阅读说明：本技术 用于利用传热流体冷却航空机架的设备 (Device for cooling an aircraft frame with a heat transfer fluid ) 是由 F·吉约 J-M·布利诺 P·阿维尼翁 S·洛克斯 F·阿尔贝罗 于 2018-06-01 设计创作，主要内容包括：一种用于冷却放置在飞行器(1)的航空机架(80)中的电子模块(81,82)的设备(100),该飞行器包括通风舱(31),该冷却设备(100)包括：用于循环传热流体(11)的闭合回路(10)；用于使传热流体(12)在闭合回路(10)中循环的第一装置；第一热交换器(50),其包括冷回路(51),该冷回路设置有用于连接至用于循环传热流体(11)的闭合回路(10)的第一装置(89,90)并且与航空机架(80)的热源热连接；第二热交换器(60)包括热回路(61),该热回路(61)设置有用于连接至用于循环传热流体(11)的闭合回路(10)的第二装置(20,21),以及热连接至来自通风舱(31)的排气口(30)的冷回路(62)。一种航空机架和包括这样的机架的飞行器。(an apparatus (100) for cooling electronic modules (81,82) placed in an airframe (80) of an aircraft (1), the aircraft comprising a ventilation cabin (31), the cooling apparatus (100) comprising a closed circuit (10) for circulating a heat transfer fluid (11), a th means for circulating the heat transfer fluid (12) in the closed circuit (10), a th heat exchanger (50) comprising a cold circuit (51) provided with a th means (89, 90) for connecting to the closed circuit (10) for circulating the heat transfer fluid (11) and being thermally connected with a heat source of the airframe (80), a second heat exchanger (60) comprising a hot circuit (61), the hot circuit (61) being provided with a second means (20, 21) for connecting to the closed circuit (10) for circulating the heat transfer fluid (11), and a cold circuit (62) thermally connected to an exhaust (30) from the ventilation cabin (31), aircraft airframe and aircraft airframe comprising such an airframe.)

A device (100) for cooling at least electronic modules (81,82) placed in an aircraft frame (80) of an aircraft (1), the aircraft comprising a ventilated cabin (31), the cooling device (1) comprising:

a closed circuit (10) for circulating a heat transfer fluid (11);

th means for circulating the heat transfer fluid (12) in the closed circuit (10);

-th heat exchanger (50) comprising a cold circuit (51), said cold circuit (51) being provided with -th devices (89, 90) for connection to the closed circuit (10) for circulating a heat transfer fluid (11) and being thermally connected with a heat source of the aircraft frame (80);

-a second heat exchanger (60) comprising a hot circuit (61) provided with second means (20, 21) for connection to the closed circuit (10) for circulating a heat transfer fluid (11), and a cold circuit (62) thermally connected to an exhaust (30) from the ventilation cabin (31).

2. The cooling apparatus (100) of claim 1, wherein the -th heat exchanger (50) includes -th means for forced air flow (94).

3. A cooling apparatus (100) as claimed in any of the preceding claims, characterized in that the second heat exchanger (60) comprises second means for forced air flow (32).

4., the cooling device (100) of claim 2 or 3, characterized in that the and/or second means for forcing air flow comprise fans (32, 94).

5. The cooling apparatus (100) according to any of the preceding claims, wherein the th heat exchanger (50) comprises second means (93) for circulating the heat transfer fluid (11) in the closed circuit (10).

6. A cooling device (100) as in claim 3, characterized by comprising means for controlling and supplying (40) the th means for forced air flow.

7. The cooling apparatus (100) according to any , wherein the device for circulating (12) the heat transfer fluid (11) comprises a turbine (12) the rotor (2) of which acts as an armature for the short circuit.

A method for cooling an electronic module of an airframe (80) of an aircraft (1), comprising a step of transferring heat from the electronic module (81,82) to a closed circuit (10) for circulating a heat transfer fluid (11), and a step of removing heat from the heat transfer fluid (11) into an air flow drawn through an air outlet of a ventilated cabin (31) of the aircraft (1).

An airframe (80) of the kind 9, , comprising a th heat exchanger (50), a cold circuit (51), said cold circuit (51) being provided with th means (89, 90) to a closed circuit (10) of a heat transfer fluid (11).

