CN114364232B - Aircraft distributed pump-drive two-phase cooling system - Google Patents
Aircraft distributed pump-drive two-phase cooling system Download PDFInfo
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- CN114364232B CN114364232B CN202210097756.7A CN202210097756A CN114364232B CN 114364232 B CN114364232 B CN 114364232B CN 202210097756 A CN202210097756 A CN 202210097756A CN 114364232 B CN114364232 B CN 114364232B
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Abstract
The invention relates to a distributed pump-driven two-phase cooling system for an aircraft. The cooling system is characterized in that a liquid storage tank, a precooling device, a pump, a flowmeter, a preheater, a first valve group, a heat source group, a condensing device, a reheater and the liquid storage tank are sequentially connected, and a first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the precooling device and the pump, and the third sensor group is arranged between the preheater and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both arranged between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater and the liquid storage tank, and the controller is connected with the sensor group, the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device respectively. The invention can solve the problem of cooperative heat dissipation of airborne equipment.
Description
Technical Field
The invention relates to the technical field of aircraft environment control, in particular to an aircraft distributed pump drive two-phase cooling system.
Background
With the continuous improvement of the performance of the aircraft, the thermal load of airborne electronic equipment and high-energy equipment is rapidly increased, and the potential of a single-phase cooling technology adopting ram air cooling (air cooling) and anti-freezing liquid cooling (liquid cooling) is developed, so that the cooling requirement of the airborne equipment of the aircraft is difficult to meet. Therefore, a pump-driven two-phase cooling technology, which is a novel heat dissipation technology capable of matching with the ultrahigh heat load of the airborne equipment, needs to be developed, the technology utilizes the phase change of the flowing working medium to absorb and release a large amount of latent heat, the heat exchange capacity and the heat exchange coefficient are higher than those of the current air cooling and liquid cooling technologies by one order of magnitude, and the heat dissipation requirement of the airborne equipment can be met. However, besides the increasing heat load of the aircraft, the aircraft also has the situations of multiple onboard heating devices, constant change of device heat load and aircraft heat sink under different flight missions, and the like, which makes the cooperative heat dissipation of "large heat, multiple heat sources, variable load and variable heat sink" very difficult, so the problem of cooperative heat dissipation of the onboard devices cannot be solved by adopting the existing pump-driven two-phase system, and therefore, a pump-driven two-phase system with reasonable layout needs to be researched urgently.
Disclosure of Invention
The invention aims to provide a distributed pump-driven two-phase cooling system for an aircraft, which can solve the problem of cooperative heat dissipation of airborne equipment.
In order to achieve the purpose, the invention provides the following scheme:
an aircraft distributed pump drive two-phase cooling system comprising:
the system comprises a controller, a pump driving module, a working medium cooling module, a compensation module and a heat source cooling module;
the pump drive module includes: the device comprises a first sensor group, a second sensor group, a liquid storage tank, a flowmeter and a pump; the compensation module comprises: the system comprises a third sensor group, a fourth sensor group, a preheater and a reheater; the heat source cooling module includes: the system comprises a fifth sensor group, a sixth sensor group, a seventh sensor group, a first valve group and a heat source group; the working medium cooling module comprises: a condensing device and a precooling device;
the liquid storage tank, the pre-cooling device, the pump, the flowmeter, the pre-heater, the first valve group, the heat source group, the condensing device, the reheater and the liquid storage tank are sequentially connected, and the first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the pre-cooling device and the pump, and the third sensor group is arranged between the pre-heater and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both disposed between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater and the liquid storage tank, the controller is respectively connected with the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group, the seventh sensor group, the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device, and the controller is used for controlling the work of the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device according to data obtained by the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group and the seventh sensor group.
Optionally, the pre-cooling device includes: a precooler and a precooling cold source; the first inlet of the precooler is communicated with the outlet of the liquid storage tank, and the first outlet of the precooler is communicated with the inlet of the pump through a first pipeline; a second outlet of the precooler is communicated with an inlet of the precooling cold source; and the second inlet of the precooler is communicated with the outlet of the precooling cold source.
