CN118205714A - A heat exchange circuit and heat exchange system for hybrid aircraft - Google Patents

Abstract

The present application provides a hybrid aircraft heat exchange circuit and heat exchange system, which relates to the field of aircraft thermal management technology, and is used to transfer cold to the required heat dissipation equipment to achieve equipment heat dissipation and ensure the stable and safe operation of aircraft system equipment. The heat exchange circuit includes: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a common mixed liquid heat exchanger; the cold side flow path is composed of a wing oil tank, a first electric drive pump, an oil collecting tank, a mixed liquid heat exchanger, and an engine connected in sequence; the hot side flow path is composed of a lubricating oil tank, a second electric drive pump, a mixed liquid heat exchanger, and a generator connected in sequence; wherein the cold side flow path is used to realize the circulation of fuel in the wing oil tank through the drive of the first electric drive pump, and the hot side flow path is used to realize the circulation of lubricating oil in the lubricating oil tank through the drive of the second electric drive pump.

Description

A heat exchange circuit and heat exchange system for hybrid aircraft

Technical Field

The present application relates to the technical field of aircraft thermal management, and in particular to a heat exchange circuit and a heat exchange system for a hybrid aircraft.

Background technique

With the development of hybrid technology for civil aircraft, the heat generation power of the whole aircraft under the hybrid architecture has increased significantly. Therefore, it is necessary to develop a comprehensive thermal management system suitable for hybrid aircraft and find new heat sinks to meet the heat dissipation needs of the aircraft. Currently, the available heat sinks on civil aircraft are mainly ram air. Fuel itself has a large thermal capacity reserve and can be used as one of the heat sinks for heat dissipation, and it will hardly cause fuel compensation loss to the aircraft. Therefore, it is necessary to reasonably use ram air, fuel and other heat sinks to design a thermal management system for hybrid aircraft.

In the field of military aircraft, there are some thermal management systems or methods for using engine fuel as a heat sink, using technical solutions or structures of gas-liquid heat exchangers and gas-gas heat exchangers. However, at present, there is little research on thermal management technology for hybrid aircraft in China. With the development of domestic hybrid aircraft related technologies, a large number of thermal equipment need to dissipate heat, so it is necessary to reasonably utilize the available heat sinks of the aircraft and design a suitable thermal management system.

Summary of the invention

The embodiments of the present application provide a hybrid aircraft heat exchange circuit and a heat exchange system for transmitting cold energy to a required heat dissipation device, thereby achieving equipment heat dissipation and ensuring stable and safe operation of aircraft system equipment.

An embodiment of the present invention provides a hybrid aircraft heat exchange circuit, the heat exchange circuit comprising: a cold side flow path and a hot side flow path, the cold side flow path and the hot side flow path are connected via a shared mixed liquid heat exchanger;

The cold side flow route is composed of a wing oil tank, a first electric drive pump, an oil collecting tank, a mixed liquid heat exchanger, and an engine connected in sequence; the hot side flow route is composed of a first oil tank, a second electric drive pump, a mixed liquid heat exchanger, and a generator connected in sequence;

The cold side flow path is used to realize the circulation of fuel in the wing oil tank by driving the first electrically driven pump, and the hot side flow path is used to realize the circulation of lubricating oil in the oil tank by driving the second electrically driven pump.

An embodiment of the present invention provides a hybrid aircraft heat exchange system, the heat exchange system comprising a first heat exchange circuit, a second heat exchange circuit and the hybrid aircraft heat exchange circuit described above;

The first heat exchange circuit is connected through a wing oil tank in the heat exchange circuit of the hybrid aircraft, and the second heat exchange circuit is connected through an oil storage tank in the first heat exchange circuit.

The present invention provides a hybrid aircraft heat exchange circuit, which includes: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a common mixed liquid heat exchanger; the cold side flow path is composed of a wing oil tank, a first electric drive pump, an oil collecting tank, a mixed liquid heat exchanger, and an engine connected in sequence; the hot side flow path is composed of a lubricating oil tank, a second electric drive pump, a mixed liquid heat exchanger, and a generator connected in sequence; wherein the cold side flow path is used to realize the circulation of fuel in the wing oil tank through the drive of the first electric drive pump, and the hot side flow path is used to realize the circulation of lubricating oil in the lubricating oil tank through the drive of the second electric drive pump. The generator of the present application uses lubricating oil as a heat dissipation medium, and at the same time extracts the coldness of the engine oil, fully utilizing the fuel and lubricating oil heat sink to dissipate heat from the heat load equipment, realizes equipment heat dissipation and ensures the stable and safe operation of the aircraft system equipment.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a structural diagram of a heat exchange circuit of a hybrid aircraft provided by the present application;

FIG2 is a control architecture diagram provided by the present application;

FIG3 is a structural diagram of a hybrid aircraft heat exchange system provided by the present application;

FIG4 is a structural diagram of a first heat exchange circuit provided by the present application;

FIG5 is a structural diagram of a second heat exchange circuit provided in the present application.

