming the refrigerant from a liquid phase to a gas phase. Advantageously, the use of a cooling device constituted by a trithermal thermal machine makes it possible to replace the work generally consumed by a compressor on the one hand by a much lower work and consumed by a pump, and on the other hand by a heat supplied to evaporators at medium or high temperature. In fact, the cooling device consumes less energy to cool the intake air and subsequently increase the power delivered by the engine. Consequently, the balance of the power consumed by the cooling device and the additional power delivered by the heat engine is positive and favorable to the implementation of such a cooling device within a power plant intended in particular to equip a rotary wing aircraft. The cooling device being a trithermal thermal machine also comprises a pump, an expander, a compression and drive means, a condenser and second conduits. Second conduits connect first the condenser to the pump, the pump to the first evaporator and the first evaporator by means of compression and drive. Second conduits also connect the condenser to the expander, the expander to the second evaporator and the second evaporator by means of compression and drive. Finally, a second conduit connects the compression and driving means to the condenser. The refrigerant thus circulates in the second ducts and passes through the components of this cooling device. The condenser converts a first gaseous phase of the refrigerant into a liquid phase, exchanging thermal energy with a first heat source. Then, the refrigerant separates into two parts.
[0006] The pump compresses a first portion of the refrigerant fluid, this refrigerant being in liquid form, thereby increasing its pressure. The first evaporator then converts this first portion of the refrigerant fluid into a second high pressure gas phase by exchanging thermal energy with a second heat source. In parallel, the regulator transforms a second portion of the refrigerant fluid, this refrigerant also being in liquid form, thus reducing its pressure. The second evaporator converts this second portion of the refrigerant fluid into a third low pressure gas phase by exchanging thermal energy with a third heat source. The compression and drive means compresses and drives the third gaseous phase at low pressure of the refrigerant through the second gaseous phase at high pressure of this refrigerant. This compression and driving means also mixes the third low-pressure gaseous phase and the second high-pressure gaseous phase of the refrigerant to form the first gaseous phase of the refrigerant.
[0007] Finally, this first gaseous phase of the refrigerant fluid circulates in the condenser to be condensed and form the liquid phase of the refrigerant, then restarting a new trithermal cycle.
[0008] This cooling device thus comprises two loops, a primary or driving loop and a secondary or refrigerating loop. The primary loop comprises the pump, the first evaporator, the compression and drive means and the condenser. The refrigerant circulates at high pressure in this primary loop, in particular from the pump to the compression and drive means. The secondary loop comprises the expander, the second evaporator, the compression and drive means and the condenser. The refrigerant circulates at low pressure in this primary loop, including the expander to the compression and drive means. The cooling device thus operates by cooperating with three thermal sources. The first heat source is for example the ambient air surrounding the power plant, this first heat source absorbing the thermal energy of the refrigerant through the condenser. The second heat source and the third heat source are successively the intake air of the heat engine and supply thermal energy to the refrigerant via the first and second evaporators, respectively. The second thermal source is the intake air leaving the first compression stage and entering the intermediate cooling device while the third heat source is the intake air leaving the first evaporator. It may be noted that the third heat source has a lower temperature than the second heat source, the intake air constituting this third heat source having been cooled through the first evaporator. The primary loop preferably works, but not exclusively, according to the Rankine cycle. The Rankine cycle makes it possible to recover mechanical power from a heat source. In the cooling device according to the invention, this heat source is the second heat source and the mechanical power is then used in the secondary loop to compress a part of the refrigerant in the gas phase. This compression and driving means is according to a first embodiment of the invention an ejector whose operating principle is known. The second gaseous phase at high pressure of the refrigerant is accelerated in a convergent-divergent form of the ejector, thereby creating a pressure drop in a mixing zone which has the effect of sucking the third gaseous phase at low pressure. of this refrigerant fluid. The second and third gaseous phases of the refrigerant are then mixed. This results in an increase in the pressure of the mixture of this refrigerant and a decrease in its speed. According to a second embodiment of the invention, the compression and drive means comprise a volumetric expansion valve connected to the first evaporator by a second pipe and a positive displacement compressor connected to the second evaporator by another second pipe. The volumetric expansion valve and the volumetric compressor are connected by a second pipe to the condenser. The volumetric expansion valve and the volumetric compressor are also secured mechanically in rotation, for example by means of a connecting shaft. The volumetric expansion valve is rotated by the second high-pressure gaseous phase of the refrigerant leaving the first evaporator, this second gaseous phase at high pressure of the refrigerant then being expanded in this volumetric expansion valve. The volumetric expansion valve drives the rotary compressor in rotation through the connecting shaft. The third gaseous phase at low pressure of the refrigerant leaving the second evaporator circulates in the volumetric compressor which, through its rotation, compresses and, consequently, causes this third gaseous phase of the refrigerant. The second gaseous phase of the refrigerant flows out of the volumetric expansion valve by a second pipe. Likewise, the third gaseous phase of the refrigerant flows out of the volumetric compressor by a second pipe. These two second pipes meet to form a single second pipe thus allowing the second gas phase and the third gas phase of the refrigerant to mix and then flow to the condenser.