Optionally, the condensing device comprises a condenser and a condensation cold source; an outlet of the heat source group is communicated with a first inlet of the condenser through a third pipeline; a first outlet of the condenser is communicated with an inlet of the reheater; and a second inlet of the condenser is communicated with an outlet of the condensation cold source, and a second outlet of the condenser is communicated with an inlet of the condensation cold source.
Optionally, the heat source cooling module further comprises: a second valve group; the second valve set is disposed on the third conduit.
Optionally, the first sensor set includes: a first pressure sensor and a first temperature sensor; the second sensor group includes: a second pressure sensor and a second temperature sensor; the third sensor group comprises a third pressure sensor and a third temperature sensor; the fourth sensor group includes a tenth temperature sensor and a fifth pressure sensor.
Optionally, the first valve group comprises a first valve, a second valve and a third valve; the heat source group comprises a first heat source, a second heat source and a third heat source; the second valve group comprises a first one-way valve, a second one-way valve and a third one-way valve;
the inlet of the first valve, the inlet of the second valve and the inlet of the third valve are communicated with the outlet of the preheater; an outlet of the first valve is communicated with an inlet of the first heat source; the outlet of the first heat source is communicated with the inlet of the first one-way valve; an outlet of the second valve is communicated with an inlet of the second heat source, and an outlet of the second heat source is communicated with an inlet of the second one-way valve; an outlet of the third valve is communicated with an inlet of the third heat source, and an outlet of the third heat source is communicated with an inlet of the third one-way valve; and the outlet of the first one-way valve, the outlet of the second one-way valve and the outlet of the third one-way valve are communicated with the inlet of the condensing device.
Optionally, the fifth sensor group includes: a fourth temperature sensor, a fifth temperature sensor and a sixth temperature sensor; the fourth temperature sensor is arranged on the first heat source, and the fifth temperature sensor is arranged on the second heat source; the sixth temperature sensor is disposed on the third heat source.
Optionally, the sixth sensor group includes: a seventh temperature sensor, an eighth temperature sensor, and a ninth temperature sensor; the seventh temperature sensor is arranged between the first heat source and the first one-way valve, and the eighth temperature sensor is arranged between the second heat source and the second one-way valve; the ninth temperature sensor is disposed between the third heat source and the third check valve.
Optionally, the seventh sensor group is: a fourth pressure sensor; the fourth pressure sensor is arranged between the outlet of the first one-way valve, the outlet of the second one-way valve and the outlet of the third one-way valve and the inlet of the condensing device.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the invention relates to a liquid storage tank, a precooling device, a pump, a flowmeter, a preheater, a first valve group, a heat source group, a condensing device, a reheater and the liquid storage tank which are connected in sequence, wherein a first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the precooling device and the pump, and the third sensor group is arranged between the preheater and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both arranged between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater and the liquid storage tank, the controller is connected with the sensor group, the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device respectively, and the controller controls the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device to work according to data of the sensors, so that the problem of cooperative heat dissipation of airborne equipment can be solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of an aircraft distributed pump-drive two-phase cooling system according to an embodiment of the present invention.