Detailed ways

In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

Please refer to FIG1 , which shows a hybrid aircraft heat exchange circuit provided by an embodiment of the present invention, wherein the heat exchange circuit comprises: a cold side flow path (100) and a hot side flow path (200); the cold side flow path (100) and the hot side flow path (200) are connected via a common mixed liquid heat exchanger (15);

The cold side flow path (100) is composed of a wing oil tank (1), a first electrically driven pump (10), an oil collecting tank (11), a mixed liquid heat exchanger (15), and an engine (18) connected in sequence; the hot side flow path (200) is composed of a lubricating oil tank (25), a second electrically driven pump (26), a mixed liquid heat exchanger (15), and a generator (21) connected in sequence; wherein the cold side flow path (100) is used to realize the circulation of fuel in the wing oil tank (1) by driving the first electrically driven pump (10), and the hot side flow path (200) is used to realize the circulation of lubricating oil in the lubricating oil tank (25) by driving the second electrically driven pump (26).

In one embodiment provided in the present application, the cold side fluid in the cold side flow path (100) where the mixed liquid heat exchanger (15) is located is the fuel flowing into the wing tank (1). After the first electrically driven pump (10) delivers the fuel from the wing tank (1) to the oil collecting tank (11), the fuel flows into the cold side flow path in the mixed liquid heat exchanger (15) and supplies fuel to the engine (18) after heat exchange.

A first temperature sensor (12) and a first pressure sensor (13) are arranged between the oil collecting tank (11) and the mixed liquid heat exchanger (15); a second temperature sensor (17) and a second pressure sensor (16) are arranged between the mixed liquid heat exchanger (15) and the engine; the first temperature sensor (12) and the second temperature sensor (17) are used to respectively measure the fuel temperature of the fuel entering and exiting the mixed liquid heat exchanger (15); and the first pressure sensor (13) and the second pressure sensor (16) are used to respectively measure the fuel pressure of the fuel entering and exiting the mixed liquid heat exchanger (15).

In one embodiment provided in the present application, the hot side fluid in the hot side flow path (200) where the mixed liquid heat exchanger (15) is located is the lubricating oil in the lubricating oil tank (25), and the second electric drive pump drives (26) the lubricating oil to flow in the hot side flow path of the mixed liquid heat exchanger (15), and after heat exchange, it flows into the generator (21) to dissipate heat, and then flows back into the lubricating oil tank (25) after passing through the one-way valve (24).

A temperature sensor (29) and a pressure sensor (28) are provided between the second electric drive pump (26) and the mixed liquid heat exchanger (15), a temperature sensor (19) and a pressure sensor (20) are provided between the mixed liquid heat exchanger (15) and the generator (21), and a temperature sensor (22) and a pressure sensor (23) are provided between the generator (21) and the lubricating oil tank (25). The temperature sensors (29, 19) respectively measure the inlet and outlet temperatures of the hot side flow channel of the fuel/lubricating oil heat exchanger (15); the pressure sensors (28, 20) respectively measure the inlet and outlet pressures of the hot side flow channel of the fuel/lubricating oil heat exchanger (15); the temperature sensor (22), the pressure sensor (23), and the flow sensor (27) respectively measure the lubricating oil temperature, pressure, and circuit flow after the generator (21).

A first mass flow sensor (14) and a second mass flow sensor (27) are respectively provided in the cold edge flow path (100) and the hot edge flow path (200); the first mass flow sensor (14) is used to measure the mass flow of the fuel in the cold edge flow path (100), and the second mass flow sensor (27) is used to measure the mass flow of the lubricating oil in the hot edge flow path (200).