[0009] After this compression and drive means, the entire refrigerant is condensed by heat exchange with the first heat source through the condenser. Advantageously, the condenser can be deported with respect to the position of the heat engine thus facilitating its integration on a rotary wing aircraft for example and also to optimize its thermal efficiency.
[0010] Furthermore, the mechanical power generated by the expansion of the second phase of the refrigerant in the volumetric expansion valve may be greater than the mechanical power required for the compression and entrainment of the third gaseous phase of this refrigerant. As a result, this surplus of mechanical power can be used by one or more auxiliary systems of the cooling device. For this purpose, the cooling device may comprise a mechanical transmission shaft mechanically connected in rotation to the volumetric expansion valve. This mechanical transmission shaft can thus provide this surplus of mechanical power necessary for the operation of an auxiliary system. The cooling device may also comprise a clutch means which solidarises the volumetric expansion valve and the mechanical transmission shaft in rotation. Thus, the mechanical transmission shaft and the volumetric expansion valve can be secured and disengaged in rotation on the one hand according to the availability or not of a surplus of mechanical power and on the other hand according to the need for mechanical power of the auxiliary system. Such a clutch means is for example a magnetic coupling. Advantageously, such a magnetic coupling avoids the use of a mechanical transmission shaft leaving the compression and drive means as well as sealing means such as a rotary joint. The compression and drive means constituted by this volumetric expander and this volumetric compressor can thus be sealed and, consequently, more reliable. An auxiliary system is for example a condenser ventilation system in order to improve the thermal efficiency of this condenser.
[0011] It is also possible to use a portion of the cooling capacity of the refrigerant for at least one additional heat exchange function. For this purpose, the power plant comprises at least a third pipe connected to a second pipe located between the condenser and the pump. The refrigerant can then circulate in this third pipe to a complementary heat exchange system, then return to flow in a second pipe before the pump. For example, the power plant having at least one main power gearbox, a third line connects the second line to the main power gearbox. The refrigerant circulates in this third pipe to the main gearbox to cool it. This cooling capacity of the refrigerant can be used in the context of an emergency cooling or additional cooling in case of temporary overload of the main gearbox. In another example, the power plant being intended to equip a rotary wing aircraft having at least one passenger compartment and at least one heat exchanger for cooling the passenger compartment, a third pipe connects the second pipe to each heat exchanger. The refrigerant circulates in this third pipe to each heat exchanger for cooling the passenger compartment of the aircraft. This refrigerating capacity of the refrigerant can be used instead of a usual air conditioning device of this cabin and thus allows on the one hand a saving in mass thanks to the pooling of the cooling device of the intake air of the engine and on the other hand an optimization of the consumption of the energies used on the aircraft. Indeed, this air conditioning function of the cabin is obtained without additional energy extraction, the cooling device simultaneously providing two cooling functions. According to the same architecture, the refrigerant can also provide cooling of other equipment of an aircraft such as electronic equipment and / or avionics for example. Furthermore, it is also possible to use a part of the heat evacuated during the transformation of the third gaseous phase of the refrigerant into the first liquid phase of the refrigerant via the condenser for at least one additional function of heating. For this purpose, the condenser being a heat exchanger between the refrigerant and a secondary fluid, the power plant comprises a fourth pipe connected to the condenser in order to channel the secondary fluid at the outlet of this condenser. The secondary fluid can then flow in this fourth pipe to an auxiliary device to transmit the heat absorbed at the condenser. For example, the power plant being intended to equip a rotary wing aircraft comprising at least one passenger compartment, the fourth pipe can channel and direct the secondary fluid to this cabin to heat it. This heating principle of the cabin of the aircraft can be used instead of a traditional heating device of this cabin using for example a portion of the compressed air by the compressor of the heat engine and thus avoids overconsumption of fuel from this engine. The secondary fluid may be ambient air surrounding the power plant. The condenser is then a heat exchanger between the refrigerant and the ambient air, this ambient