10. The airframe (80) as recited in claim 9, characterized in that said heat exchanger (50) is arranged to exchange heat by conduction with said heat transfer fluid (11).

An aircraft (11) of comprising a cooling device (100) of any of claims 1 to 7 of .

An aircraft of the type 12, , comprising an airframe as defined in claim 9 or claim 10, .

Technical Field

The invention applies to the field of aircraft racks intended to house electronic modules, and in particular to devices for cooling such racks.

Background

The management of the flight control and all the information necessary for the proper functioning of the aircraft is performed in the aircraft by electronic modules inserted in or more airframes distributed throughout the entire aircraft, in operation, the electronic modules generate heat that must be eliminated in order not to jeopardize the integrity of the modules and/or their performance, such elimination is generally done using equipment for cooling the electronic modules placed in the airframes, which includes means for forcing the flow of ventilation air into the airframes, this air flow being drawn and returned to the ventilation circuit throughout the aircraft.

Object of the Invention

The object of the invention is to reduce the size of the equipment used for cooling the electronic modules placed in the airframe of an aircraft.

Disclosure of Invention

To this end, an apparatus for cooling at least electronic modules placed in an aircraft frame of an aircraft comprising a ventilated cabin is provided, the cooling apparatus comprising a closed circuit for circulating a heat transfer fluid, a th device for circulating the heat transfer fluid in the closed circuit and a th heat exchanger comprising a cold circuit provided with a th device for connecting to the closed circuit for circulating the heat transfer fluid and thermally connected to a heat source in the aircraft frame.

The previously lost resource is then used as a heat sink, i.e. the air flow at the outlet of the air outlet of the ventilation chamber.

When the th heat exchanger comprises the th means for forced air flow and/or the second heat exchanger comprises the second means for forced air flow, the reliability of the cooling device is improved.

A particularly robust and economical device is obtained when the th and/or second means for forced air flow comprise a fan.

When the th heat exchanger includes a second means for circulating a heat transfer fluid in a closed loop, the reliability of the cooling device is further improved .

Advantageously, the cooling device comprises means for controlling and supplying th means for forced air flow, which means allow activation of th means only when necessary, thereby reducing the power consumption of the cooling device.

The th device for circulating heat transfer fluid advantageously includes a turbine, the rotor of which acts as a shorting armature, the design is advantageous due to its simplicity of construction, use and maintenance, as well as its robustness and low manufacturing cost in case of turbine failure, the fluid flow is not blocked, and step improves the reliability of the cooling apparatus.

The invention also relates to a method for cooling an electronics module of an aircraft rack, the method comprising a st step of transferring heat from the electronics module to a closed circuit for circulating a heat transfer fluid, and a second step of removing heat from the heat transfer fluid into an air flow drawn from an air outlet of an aircraft cabin.

The invention also relates to an aircraft frame comprising a th heat exchanger, the cold circuit of which th heat exchanger is provided with a th device for connection to a closed circuit for circulating a hot fluid, and an aircraft frame in which the th heat exchanger is arranged to exchange heat by conduction with a heat transfer fluid.

Finally, the invention also includes aircraft having the aforementioned cooling device and/or an airframe of the type described above.

Other features and advantages of the present invention will become apparent from the following description of non-limiting embodiments thereof.

With reference to fig. 1, the cooling device of the invention, generally designated 100, is intended to cool an th aircraft rack 80 of an aircraft 1 and a second aircraft rack 180 identical to the th aircraft rack 80, two electronic modules 81 and 82 being inserted into the th aircraft rack 80 and two electronic modules 181 and 182 being inserted into the second aircraft rack 180.

The cooling device 100 comprises a closed circuit 10 for circulating glycol water 11, the closed circuit 10 being made of aluminium pipes and a circulation pump 12, the closed circuit 10 comprising a th flat flange 13 and a second flat flange 14 connected to homologous flanges 20 and 21, respectively, of an inlet 22 and an outlet 23 of an th aluminium coil 24, the th coil 24 being placed opposite an air outlet 30 of an air-conditioning cabin 31 designed to accommodate passengers, a th fan 32 connected to the control unit 40 being arranged to force an air flow over the th coil 24.