In an optional embodiment provided by the present application, the heat exchange circuit in this embodiment further includes: a thermal management controller. As shown in FIG2 , a control architecture diagram provided by this embodiment, the thermal management controller in this embodiment is used to obtain sensor data transmitted by a temperature sensor, a pressure sensor, and a mass flow sensor, and control the first electrically driven pump (10) and the second electrically driven pump (26) according to the sensor data.

As shown in FIG1 , the heat exchange circuit uses the heat sink of the fuel supplied by the engine (18) to provide heat dissipation for the generator (21), thereby realizing the extraction of the heat sink of the fuel supplied by the engine (18) and improving the utilization efficiency of the fuel heat sink. After the first electric drive pump (10) drives the fuel into the oil collecting tank (11), the fuel cooling capacity is transferred to the cooling circuit of the generator (21) through the mixed liquid heat exchanger (15). The temperature sensor (17) monitors the real-time temperature T ₁₇ of the fuel supply of the engine (18), and the thermal management controller (80) always controls the second electric drive pump (26) to make T _{engine fuel supply} - T ₁₇ <3°C, so as to prevent the fuel supply temperature of the engine (18) from exceeding the limit and ensure the safe and stable operation of the engine (18). The pressure sensors (13, 16) measure the real-time pressure and flow resistance of the fuel circuit of the fuel/lubricating oil heat exchanger (15), and the flow sensor (14) measures the real-time flow rate of the fuel supply; the pressure sensors (28, 20) measure the real-time pressure and flow resistance of the lubricating oil circuit of the fuel/lubricating oil heat exchanger (15), and the flow sensor (27) is used to measure the real-time circulation flow rate of the lubricating oil. The temperature sensor (19) measures the inlet lubricating oil temperature _T19 of the heat generating device generator (21). When the value of _T19 increases or decreases, the thermal management controller (80) adjusts the operating power of the electric drive pump (26) to adjust the flow rate in the lubricating oil circuit. All sensor data are uploaded to the thermal management controller (80) in real time for adjusting the electric drive pump (10, 26) and monitoring the pipeline pressure, flow rate, and temperature.

The present embodiment provides a hybrid aircraft heat exchange circuit, which includes: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a common mixed liquid heat exchanger; the cold side flow path is composed of a wing oil tank, a first electric drive pump, an oil collecting tank, a mixed liquid heat exchanger, and an engine connected in sequence; the hot side flow path is composed of a lubricating oil tank, a second electric drive pump, a mixed liquid heat exchanger, and a generator connected in sequence; wherein the cold side flow path is used to realize the circulation of fuel in the wing oil tank through the drive of the first electric drive pump, and the hot side flow path is used to realize the circulation of lubricating oil in the lubricating oil tank through the drive of the second electric drive pump. The generator of the present application uses lubricating oil as a heat dissipation medium, and at the same time extracts the coldness of the engine oil, making full use of the fuel and lubricating oil heat sink to dissipate heat from the heat load equipment, realizing equipment heat dissipation and ensuring the stable and safe operation of the aircraft system equipment.

Please refer to FIG3 , which is a hybrid aircraft heat exchange system provided by an embodiment of the present invention, wherein the heat exchange system comprises a first heat exchange loop A, a second heat exchange loop C and the hybrid aircraft heat exchange loop B described above; the first heat exchange loop A is connected via the wing oil tank (1) in the hybrid aircraft heat exchange loop B, and the second heat exchange loop C is connected via the oil storage tank (31) in the first heat exchange loop A. The second heat exchange loop C and the first heat exchange loop A share a liquid storage tank (31), thereby achieving sharing of the cooling capacity of the ram air heat sink and the cooling capacity of the wing oil tank fuel heat sink, achieving the use of the ram air heat sink to dissipate heat when the equipment in the hybrid aircraft heat exchange loop A cannot use the wing oil tank fuel heat sink, thereby improving the heat dissipation redundancy of the thermal management system.

Please refer to FIG. 3 and FIG. 4 , which are a first heat exchange circuit provided in an embodiment of the present invention, wherein the first heat exchange circuit comprises a cold side flow path (100) and a hot side flow path (200), wherein the cold side flow path (100) and the hot side flow path (200) are connected via a common mixed liquid heat exchanger (6). The mixed liquid heat exchanger (6) is a fuel oil/propylene glycol water mixed liquid heat exchanger.