air being directed by the fourth pipe to the cockpit of the aircraft to heat it. The power plant according to the invention thus mainly allows the cooling of the intake air of a heat engine thus providing a significant increase in the power delivered by the engine. In addition, the condenser of the cooling device of this intake air can in particular be deported, the integration of this cooling device in a rotary wing aircraft is facilitated while optimizing the thermal efficiency of the condenser. Moreover, the power plant according to the invention makes it possible, by means of the cooling device, to provide, on the one hand, a heating power to generate additional cooling and heating capacities and, on the other hand, a complementary mechanical power. . The present invention also relates to a method of cooling the intake air of a heat engine of a power plant. During this process, the inlet air of the heat engine is compressed in a compressor of the power plant equipped with two compression stages, a refrigerant circulates in a cooling device of this intake air of thermal engine, - this intake air flows successively in two evaporators of the cooling device between the two compression stages in order firstly to vaporize the refrigerant and secondly to cool the intake air.
[0012] Moreover, during this cooling process of the intake air of a heat engine of a power plant, the cooling fluid is condensed via a condenser, by exchanging thermal energy with a first thermal source, - a first portion of the refrigerant is compressed by means of a pump, - the first part of the refrigerant is vaporized by means of a first evaporator, by exchanging thermal energy with a second thermal source, the second heat source being the intake air, a second part of the refrigerant is expanded by means of an expander, - the second part of the refrigerant is vaporized by means of a second evaporator, exchanging thermal energy with a third heat source, the third thermal source being the intake air, and - the second part of the refrigerant is compressed and driven by r through the first part of the refrigerant, then mixing the second portion of the refrigerant and the first portion of the refrigerant. According to a first embodiment of this method, the second portion of the refrigerant is compressed and entrained via the first portion of the refrigerant and the second portion of the refrigerant and the first portion of the refrigerant are mixed by means of an ejector. According to a second embodiment of this method, the second part of the refrigerant is compressed and entrained by means of the first part of the refrigerant fluid by means of a volumetric expansion valve and a volumetric compressor mechanically integral in rotation. The volumetric expansion valve is rotated by the first part of the refrigerant and the second part of the refrigerant circulates in the volumetric compressor. Then, the second portion of the refrigerant is mixed with the first portion of the refrigerant.
[0013] In addition, part of the mechanical energy available at the volumetric expansion valve may be used, the volumetric expansion valve being mechanically connected in rotation to a mechanical transmission shaft. Moreover, it is possible to use the heat evacuated during the condensation of the refrigerant for an auxiliary heating function, such as the heating of a cockpit of an aircraft. In addition, one can use a portion of the thermal energy of the refrigerant for at least one additional heat exchange function. For example, a portion of the thermal energy of the refrigerant may be used for cooling a main power transmission gearbox of the powerplant or the cooling of a cockpit of an aircraft. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a rotary wing aircraft equipped with an installation According to the invention, and FIGS. 2 and 3, two embodiments of the power plant according to the invention. The elements present in several separate figures are assigned a single reference.
[0014] In FIG. 1, a rotary wing aircraft 2 is shown, this aircraft 2 comprising a main rotor 28 positioned above a fuselage 3 and a rear anti-torque rotor 29 positioned at the rear end of a tail boom.
[0015] The aircraft 2 also comprises a power plant 1 and a passenger compartment 26 located inside the fuselage 3. The power plant 1 comprises a compressor 21, a heat engine 20, a main power transmission box 24 and a power unit. cooling of the intake air of the heat engine 20. The heat engine 20 is mechanically connected to the main power transmission gearbox 24 to rotate the main rotor 28 and the rear rotor 29. Two embodiments of The power plant 1 is shown in FIGS. 2 and 3 respectively. In a manner common to these two embodiments of the power plant 1, each heat engine 20 is a turbine engine and comprises a combustion chamber 22 as shown in FIG. An expansion turbine 23. Each compressor 21 is provided with two compression stages 25, 26 for compressing the intake air before it is injected into the combustion chamber 22. The cooling device 10 consists of two loops. A primary loop comprises a pump 11, a first evaporator 12, a condenser 16 and a compression and drive means 15. A secondary loop comprises an expander 13, a second evaporator 14, the condenser 16 and the means of compression and training 15.
[0016] The cooling device 10 also comprises first ducts 27 and second ducts 17. The first ducts 27 connect the first compression stage 25 to the first evaporator 12, the first evaporator 12 to the second evaporator 14 and the second evaporator 14 to the second stage 26 compression. The second lines 17 connect, on the one hand, in the primary loop, the condenser 16 to the pump 11, the pump 11 to the first evaporator 12 and the first evaporator 12 to the compression and drive means 15 and, on the other hand, in the secondary loop, the condenser 16 to the expander 13, the expander 13 to the second evaporator 14 and the second evaporator 14 to the compression and drive means 15. A second conduit 17 also connects the compression and drive means 15 to the condenser 16 to close the primary loop and the secondary loop. The cooling device 10 thus forms a trithermal thermal machine whose primary loop operates according to the Rankine cycle.