Description of the symbols:
1-aircraft, 2-precooler, 3-pump, 4-preheater, 5-first heat source, 6-second heat source, 7-third heat source, 8-condenser, 9-reheater, 10-liquid storage tank, 11-first valve, 12-second valve, 13-third valve, 14-first check valve, 15-second check valve, 16-third check valve, 17-condensation cold source, 18-precooling cold source, 19-flowmeter, 20-first pressure sensor, 21-second pressure sensor, 22-third pressure sensor, 23-fourth pressure sensor, 24-first temperature sensor, 25-second temperature sensor, 26-third temperature sensor, 27-fourth temperature sensor, 28-seventh temperature sensor, 29-fifth temperature sensor, 30-eighth temperature sensor, 31-sixth temperature sensor, 32-ninth temperature sensor, 33-tenth temperature sensor, 34-fifth temperature sensor, 35-controller.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The invention discloses a distributed pump-driven two-phase cooling system of an aircraft, which comprises a pump-driven module, a heat source cooling module, a working medium cooling module, a compensation module and a control module, wherein the pump-driven module is used for driving a working medium to cool the working medium; the pump driving module provides power for the system to enable the working medium to flow circularly; the heat source cooling module absorbs heat of a heat source through flowing boiling; the working medium cooling module utilizes a condensing device to discharge system heat through flowing condensation and utilizes a precooling device to ensure that the working medium entering the pump 3 is in a supercooled liquid state through a supercooling measure (temperature reduction); the compensation module utilizes the preheater 4, the third temperature sensor 26 and the third pressure sensor 22 to adjust the dryness of the working medium entering the heat source cooling module in a heat compensation mode, and utilizes the reheater 9, the tenth temperature sensor 33 and the fifth pressure sensor 34 to adjust the system pressure in a heat compensation mode, so as to adjust the state parameters such as the saturation pressure of the working medium entering the heat source cooling module; the control module is according to the temperature, pressure and the flow signal of gathering, adjusts the pump and drives the rotational speed of pump 3 in the module, the heating volume of compensation module, the cold volume input of working medium cooling module, the valve aperture of heat source cooling module etc. and it is all adjustable in time to reasonable state to ensure under each operating mode system to make the heat source temperature remain throughout and set for the within range, specifically as shown in figure 1, aircraft distributing type pump drives two-phase cooling system, includes: the device comprises a controller 35, a pump driving module, a working medium cooling module, a compensation module and a heat source cooling module; the pump drive module includes: the first sensor group, the second sensor group, the liquid storage tank 10, the flowmeter 19 and the pump 3; the compensation module includes: a third sensor group, a fourth sensor group, a preheater 4 and a reheater 9; the heat source cooling module includes: the system comprises a fifth sensor group, a sixth sensor group, a seventh sensor group, a first valve group and a heat source group; the working medium cooling module comprises: a condensing device and a precooling device; the liquid storage tank 10, the pre-cooling device, the pump 3, the flowmeter 19, the pre-heater 4, the first valve group, the heat source group, the condensing device, the reheater 9 and the liquid storage tank 10 are connected in sequence, and the first sensor group is arranged on the liquid storage tank 10; the second sensor group is arranged between the pre-cooling device and the pump 3, and the third sensor group is arranged between the pre-heater 4 and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both disposed between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater 9 and the liquid storage tank 10, the controller 35 is respectively connected to the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group, the seventh sensor group, the precooling apparatus, the pump 3, the preheater 4, the reheater 9, the first valve group and the condensing apparatus, the controller 35 is configured to control the operation of the precooling apparatus, the pump 3, the preheater 4, the reheater 9, the sixth sensor group and the condensing apparatus according to data obtained by the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group and the seventh sensor group, specifically, an outlet of the precooling apparatus is communicated with an inlet of the precooling apparatus, and an outlet of the liquid storage tank is communicated with an inlet of the liquid storage tank 3 through a first pipeline; the outlet of the pump 3 is communicated with the inlet of the flow meter 19, the outlet of the flow meter 19 is communicated with the inlet of the preheater 4, and the outlet of the preheater 4 is communicated with the inlet of the first valve group through a second pipeline; an outlet of the first valve group is communicated with an inlet of the heat source group, and an outlet of the heat source group is communicated with an inlet of the condensing device through a third pipeline; the outlet of the condensing device is communicated with the inlet of the reheater 9; an outlet of the reheater 9 is communicated with an inlet of the liquid storage tank 10 through a fourth pipeline, and the first sensor group is arranged on the liquid storage tank 10; the second sensor group is arranged on the first pipeline, and the third sensor group is arranged on the second pipeline; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both disposed on the third pipeline; the fourth sensor group is disposed on the fourth pipe.