The cold side flow path (100) is composed of the mixed liquid heat exchanger (6), the wing fuel tank (1) and the first electric drive pump (2) connected in sequence end to end; the hot side flow path (200) is composed of the mixed liquid heat exchanger (6), the liquid storage tank (31), the second electric drive pump (32), the DC/DC converter (36) and the propulsion motor controller (39) connected in sequence end to end; the cold side flow path (100) realizes cold side fuel circulation by driving the first electric drive pump (2), and the hot side flow path (200) realizes hot side fuel circulation by driving the second electric drive pump (32).

In one embodiment provided in the present application, the cold side fluid in the cold side flow path (100) where the mixed liquid heat exchanger (6) is located is the fuel flowing out of the wing fuel tank (1). The fuel is driven by the first electric drive pump (2) to flow into the cold side flow path of the mixed liquid heat exchanger (6), and then flows back into the wing fuel tank (1) through the cold side flow path, thereby completing a round of cold side fuel circulation.

Wherein, a first temperature sensor (3) and a first pressure sensor (4) are arranged between the first electric drive pump (2) and the mixed liquid heat exchanger (6) in the cold edge flow path (100), and a second temperature sensor (8) and a second pressure sensor (7) are arranged between the mixed liquid heat exchanger (6) and the wing fuel tank (1) in the cold edge flow path (100); the first temperature sensor (3) and the second temperature sensor (8) are used to respectively measure the fuel temperature of the fuel entering and exiting the cold edge flow path, and the first pressure sensor (4) and the second pressure sensor (7) are used to respectively measure the fuel pressure of the fuel entering and exiting the cold edge flow path. A first mass flow sensor (5) is arranged in the cold edge flow path (100), and the first mass flow sensor (5) is used to measure the mass flow of the fuel in the cold edge flow path (100).

As shown in FIG4 , the cold side fluid in the heat exchange circuit of the fuel/propylene glycol water mixture heat exchanger (6) is the fuel flowing out of the wing tank (1). The fuel is driven by the first electric drive pump (2) to continuously flow into the cold side flow channel of the fuel/propylene glycol water mixture heat exchanger (6), flows through the cold side flow channel through the one-way valve (9) and then flows back into the wing tank (1), thus completing a round of cold side fuel circulation. The temperature sensors (3, 8) in the cold side flow channel respectively measure the fuel temperatures at the inlet and outlet of the cold side flow channel, the pressure sensors (4, 7) respectively measure the fuel pressures at the inlet and outlet of the cold side flow channel, and the mass flow sensor (5) measures the mass flow of the fuel in the cold side flow channel of the heat exchange circuit 1.

In one embodiment provided by the present application, the hot side fluid in the hot side flow path (200) where the mixed liquid heat exchanger (6) is located is the mixed liquid flowing out of the liquid storage tank (31), and the mixed liquid is driven by the second electric drive pump (32) to flow into the DC/DC converter (36), and then flows into the hot side flow path of the mixed liquid heat exchanger (6) after passing through the propulsion motor controller (39), and finally flows back into the liquid storage tank (31), thus completing a round of hot side fuel circulation. A second mass flow sensor (33) is provided in the hot side flow path (200), and the second mass flow sensor (33) is used to measure the mass flow of the fuel in the hot side flow path (200).

Wherein, a first temperature sensor (35) and a first pressure sensor (34) are provided between the second electric drive pump (32) and the DC/DC converter (36) in the hot edge flow path (200), and are used to respectively measure the temperature and pressure of the mixed liquid before the mixed liquid flows into the DC/DC converter; a second temperature sensor (38) and a second pressure sensor (37) are provided between the DC/DC converter (36) and the propulsion motor controller (39) in the hot edge flow path (200), and are used to respectively measure the temperature and pressure of the mixed liquid before the mixed liquid flows into the propulsion motor controller (39). a third temperature sensor (41) and a third pressure sensor (40) are provided between the propulsion motor controller (39) and the mixed liquid heat exchanger (6) in the hot edge flow path (200), for respectively measuring the mixed liquid temperature and the mixed liquid pressure before the mixed liquid flows into the mixed liquid heat exchanger (6); a fourth temperature sensor (76) and a fourth pressure sensor (77) are provided between the mixed liquid heat exchanger (6) and the liquid storage tank (31) in the hot edge flow path (200), for respectively measuring the mixed liquid temperature and the mixed liquid pressure after the mixed liquid flows out of the mixed liquid heat exchanger (6).