[0017] A cooling fluid circulates in the cooling device 10 and more precisely in the primary loop and the secondary loop, passing through all the components 11, 12, 13, 14, 15, 16 of the cooling device 10 as well as the second conduits 17. .
[0018] The condenser 16 makes it possible to condense the refrigerant in a liquid phase, evacuating thermal energy to a first heat source constituted by the ambient air surrounding the power plant 1. Then, the cooling fluid separates into two parts in the second led 17.
[0019] In the primary loop, the pump 11 compresses the refrigerant which is then transformed into a gas phase at high pressure in the first evaporator 12 by absorbing thermal energy at a second heat source constituted by the intake air coming out of the first 25 compression stage. In the secondary loop, the expander 13 expands the refrigerant which is then transformed into a low pressure gas phase in the second evaporator 14 by absorbing thermal energy to a third heat source constituted by the intake air coming out of the first Evaporator 12. The compression and drive means 15 compresses and entrains the refrigerant flowing in the secondary loop through the refrigerant flowing in the primary loop. This compression and drive means 15 also mixes the cooling fluid circulating in the primary and secondary loops before it is directed towards the condenser 16. Finally, the refrigerant circulates again in the condenser 16 and restarts a new trithermal cycle. . The intake air circulates in the compressor 21 as well as in the cooling device 10. The intake air successively passes through the two evaporators 12, 14 between the two stages 25, 26 of compression so as, on the one hand, to vaporize the refrigerant and secondly to cool the intake air between the two stages 25,26 compression.
[0020] This cooling of the intake air between the two stages 25, 26 of compression makes it possible to increase the power delivered by the turbine engine 20. According to the first embodiment of the power plant 1 represented in FIG. compression and drive 15 is an ejector, for example of convergent-divergent form. According to the second embodiment of the power plant 1 shown in FIG. 3, the compression and drive means 15 comprise a volumetric expansion valve 18 connected to the first evaporator 12 by a second pipe 17 and a volumetric compressor 19 connected to the second evaporator 14 by a second pipe 17. The volumetric expansion valve 18 and the volumetric compressor 19 are mechanically fixed in rotation and connected by a second pipe 17 to the condenser 16. The volumetric expansion valve 18 is thus rotated by the refrigerant leaving the first evaporator 12, the volumetric expander 18 rotating the volumetric compressor 19 which then compresses and drives the refrigerant leaving the second evaporator 14. Then, the refrigerant from the primary and secondary loops is mixed and directed to the condenser 16. According to this second embodiment of the installa 1, the cooling device 10 also comprises a mechanical transmission shaft 32, a clutch means 31, an inlet pipe 53, a ventilation system 33 and a fourth pipe 52. The clutch means 31 is constituted by a magnetic coupling solidarisant in rotation the volumetric expander 18 25 and the mechanical transmission shaft 32. The ventilation system 33 is integral in rotation with the mechanical transmission shaft 32. The inlet pipe 53 and the fourth pipe 52 are connected to the condenser 16. The inlet pipe 53 can channel and direct a portion of the ambient air surrounding the power plant 1 to the condenser 16 and the fourth pipe 52 can channel the ambient air Exiting the condenser 16. The ventilation system 33 activates the circulation 5 of the ambient air in the inlet pipe 53 thus improving the thermal efficiency of the condenser 16. As shown in FIG. 1, the fourth line 52 makes it possible to direct the ambient air coming from the condenser 16 towards the passenger compartment 26 of the aircraft 2 in order to heat it.
[0021] According to this second embodiment of the power plant 1, the cooling device 10 comprises a separator 35 positioned after the condenser 16 on a second pipe 17. This separator 35 makes it possible to separate the liquid and gaseous phases from the refrigerant and does not delivers at its output only the liquid phase 15 of the refrigerant. Thus, after the separator 35, only a liquid phase of the refrigerant flows in the second ducts 17 to the pump 11 and the expander 13. This absence of gas phase in the second ducts 17 is particularly important for efficient operation of the refrigerant. According to this second embodiment of the power plant 1, the power plant 1 comprises a third pipe 51 connected to a second pipe 17 located between the condenser 16 and the pump 11. This third pipe 51 is also shown. 25 in FIG. 1 and makes it possible to connect the second pipe 17 to the main power transmission box 24 and to a heat exchanger 27 located in the cockpit 26 of the aircraft 2. The refrigerant fluid thus circulates in a third pipe 51 from a second pipe 17, passes through the main power transmission 24 and the heat exchanger 27 and returns to the second pipe 17 by a The refrigerant fluid thus enables the main power transmission box 24 as well as the passenger compartment 26 of the aircraft 2 to be cooled. Naturally, the present invention is subject to numerous variations as to its implementation. . Although several embodiments have been described, it is understood that it is not conceivable to exhaustively identify all possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.