Referring to fig. 2, the th aircraft rack 80 comprises a th aluminum parallelepiped frame 83 defining th units 84 and 85 for housing th electronic modules 81 and 82. the th aircraft rack 80 comprises a th power and communication unit 70 which connects the th electronic modules 81 and 82 to the power supply of the aircraft 1 and to the communication/ control network 71 and 72. the th electronic modules 81 and 82 are held in place in the th units 84 and 85 using th bronze spring blades 83.1 attached to the th frame 83. a second coil 86 made of bent aluminum tubes 87 is welded to a plate 88 for closing the upper part of the fifth 2 6959 frame 83. the fifth plate 88 is also welded to the 1 th frame 83. the second coil 86 comprises a third and a fourth flat flange 89 and 90 placed on the th inlet line 91 and on the th outlet line 92 of the second coil 86 and a third and a fourth flat flange 90 and a fourth flat flange 3690 and a 3690 connected to the second power and communication inlet line of the second coil 80 and 3615. the integral water return circuit and 3610. the second coil 80 is also connected to the closed loop 3610 and 3610. the integral water return circuit and 3617 of the second closed loop 3610. the integral water return and 3610. the integral water return line is connected to the closed loop 3610. the second coil and 3610. the integral water return circuit and 3610. the integral water return line is also connected to the closed 3610 and 3610 closed 3610.

The second coil 86 creates, with the frame 83 of the th airframe 80, a th heat exchanger 50, the cold circuit 51 of the th heat exchanger (consisting of the second coil 86) is connected to the closed circuit 10 the second coil 86 is thermally connected to the th frame 83 as the heat source 52 of the th heat exchanger 50 and exchanges heat primarily by conduction with the th electronic modules 81 and 82₉₁The glycol water 11 entering the th inlet pipe 91 of the second coil 86 cools the th frame 83 by conduction and at a temperature above the inlet temperature T₉₁Outlet temperature T of₉₂Exits the second coil 86 through an outlet duct 92 at .

Similarly and with reference to fig. 3, the second aircraft frame 180 comprises a second aluminum parallelepiped frame 183 defining second cells 184 and 185 for housing second electronic modules 181 and 182. The second airframe 180 includes a second power and communications unit 170 that connects second electronic modules 181 and 182 to the power and communications/ control networks 71 and 72 of the aircraft 1. The second electronic modules 181 and 182 are held in place in the second units 184 and 185 using second bronze spring blades 183.1 integrated with the second frame 183. A third coil 186 made of a bent aluminum pipe 187 is welded to a second plate 188 for closing the upper portion of the second frame 183. The second plate 188 is also welded to the second frame 183. The third coil 186 includes fifth and sixth flat flanges 189 and 190 which are respectively placed on the second inlet pipe 191 and the second outlet pipe 92 of the third coil 186. Fifth and sixth flat flanges 189 and 190 are connected to third and fourth homologous flanges 115 and 116, respectively, for connection to closed circuit 10. The third flange 115 is integrated with a filling tap 117 of the third glycol water 11 of the closed circuit 10 and the fourth flange 116 is integrated with a fourth outlet return tap 118 of the glycol water 11 of the closed circuit 10. The second inlet line 191 includes a second wet rotor circulator 193 connected to the second power supply and communication unit 170. A third fan 194, which is also connected to the second power supply and communication unit 170, is arranged to force air over the third coil 186 to flow. The second airframe 180 also includes a second resistive internal temperature sensor 195 connected to the second power and communications unit 170.

The third coil 186 creates, with the second frame 183 of the second airframe 180, the second heat exchanger 150, the cold circuit 151 (made up of the third coil 186) of the second heat exchanger 150 being connected to the closed circuit 10 the third coil 186 is thermally connected to the second frame 183 which is the heat source 152 of the second heat exchanger 150 and exchanges heat primarily by conduction with the second electronic modules 181 and 182, thus, at an inlet temperature T₁₉₁The glycol water 11 entering the second inlet pipe 191 of the third coil 186 cools the second frame 183 by conduction and at a temperature higher than the inlet temperature T₁₉₁Outlet temperature T of₁₉₂Exits the third coil 186 through a second outlet tube 192.