As shown in FIG. 4 , the hot side fluid in the heat exchange circuit of the fuel/propylene glycol water mixture heat exchanger (6) is a propylene glycol water mixture (volume ratio 4 to 6) flowing out of the liquid storage tank (31). The mixture is driven by an electric drive pump (32) to flow into the DC/DC converter (36), and then flows into the hot side flow channel of the fuel/propylene glycol water mixture heat exchanger (6) after passing through a propulsion motor controller (39). Finally, it flows back into the liquid storage tank (31) after passing through a one-way valve (30). The temperature sensors (35, 38, 41, 76) in the hot side flow channel respectively measure the temperature before and after the DC/DC converter (36). The temperature of the mixed liquid before entering the motor controller (39), before the hot side flow channel inlet of the fuel/propylene glycol water mixed liquid heat exchanger (6), and at the hot side flow channel outlet of the fuel/propylene glycol water mixed liquid heat exchanger (6); the pressure sensors (34, 37, 40, 77) respectively measure the mixed liquid pressure before the DC/DC converter (36), before the propulsion motor controller (39), before the hot side flow channel inlet of the fuel/propylene glycol water mixed liquid heat exchanger (6), and at the hot side flow channel outlet of the fuel/propylene glycol water mixed liquid heat exchanger (6); and the mass flow sensor (33) measures the mass flow rate of the mixed liquid in the hot side flow channel.

In an optional embodiment provided by the present application, the first heat exchange circuit in this embodiment further includes: a thermal management controller. As shown in FIG2 , a control architecture diagram provided by this embodiment, the thermal management controller in this embodiment is used to obtain sensor data transmitted by a temperature sensor, a pressure sensor, and a mass flow sensor, and control the driving of the first electrically driven pump (2) and the second electrically driven pump (32) in FIG4 according to the sensor data.

As shown in FIG4 , a loop is added to the wing tank (1), and the fuel is continuously flowed through the heat exchanger (6) by the first electric drive pump (2), and the cold of the fuel in the wing tank (1) is continuously transmitted to the cooling circuit of the propulsion motor controller (39). When the temperature T ₈ of the temperature sensor (8) exceeds the maximum limit temperature T _wingfuel of the wing tank fuel, the first electric drive pump (2) automatically stops running to prevent the wing fuel from overheating; the second electric drive pump (32) makes the coolant in the liquid storage tank (31) flow continuously and dissipates heat for the heating device. The temperature sensors (35, 38, 41, 76) continuously monitor the real-time operating temperature and upload it to the thermal management controller (80), and dynamically adjust according to the actual heating power of the propulsion motor controller (39) and the DC/DC converter (36) in the loop. When the actual heating power of the propulsion motor controller (39) and the DC/DC converter (36) increases or decreases, the temperature sensors (38, 41) respectively send the temperature data T ₃₈ , T 76 to the thermal management controller (80). _{The temperature T 41} is transmitted to the thermal management controller (80), and the thermal management controller (80) increases or decreases the operating power of the second electric drive pump (32) according to the temperature values of T ₃₈ and T ₄₁ , so as to adjust the flow rate of the liquid storage tank (31) circuit in the heat exchange circuit.

In the heat exchange circuit, the pressure sensors (4, 7) are used to monitor the flow resistance loss and the real-time pressure value in the fuel circuit of the fuel/propylene glycol heat exchanger (6). The real-time pressure value will be transmitted to the thermal management controller (80) for monitoring. When the pressure value of the pressure sensor (7) exceeds the maximum oil pressure limit P _fuel , the power of the electric drive pump (32) is adjusted to reduce the pressure to below the oil pressure limit to ensure the safety of the circuit pressure. The flow sensor (5) monitors the real-time flow in the fuel circuit of the fuel/propylene glycol heat exchanger (6), transmits the data to the thermal management controller (80), and is used for flow regulation of the electric drive pump (2).

The embodiment of the present invention provides a first heat exchange circuit, which includes: a cold side flow path and a hot side flow path, wherein the cold side flow path and the hot side flow path are connected through a common mixed liquid heat exchanger. The cold side flow path is composed of the mixed liquid heat exchanger, the wing oil tank and the first electric drive pump connected end to end in sequence; the hot side flow path is composed of the mixed liquid heat exchanger, the liquid storage tank, the second electric drive pump, the DC/DC converter and the propulsion motor controller connected end to end in sequence; wherein the cold side flow path realizes cold side fuel circulation through the drive of the first electric drive pump, and the hot side flow path realizes hot side fuel circulation through the drive of the second electric drive pump. Through this application, the low-temperature fuel cooling capacity in the wing oil tank is utilized to dissipate heat from the DC/DC converter and the propulsion motor controller through the mixed liquid heat exchanger, and a large amount of fuel heat sink cooling capacity in the wing oil tank is fully utilized to achieve equipment heat dissipation and ensure the stable and safe operation of aircraft system equipment.