权利要求:
Claims (23)
[0001]
REVENDICATIONS1. Power plant (1) comprising at least one compressor (21), at least one heat engine (20) and a cooling device (10) for the intake air of each heat engine (20), each heat engine (20) ) being provided with a combustion chamber (22), each compressor (21) having at least two stages (25,26) of compression for compressing said intake air prior to injection into said combustion chamber (22); each heat engine (20), characterized in that said cooling device (10) is a trithermal heat machine comprising a refrigerant, first pipes (27) and two evaporators (12, 14), said first pipes (27) connecting a first stage (25) of compression to a first evaporator (12), said first evaporator (12) to a second evaporator (14) and said second evaporator (14) to a second stage (26) of compression, said air of admission flowing in said first conduits ( 27) and successively in said two evaporators (12,14) in order firstly to vaporize said refrigerant fluid and secondly to cool said intake air between said two stages (25,26) of compression.
[0002]
2. Powerplant (1) according to claim 1, characterized in that said cooling device (10) comprises a pump (11), an expander (13), a compression and drive means (15), a condenser (16) and second pipes (17), said refrigerant flowing in said second pipes (17) and the components (11,12,13,14,15,16) of said cooling device (10), said second pipes ( 17) connecting: - said condenser (16) to said pump (11), said pump (11) to said first evaporator (12) and said first evaporator (12) to said compression and drive means (15), - said condenser (16) said expander (13), said expander (13) to said second evaporator (14) and said second evaporator (14) to said compression and drive means (15), and - said compression and drive means ( 15) to said condenser (16).
[0003]
3. Powerplant (1) according to claim 2, characterized in that said compression and drive means (15) is an ejector.
[0004]
4. Powerplant (1) according to claim 2, characterized in that said compression and drive means (15) comprises a volumetric expansion valve (18) connected to said first evaporator (12) by a second pipe (17) and a volumetric compressor (19) connected to said second evaporator (14) by a second conduit (17), said volumetric expander (18) and said positive displacement compressor (19) being connected by a second conduit (17) to said condenser (16), said expander volumetric device (18) and said volumetric compressor (19) being mechanically integral in rotation, said volumetric expander (18) being rotated by said refrigerant leaving said first evaporator (12) and said refrigerant leaving said second evaporator (14) flowing in said positive displacement compressor (19).
[0005]
5. Powerplant (1) according to claim 4, characterized in that, said cooling device (10) comprising a mechanical transmission shaft (32), said volumetric expander (18) is mechanically connected in rotation to said mechanical transmission shaft ( 32).
[0006]
6. Powerplant (1) according to claim 5, characterized in that said cooling device (10) comprises a clutch means (31) solidarisant in rotation said volumetric expander (18) and said mechanical transmission shaft ( 32).
[0007]
7. Powerplant (1) according to any one of claims 5 to 6, characterized in that said cooling device (10) comprises a ventilation system (33) of said condenser (16), said ventilation system (33). ) being secured mechanically in rotation with said mechanical transmission shaft (32).
[0008]
8. Powerplant (1) according to any one of claims 2 to 7, characterized in that, said power plant (1) comprising at least a third pipe (51), said third pipe (51) is capable of connecting a second pipe (17) located between said condenser (16) and said pump (11) to a complementary system, said refrigerant flowing in said third pipe (51) and said complementary system.
[0009]
9. Powerplant (1) according to claim 8, characterized in that, said power plant (1) comprising at least one main gearbox (24), said complementary system is said main gearbox ( 24), said refrigerant circulating in said third conduit (51) and said main power transmission (24) for cooling said main power transmission (24).
[0010]
10. Powerplant (1) according to any one of claims 8 to 9, characterized in that said power plant (1) being intended to equip a rotary wing aircraft (2) comprising at least one passenger compartment (26) and to less a heat exchanger (27) for cooling said passenger compartment (26), said complementary system is each heat exchanger (27), a third pipe (51) being able to connect a second pipe (17) located between said condenser (16) and said pump (11) to each heat exchanger (27), said refrigerant flowing in said third pipe (51) and each heat exchanger (27) for cooling said passenger compartment (26).