As an optional embodiment, the pre-cooling device includes: a precooler 2 and a precooling cold source 18; a first inlet of the precooler 2 is communicated with an outlet of the liquid storage tank 10, and a first outlet of the precooler 2 is communicated with an inlet of the pump 3 through a first pipeline; the second outlet of the precooler 2 is communicated with the inlet of the precooling cold source 18; the second inlet of the precooler 2 is communicated with the outlet of the precooling cold source 18.
As an alternative embodiment, the condensing device comprises a condenser 8 and a condensation cold source 17; the outlet of the heat source group is communicated with the first inlet of the condenser 8 through a third pipeline; a first outlet of the condenser 8 communicates with an inlet of the reheater 9; the second inlet of the condenser 8 is communicated with the outlet of the condensation cold source 17, and the second outlet of the condenser 8 is communicated with the inlet of the condensation cold source 17.
As an optional embodiment, the heat source cooling module further comprises: a second valve group; the second valve set is disposed on the third conduit.
As an optional implementation, the first sensor set includes: a first pressure sensor 20 and a first temperature sensor 24; the second sensor group includes: a second pressure sensor 21 and a second temperature sensor 25; the third sensor group includes a third pressure sensor 22 and a third temperature sensor 26; the fourth sensor group comprises a tenth temperature sensor 33 and a fifth pressure sensor 34.
As an alternative embodiment, the first valve group comprises a first valve 11, a second valve 12 and a third valve 13; the heat source group comprises a first heat source 5, a second heat source 6 and a third heat source 7; the second valve group comprises a first one-way valve 14, a second one-way valve 15 and a third one-way valve 16; the inlet of the first valve 11, the inlet of the second valve 12 and the inlet of the third valve 13 are all communicated with the outlet of the preheater 4; the outlet of the first valve 11 is communicated with the inlet of the first heat source 5; the outlet of the first heat source 5 is communicated with the inlet of the first one-way valve 14; the outlet of the second valve 12 is communicated with the inlet of the second heat source 6, and the outlet of the second heat source 6 is communicated with the inlet of the second one-way valve 15; the outlet of the third valve 13 is in communication with the inlet of the third heat source 7, and the outlet of the third heat source 7 is in communication with the inlet of the third one-way valve 16; the outlet of the first check valve 14, the outlet of the second check valve 15 and the outlet of the third check valve 16 are all communicated with the inlet of the condensing device, and when the number of heat sources is more or less, the pump-driven two-phase cooling system and the control method thereof are still applicable.
As an optional implementation, the fifth sensor group includes: a fourth temperature sensor 27, a fifth temperature sensor 29, and a sixth temperature sensor 31; the fourth temperature sensor 27 is disposed on the first heat source 5, and the fifth temperature sensor 29 is disposed on the second heat source 6; the sixth temperature sensor 31 is provided on the third heat source 7.
As an alternative embodiment, the sixth sensor group includes: a seventh temperature sensor 28, an eighth temperature sensor 30, and a ninth temperature sensor 32; the seventh temperature sensor 28 is disposed between the first heat source 5 and the first check valve 14, and the eighth temperature sensor 30 is disposed between the second heat source 6 and the second check valve 15; the ninth temperature sensor 32 is disposed between the third heat source 7 and the third check valve 16.
As an optional implementation, the seventh sensor group is: a fourth pressure sensor 23; the fourth pressure sensor 23 is arranged between the outlet of the first one-way valve 14, the outlet of the second one-way valve 15 and the outlet of the third one-way valve 16 and the inlet of the condensation device.
As an alternative embodiment, the third sensor group is arranged between the inlet of the first valve 11, the inlet of the second valve 12 and the inlet of the third valve 13 and the outlet of the preheater 4.
As an alternative embodiment, the condensation cold source 17 and the pre-cooling cold source 18 may be heat sinks in different forms, such as ram air, fuel oil, anti-freezing solution, and the like, on the aircraft 1.