Please refer to FIG. 3 and FIG. 5 , which are a second heat exchange circuit provided by an embodiment of the present invention, a cold side flow path 100 and a hot side flow path (200), wherein the cold side flow path (100) and the hot side flow path (200) are connected via a common mixed liquid heat exchanger (42). The mixed liquid heat exchanger (42) is a ram air/propylene glycol heat exchanger.

In this embodiment, the cold side flow path (100) is composed of a ram air inlet (69), the mixed liquid heat exchanger (42), and a ram air outlet (76) connected in sequence; the hot side flow path (200) is composed of the mixed liquid heat exchanger (42), the heat exchange branch (300), and the liquid storage tank (31) connected in sequence end to end; wherein the cold side flow path (100) is used to realize the circulation of the ram air, and the hot side flow path (200) is used to realize the circulation of the mixed liquid flowing out of the liquid storage tank by driving the electric drive pump (44, 53, 61) in the heat exchange branch (300).

In an optional embodiment provided in the present application, the cold side fluid in the cold side flow path (100) where the mixed liquid heat exchanger (42) is located is the ram air flowing into the ram air inlet (69), and the ram air flows through the cold side flow path of the mixed liquid heat exchanger (42) and is discharged outside the machine through the ram air outlet (75).

Specifically, a first temperature sensor (70) and a first pressure sensor (71) are provided between the ram air inlet (36) in the cold side flow path (100) and the mixed liquid heat exchanger (42); a second temperature sensor (72), a second pressure sensor (73), and a mass flow sensor (74) are provided between the mixed liquid heat exchanger (42) and the ram air outlet (75). The first temperature sensor (70) and the first pressure sensor (71) are used to respectively measure the gas temperature and gas pressure before the ram air enters the mixed liquid heat exchanger; the second temperature sensor (72), the second pressure sensor (73), and the mass flow sensor (74) are used to respectively measure the gas temperature, gas pressure, and gas mass flow after the ram air enters the mixed liquid heat exchanger.

In an optional embodiment provided by the present application, the heat exchange branch includes three parallel sub-heat exchange branches, each of which includes an electric drive pump (44, 53, 61) and a heat load device connected in sequence. The heat load device is: a lithium battery (47), a rectifier (48), a fuel cell (56), and a propulsion motor (64).

The hot side fluid in the hot side flow path (200) where the mixed liquid heat exchanger (42) is located is a mixed liquid (the mixed liquid is a propylene glycol-water mixed liquid, with a volume ratio of 4 to 6) flowing out of the liquid storage tank (31). After the mixed liquid flows through the hot side flow path of the mixed liquid heat exchanger (42), it is respectively divided into each sub-heat exchange branch after passing through a one-way valve (43); the electrically driven pump (44, 53, 61) is used to adjust the mixed liquid flow rate in the corresponding sub-heat exchange branch.

Specifically, a temperature sensor and a pressure sensor are provided before and after the heat load device of each sub-heat exchange branch (300), and are used to respectively measure the mixed liquid temperature and the mixed liquid pressure respectively before and after the mixed liquid flows to each sub-heat exchange branch; a mass flow sensor and a one-way valve are also provided after the heat load device of each sub-heat exchange branch (300); the mass flow sensor is used to measure the mixed liquid mass flow rate of the mixed liquid flowing to each sub-heat exchange branch; and the one-way valve is used to prevent the mixed liquid of each branch from flowing back.

As shown in FIG5 , the hot side fluid in the hot side flow path of the ram air/propylene glycol water mixed liquid heat exchanger (42) is the propylene glycol water mixed liquid flowing out of the liquid storage tank (31). The mixed liquid flows through the hot side flow path of the ram air/propylene glycol water mixed liquid heat exchanger (42) and then passes through the one-way valve (43) and is respectively divided into the sub-heat exchange branch where the lithium battery (47) and the rectifier (48) are located, the sub-heat exchange branch where the fuel cell (56) is located, and the sub-heat exchange branch where the propulsion motor (64) is located. The electric drive pumps (44, 53, 61) regulate the flow of the mixed liquid for the three branches respectively.