[0011]
11. Power plant (1) according to any one of claims 2 to 10, characterized in that said condenser (16) being a heat exchanger between said refrigerant and a secondary fluid, said power plant (1) comprises a fourth pipe (52) connected to said condenser (16) for channeling and directing said secondary fluid to an ancillary device.
[0012]
12. Powerplant (1) according to claim 11, characterized in that said power plant (1) being intended to equip a rotary wing aircraft (2) comprising at least one passenger compartment (26), said fourth line (52) is adapted to channel and direct said secondary fluid to said passenger compartment (26) to heat said passenger compartment (26).
[0013]
13. Powerplant (1) according to any one of claims 2 to 12, characterized in that said condenser (16) is a heat exchanger between said refrigerant and ambient air surrounding said power plant (1).
[0014]
14. A method of cooling the intake air of a heat engine (20) of a power plant (1), during which, said intake air is compressed in a compressor (21) of said power plant (1) provided with two stages (25,26) of compression, a refrigerant circulates in a cooling device (10) of the intake air of said engine (20), and said intake air circulates successively in two evaporators (12,14) of said cooling device (10) between said two stages (25,26) of compression in order firstly to vaporize said refrigerating fluid and secondly to cool said intake air.
[0015]
15. A method of cooling according to claim 15, characterized in that - said cooling fluid is condensed, by exchanging thermal energy with a first heat source, - a first portion of said refrigerant is compressed, - said vaporized first part of said refrigerant, by exchanging thermal energy with a second heat source, said second heat source being said intake air, a second part of said refrigerant is expanded, said second part of said refrigerant is vaporized, exchanging thermal energy with a third heat source, said third thermal source being said intake air, - said second part of said refrigerant is compressed and entrained through said first part of said refrigerant, and then mixed said second portion of said refrigerant and said first portion of said refrigerant.
[0016]
16. A method of cooling according to any one of claims 14 to 15, characterized in that one compresses and that one drives said second portion of said refrigerant through said first portion of said refrigerant and that the said second portion of said refrigerant and said first portion of said refrigerant are mixed by an ejector.
[0017]
17. Cooling method according to any one of claims 14 to 15, characterized in that one compresses and that one drives said second portion of said refrigerant through said first portion of said refrigerant through a a volumetric expansion valve (18) and a volumetric compressor (19) mechanically integral in rotation, said volumetric expander (18) being rotated by said first portion of said refrigerant and said second portion of said refrigerant circulating in said positive displacement compressor (19), then mixing said second portion of said refrigerant and said first portion of said refrigerant.
[0018]
18. A method of cooling according to claim 17, characterized in that a portion of the mechanical energy available at said volumetric expander (18) is used, said volumetric expander (18) being mechanically connected in rotation to a shaft. mechanical transmission (32).
[0019]
19. A method of cooling according to any one of claims 14 to 18, characterized in that the heat evacuated during the condensation of said refrigerant for an auxiliary heating function is used.
[0020]
20. A method of cooling according to claim 19, characterized in that said auxiliary heating function is the heating of a passenger compartment (26) of said aircraft (2).
[0021]
21. A method of cooling according to any one of claims 14 to 20, characterized in that one uses a portion of the thermal energy of said refrigerant for at least one complementary function of heat exchange.
[0022]
22. A method of cooling according to claim 21, characterized in that said additional cooling function is the cooling of a main gearbox (21) of said power plant (1).
[0023]
23. A method of cooling according to any one of claims 21 to 22, characterized in that, said cooling method being used to cool the intake air of a heat engine (20) equipping an aircraft (2) to rotary wing, said additional cooling function being the cooling of a passenger compartment (26) of said aircraft (2).