The working process of the distributed pump-driven two-phase cooling system of the aircraft of the embodiment is as follows:
the pump in the pump driving module extracts working media from the liquid storage tank, the working media are cooled to a supercooling state through the precooler of the working media cooling module and enter the pump, then enter the preheater of the compensation module and are heated to a saturation state and set dryness, then enter the heat source cooling module, respectively enter the first heat source, the second heat source and the third heat source through the first valve, the second valve and the third valve, take away heat of the heat sources through flowing boiling, then enter the condenser of the working media cooling module through the first check valve, the second check valve and the third check valve, transfer the heat to a condensation cold source through flowing condensation, then the working media enter the reheater of the compensation module and are heated, and finally flow back to the liquid storage tank. When the load of the heat source changes, the controller adjusts the rotating speed of the pump, changes the flow of the system, adjusts the opening degrees of the first valve, the second valve and the third valve to ensure that the flow flowing through the heat source is matched with the heat load of the heat source, changes the heating quantity of the preheater in the compensation module to ensure that the working medium reaches the saturation state again and the set dryness factor, and changes the cold input of the precooling cold source and the condensation cold source in the working medium cooling module and the heating quantity of the reheater in the compensation module to ensure that the system reaches the balance of the heat input and the cold input again, thereby realizing the stable operation of the system.
Compared with the prior art, the invention achieves the following technical effects:
1. the aircraft distributed pump drive two-phase cooling system solves the problem of cooperative heat dissipation of the aircraft, such as high heat, multiple heat sources, variable load and variable heat sink, and realizes the compactness, high efficiency and technical innovation of an aircraft environment control system. The invention designs the configuration and the control strategy of the pump-driven two-phase cooling system of the aircraft, and utilizes the technologies of flowing boiling, flowing condensation, cold-heat compensation, dynamic adjustment and the like to ensure that the temperature of airborne equipment is always controlled in a reasonable range.
2. The controller adjusts the rotating speed of a pump in the pump driving module, the heating quantity of the compensation module, the cold quantity input of the working medium cooling module, the valve opening degree of the heat source cooling module and the like according to the acquired temperature, pressure and flow signals, and ensures that a system is timely adjusted to a reasonable state when the load of a heat source is dynamically changed, so that the temperature of the heat source is always kept in a set range.
3. The controller regulates the flow of the working medium in the system through the pump; working medium flows entering a first heat source, a second heat source and a third heat source are regulated through a first valve, a second valve and a third valve; working medium backflow is prevented through the first one-way valve, the second one-way valve and the third one-way valve; compensating the insufficient heat of the system and increasing the pressure of the system through a preheater and a reheater; the cold input of the system is controlled and the system pressure is reduced through a condensation cold source and a precooling cold source; the stable operation of the system is ensured through the balance of the heat input and the cold input of the system.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (1)
1. An aircraft distributed pump-drive two-phase cooling system, comprising:
the system comprises a controller, a pump driving module, a working medium cooling module, a compensation module and a heat source cooling module;
the pump drive module includes: the device comprises a first sensor group, a second sensor group, a liquid storage tank, a flowmeter and a pump; the compensation module includes: the system comprises a third sensor group, a fourth sensor group, a preheater and a reheater; the heat source cooling module includes: the system comprises a fifth sensor group, a sixth sensor group, a seventh sensor group, a first valve group and a heat source group; the working medium cooling module comprises: a condensing device and a precooling device;
the liquid storage tank, the pre-cooling device, the pump, the flowmeter, the pre-heater, the first valve group, the heat source group, the condensing device, the reheater and the liquid storage tank are sequentially connected, and the first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the pre-cooling device and the pump, and the third sensor group is arranged between the pre-heater and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both disposed between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater and the liquid storage tank, the controller is respectively connected with the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group, the seventh sensor group, the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device, and the controller is used for controlling the operations of the precooling device, the pump, the preheater, the reheater, the first valve group and the condensing device according to data obtained by the first sensor group, the second sensor group, the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group and the seventh sensor group;