The temperature sensors (46, 51) respectively measure the temperature of the mixed liquid before the lithium battery (47) and after the rectifier (48) in the branch between the lithium battery (47) and the rectifier (48); the temperature sensors (55, 59) respectively measure the temperature of the mixed liquid before and after the fuel battery; the temperature sensors (63, 67) respectively measure the temperature of the mixed liquid before and after the propulsion motor (64); the temperature sensor (78) measures the temperature of the mixed liquid refluxed from the main circuit; the pressure sensors (45, 50) respectively measure the pressure of the mixed liquid before the lithium battery (47) and after the rectifier (48) in the branch between the lithium battery (47) and the rectifier (48); the mass flow sensors (49, 57, 65) respectively measure the mass flow of the mixed liquid in each branch; the one-way valves (52, 60, 68) prevent the mixed liquid in each branch from refluxing, and the pressure sensor (79) measures the pressure of the mixed liquid refluxed from the liquid storage tank.

In an optional embodiment provided by the present application, the second heat exchange circuit in this embodiment further includes: a thermal management controller. As shown in FIG2 , a control architecture diagram provided by this embodiment, the thermal management controller in this embodiment is used to obtain sensor data transmitted by a temperature sensor, a pressure sensor, and a mass flow sensor, and control the electric drive pump (44, 53, 61) in each sub-heat exchange branch according to the sensor data.

In the second heat exchange loop shown in FIG5 , the heat load device is in a hybrid form, and each sub-heat exchange branch has an electric drive pump (44, 53, 61), and the flow rate of the branch is controlled and monitored by flow sensors (49, 57, 65). The pressure sensors (45, 50) monitor the real-time node pressure of the rectifier and lithium battery circuits; the pressure sensors (54, 58) monitor the real-time node pressure of the fuel cell circuit; the pressure sensors (62, 66) monitor the real-time node pressure of the propulsion motor circuit; and the pressure sensor (79) monitors the propylene glycol pressure before the reflux of the liquid storage tank. Among them, the rectifier (48) and the lithium battery (47) are connected in series and share an electric drive pump (44).

The thermal management controller (80) increases or decreases the operating power of the electric drive pump (44, 53, 61) according to the real-time temperature values _T51 , _T59 , T67 of the temperature sensors (51, 59, 67) on the three sub-heat exchange branches of the lithium battery (47), the rectifier (48), the fuel cell (56), and the propulsion motor ( ₆₄ ), respectively, so as to adjust the flow of the three sub-heat exchange branches in the second heat exchange loop; the coolant in the liquid storage tank (31) is cooled by the ram air outside the aircraft through the heat exchanger (42) and then used to cool various devices. The liquid storage tank (31) is arranged after the heat-generating device, which greatly improves the temperature difference between the hot and cold side fluids of the heat exchanger (42), improves the heat exchange efficiency of the heat exchanger (42) and the heat dissipation performance of the heat-generating device in the heat exchange loop 2. The monitoring data of the temperature sensors (70, 72), the pressure sensors (71, 73) and the flow sensor (74) are not related to the regulation of the electric drive pump (44, 53, 61).

The embodiment of the present invention provides a second heat exchange circuit, which includes: a cold side flow path and a hot side flow path, the cold side flow path and the hot side flow path are connected through a common mixed liquid heat exchanger; the cold side flow path is composed of a ram air inlet, the mixed liquid heat exchanger, and a ram air outlet connected in sequence; the hot side flow path is composed of the mixed liquid heat exchanger, the heat exchange branch, and a liquid storage tank connected in sequence from beginning to end; wherein the cold side flow path is used to realize the circulation of ram air, and the hot side flow path is used to realize the circulation of the mixed liquid flowing out of the liquid storage tank through the drive of the electric drive pump in the heat exchange branch. The present application uses the ram air cooling capacity to cool the mixed liquid in the hot side flow path passing through the mixed liquid heat exchanger, thereby realizing heat dissipation of the heat load equipment, that is, for the heat load equipment contained in the heat exchange branch, the equipment heat dissipation is realized and the stable and safe operation of the aircraft system equipment is ensured.