The th coil 24 creates, together with the exhaust opening 30 of the nacelle 31, a third heat exchanger 60, the thermal circuit 61 (consisting of the th coil 24) of the third heat exchanger 60 being connected to the closed circuit 10. the th coil 24 is thermally connected to the exhaust opening 30 as a heat sink 62 of the third heat exchanger 60 and exchanges heat by conduction with the exhaust opening 30. in this way, at the inlet temperature T₂₂The glycol water 11 entering the coil 24 at is cooled by convective exchange with the air flow 33 from the vent 30 and is below the inlet temperature T₂₂Outlet temperature T of₂₃Leaving the th coil 24.

With reference to fig. 4 and 5, the circulation pump 12 comprises a metal turbine 2, which metal turbine 2 is rotatably mounted in a cylindrical housing 3 of a frame 4 of the circulation pump 12. The outer periphery 3.1 of the housing 3 comprises stator windings 5, which stator windings 5 remotely surround the outer edge 2.1 of the turbine 2. An inlet 6 and an outlet 7 for glycol water 11 provided in the frame 4 enter the housing 3. The inlet 6 being at the axis of rotation O of the turbine 2₂Which opens near the outer edge 2.1 of the turbine 2, and the outlet 7 opens near the outer edge 2.1, like the three-phase asynchronous machine , the turbine 2 is driven in rotation by means of the rotating magnetic field generated by the stator windings 5, the turbine 2 is the rotor of the asynchronous machine and acts as an armature for the short circuit.

In operation, the control unit 40 controls the activation of the circulation pump 12, the th and second power and communication units 70 and 170 maintain the th and second circulators 93 and 193 and the second fans 94 and 194 off, respectively, and monitor the temperature within the th and second aircraft racks 80 and 180 using the th and second temperature sensors 95 and 195, respectively, the heat generated by the th modules 81 and 82 during their operation is transferred to the th frame 83 in the following pattern:

radiation from the th modules 81 and 82 to the th frame 83 and in particular the th plate 88;

convection from th modules 81 and 82 and from air contained in th rack 80, then convection between air contained in th rack 80 and th frame 83 (and in particular th plate 88);

conduction between the th modules 81 and 82 and the th frame 83 through spring blades 83.1.

This heat is then transferred by conduction to the second coil 86, which second coil 86 transfers it by convection to the flow of glycol water 11 circulating in the circuit 10 by the circulation pump 12. the glycol water flow 11 is cooled as it passes through the th coil 24 by convective exchange between the th coil 24 and the air flow 33 from the exhaust 30. the cooled glycol water 11 is then returned to the aircraft frame 80. the same heat exchange takes place between the second modules 181 and 182, the second aircraft frame 180 and the closed circuit 10.

Glycol water temperature sensors 11 may be added at various points in the closed circuit 10 and connected to the control unit 40 to control the operation of the circulation pump 12 and/or the operation of the fan 32.

In the event of a failure of the circulation pump 12, the heating of the interior of the th aircraft rack 80 is measured by the th temperature sensor 95 and detected by the th power and communication unit 70, which then controls the activation of the th circulator 93 or even the second fan 94, in the event of a failure of the circulation pump 12, the second rack 180 operates in the same manner.

In the event of a failure of the nacelle ventilation 31, the control unit 40 activates the th fan 32 to ensure circulation of air around the th coil 24.

The invention is of course not limited to the described embodiments, but covers any alternatives within the scope of the invention as defined in the claims.