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同族专利:

公开号 | 公开日

US20160131032A1|2016-05-12|

FR3028291B1|2019-04-12|

EP3018322B1|2019-08-28|

EP3018322A1|2016-05-11|

US10047675B2|2018-08-14|

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2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |

2016-05-13| PLSC| Search report ready|Effective date: 20160513 |

2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |

2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |

2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |

2021-08-06| ST| Notification of lapse|Effective date: 20210705 |

优先权:

申请号 | 申请日 | 专利标题

FR1402533|2014-11-07|

FR1402533A|FR3028291B1|2014-11-07|2014-11-07|MOTOR ASSEMBLY PROVIDED WITH A TWO STAGE COOLING DEVICE FOR THE INTAKE AIR OF A TURBOMOTEUR|FR1402533A| FR3028291B1|2014-11-07|2014-11-07|MOTOR ASSEMBLY PROVIDED WITH A TWO STAGE COOLING DEVICE FOR THE INTAKE AIR OF A TURBOMOTEUR|

EP15189968.9A| EP3018322B1|2014-11-07|2015-10-15|A power plant having a two-stage cooler device for cooling the admission air for a turboshaft engine|

US14/934,606| US10047675B2|2014-11-07|2015-11-06|Power plant having a two-stage cooler device for cooling the admission air for a turboshaft engine|

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