The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims (10)

1. A hybrid aircraft heat exchange circuit, the heat exchange circuit comprising: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a shared mixed liquid heat exchanger;

The cold edge flow path consists of a wing oil tank, a first electric drive pump, an oil collecting tank, a mixed liquid heat exchanger and an engine which are connected in sequence; the hot side flow path consists of an oil tank, a second electric drive pump, a mixed liquid heat exchanger and a generator which are sequentially connected at first;

The cold side flow path is used for realizing the circulation of fuel oil in the wing fuel tank through the driving of the first electric driving pump, and the hot side flow path is used for realizing the circulation of the lubricant oil in the lubricant tank through the driving of the second electric driving pump.

2. The heat exchange circuit according to claim 1, wherein cold side fluid in a cold side flow path where the mixed liquor heat exchanger is located is fuel oil flowing into the wing fuel tank, and the first electrically driven pump sends the fuel oil of the wing fuel tank to the fuel collecting tank, and then flows into the cold side flow path in the mixed liquor heat exchanger, and supplies the fuel oil to the engine after heat exchange.

3. The heat exchange circuit according to claim 2, wherein a first temperature sensor and a first pressure sensor are arranged between the oil collecting tank and the mixed liquor heat exchanger; a second temperature sensor and a second pressure sensor are arranged in front of the mixed liquor heat exchanger and the engine;

the first temperature sensor and the second temperature sensor are used for respectively measuring the fuel temperature of the fuel entering and exiting the mixed liquor heat exchanger;

the first pressure sensor and the second pressure sensor are used for respectively measuring the fuel pressure of the fuel entering and exiting the mixed liquor heat exchanger.

4. The heat exchange circuit of claim 1, wherein the hot side fluid in the hot side flow path where the mixed liquor heat exchanger is located is the lubricating oil in the lubricating oil tank, and the second electrically driven pump drives the lubricating oil to flow in the hot side flow path of the mixed liquor heat exchanger, flow into the generator for heat dissipation after heat exchange, and flow back into the lubricating oil tank after passing through a one-way valve.

5. The heat exchange circuit of claim 4, wherein a temperature sensor and a pressure sensor are disposed between the second electrically driven pump and the mixed liquor heat exchanger, a temperature sensor and a pressure sensor are disposed between the mixed liquor heat exchanger and the generator, and a temperature sensor and a pressure sensor are disposed between the generator and the lubricating oil tank.

6. The heat exchange circuit according to claim 3 or 5, wherein a first mass flow sensor for measuring the mass flow of fuel in the cold side flow path and a second mass flow sensor for measuring the mass flow of oil in the hot side flow path are provided in the cold side flow path and the hot side flow path, respectively.

7. The heat exchange circuit of claim 6, further comprising: and the thermal management controller is used for acquiring sensor data transmitted by the temperature sensor, the pressure sensor and the mass flow sensor and controlling the first electric drive pump and the second electric drive pump according to the sensor data.

8. A hybrid aircraft heat exchange system, characterized in that it comprises a first heat exchange circuit, a second heat exchange circuit and a hybrid aircraft heat exchange circuit according to any one of claims 1 to 7;

The first heat exchange loop is connected through a wing oil tank in the hybrid power aircraft heat exchange loop, and the second heat exchange loop is connected through an oil storage tank in the first heat exchange loop.

9. The heat exchange system of claim 8, wherein the first heat exchange circuit comprises: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a shared mixed liquid heat exchanger;

The cold edge flow path consists of the mixed liquid heat exchanger, the wing oil tank and the first electric drive pump which are connected end to end in sequence; the hot side flow path consists of the mixed liquid heat exchanger, the liquid storage tank, the second electric drive pump, the DC/DC converter and the propulsion motor controller which are connected end to end in sequence;

The cold side flow path realizes cold side fuel circulation through the driving of the first electric driving pump, and the hot side flow path realizes hot side fuel circulation through the driving of the second electric driving pump.

10. The heat exchange system of claim 8, wherein the second heat exchange circuit comprises: a cold side flow path and a hot side flow path; the cold side flow path and the hot side flow path are connected through a shared mixed liquid heat exchanger;

the cold-side flow path consists of a ram air inlet, the mixed liquor heat exchanger and a ram air outlet which are connected in sequence; the hot side flow path consists of the mixed liquid heat exchanger, a heat exchange branch and a liquid storage tank which are sequentially connected end to end;

The cold side flow path is used for realizing the circulation of ram air, and the hot side flow path is used for realizing the circulation of mixed liquid flowing out of the liquid storage tank through the driving of the electrically driven pump in the heat exchange branch.