More specifically:

although the cooling device here cools the th and second airframes, the invention is also applicable to cooling devices for cooling one or more airframes, which may be grouped or distributed at points on board the aircraft;

although the aircraft rack here accommodates two electronic modules, the invention is also applicable to aircraft racks accommodating a different number of electronic modules (such as a single module or more than two modules);

although the closed circuit here contains glycol water, the invention is also applicable to other types of heat transfer fluids, such as distilled water or mineral or synthetic oils;

although the closed circuit here is made of aluminium tubes, the invention is also applicable to other types of tubes, such as copper, galvanized steel or synthetic material tubes. The use of flexible hoses makes the wiring of the closed circuit easier;

although the apparatus herein comprises a circulation pump, the invention is also applicable to other types of devices for circulating a heat transfer fluid in a closed circuit, such as line pumps, piston pumps or peristaltic pumps;

although the closed circuit here is connected to the th and second coils, the invention is also applicable to other types of heat exchangers, such as plate heat exchangers, tube heat exchangers, spiral heat exchangers or finned heat exchangers;

although here the th coil is placed opposite the air outlet of the air-conditioned passenger compartment, the invention is also applicable to other types of ventilated passenger compartments, such as cockpit, luggage, air-conditioned or non-air-conditioned passenger compartments;

although here the th and second heat exchangers comprise th and second fans, respectively, the invention is also applicable to other types of devices for forced air flow, such as vacuum cleaners, or even to cooling apparatuses of such devices which do not have a forced air flow;

although the aircraft frame here is a parallelepiped made of aluminium, the invention is also applicable to other types of aircraft frame, such as different shapes, or other heat-or non-heat-conducting materials (such as copper, steel or composite materials), possibly in heat exchange with the second exchanger, for example by convection with the forced air flow in the frame, and not by conduction;

although the module is here held in the aircraft frame by bronze spring blades, the invention is also applicable to other means of connecting the module to the frame, which may or may not be thermally conductive, such as metal clips or pressure pads;

although the housing here comprises a resistive internal temperature sensor, the invention is also applicable to other devices for temperature monitoring, such as thermocouples or infrared sensors;

although here the second coil is welded to the aircraft frame, the invention is applicable to other means of connecting the second coil to the aircraft frame, such as snapping, bolting, gluing;

although here the th and second coils are connected to the closed circuit by flanges, the invention is also applicable to other types of means for connecting to the closed circuit of a fluid, such as welding, brazing, screwing, pressing or gluing.

The claims (modification according to treaty clause 19)

A device (100) for cooling at least electronic modules (81,82) placed in an aircraft frame (80) of an aircraft (1), the aircraft comprising a ventilated cabin (31), the cooling device (1) comprising:

a closed circuit (10) for circulating a heat transfer fluid (11);

th means for circulating the heat transfer fluid (12) in the closed circuit (10);

-th heat exchanger (50) comprising a cold circuit (51), said cold circuit (51) being provided with -th devices (89, 90) for connection to the closed circuit (10) for circulating a heat transfer fluid (11) and being thermally connected with a heat source of the aircraft frame (80);

the second heat exchanger (60) comprises a hot circuit (61) provided with second means (20, 21) for connection to the closed circuit (10) for circulating a heat transfer fluid (11), and a cold circuit (62) thermally connected to an exhaust (30) from the ventilation chamber (31).

2. The cooling apparatus (100) of claim 1, wherein the -th heat exchanger (50) includes -th means for forced air flow (94).

3. A cooling apparatus (100) as claimed in any of the preceding claims, characterized in that the second heat exchanger (60) comprises second means for forced air flow (32).

4., the cooling device (100) of claim 2 or 3, characterized in that the and/or second means for forcing air flow comprise fans (32, 94).

5. The cooling apparatus (100) according to any of the preceding claims, wherein the th heat exchanger (50) comprises second means (93) for circulating the heat transfer fluid (11) in the closed circuit (10).

6. A cooling device (100) according to claim 3, characterized by comprising means for controlling and supplying (40) said -th means for forced air flow.

7. The cooling apparatus (100) according to any , wherein the device for circulating (12) the heat transfer fluid (11) comprises a turbine (12) the rotor (2) of which acts as an armature for the short circuit.

8, method for cooling an electronic module (81,82) of an airframe (80) of an aircraft (1), comprising a step of transferring heat from the electronic module (81,82) to a closed circuit (10) for circulating a heat transfer fluid (11), and a second step of removing heat from the heat transfer fluid (11) to an air flow drawn through an air outlet of a ventilated cabin (31) of the aircraft (1).

9, aircraft (1) comprising a cooling device (100) according to any of claims 1 to 7, .