the pre-cooling device comprises: a precooler and a precooling cold source; the first inlet of the precooler is communicated with the outlet of the liquid storage tank, and the first outlet of the precooler is communicated with the inlet of the pump through a first pipeline; the second outlet of the precooler is communicated with the inlet of the precooling cold source; the second inlet of the precooler is communicated with the outlet of the precooling cold source;
the condensing device comprises a condenser and a condensation cold source; an outlet of the heat source group is communicated with a first inlet of the condenser through a third pipeline; a first outlet of the condenser is communicated with an inlet of the reheater; a second inlet of the condenser is communicated with an outlet of the condensation cold source, and a second outlet of the condenser is communicated with an inlet of the condensation cold source;
the heat source cooling module further includes: a second valve group; the second valve set is arranged on the third pipeline;
the first sensor set includes: a first pressure sensor and a first temperature sensor; the second sensor group includes: a second pressure sensor and a second temperature sensor; the third sensor group comprises a third pressure sensor and a third temperature sensor; the fourth sensor group comprises a tenth temperature sensor and a fifth pressure sensor;
the first valve group comprises a first valve, a second valve and a third valve; the heat source group comprises a first heat source, a second heat source and a third heat source; the second valve group comprises a first one-way valve, a second one-way valve and a third one-way valve;
the inlet of the first valve, the inlet of the second valve and the inlet of the third valve are communicated with the outlet of the preheater; an outlet of the first valve is communicated with an inlet of the first heat source; the outlet of the first heat source is communicated with the inlet of the first one-way valve; an outlet of the second valve is communicated with an inlet of the second heat source, and an outlet of the second heat source is communicated with an inlet of the second one-way valve; an outlet of the third valve is communicated with an inlet of the third heat source, and an outlet of the third heat source is communicated with an inlet of the third one-way valve; an outlet of the first one-way valve, an outlet of the second one-way valve and an outlet of the third one-way valve are communicated with an inlet of the condensing device;
the fifth sensor group includes: a fourth temperature sensor, a fifth temperature sensor and a sixth temperature sensor; the fourth temperature sensor is arranged on the first heat source, and the fifth temperature sensor is arranged on the second heat source; the sixth temperature sensor is arranged on the third heat source;
the sixth sensor group includes: a seventh temperature sensor, an eighth temperature sensor, and a ninth temperature sensor; the seventh temperature sensor is arranged between the first heat source and the first one-way valve, and the eighth temperature sensor is arranged between the second heat source and the second one-way valve; the ninth temperature sensor is disposed between the third heat source and the third one-way valve;
the seventh sensor group is: a fourth pressure sensor; the fourth pressure sensor is arranged between the outlet of the first one-way valve, the outlet of the second one-way valve and the outlet of the third one-way valve and the inlet of the condensing device.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210097756.7A CN114364232B (en) | 2022-01-27 | 2022-01-27 | Aircraft distributed pump-drive two-phase cooling system |
| PCT/CN2022/093801 WO2023142314A1 (en) | 2022-01-27 | 2022-05-19 | Distributed pumped two-phase cooling system for aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210097756.7A CN114364232B (en) | 2022-01-27 | 2022-01-27 | Aircraft distributed pump-drive two-phase cooling system |
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| CN114364232A CN114364232A (en) | 2022-04-15 |
| CN114364232B true CN114364232B (en) | 2023-03-03 |
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| CN114364232B (en) * | 2022-01-27 | 2023-03-03 | 南京航空航天大学 | Aircraft distributed pump-drive two-phase cooling system |
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| CN208590199U (en) * | 2018-05-21 | 2019-03-08 | 北京空间飞行器总体设计部 | A kind of cooling system driving two-phase fluid circuit based on compressor and pump |
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|---|---|---|---|---|
| CN112078806B (en) * | 2020-09-25 | 2022-12-30 | 中国直升机设计研究所 | Helicopter liquid cooling integrated control system |
| CN112218497B (en) * | 2020-10-10 | 2021-08-13 | 西安交通大学 | Two-phase heat dissipation loop active control system and method |
| US11273925B1 (en) * | 2020-10-14 | 2022-03-15 | Rolls-Royce North American Technologies Inc. | Thermal management system and method for cooling a hybrid electric aircraft propulsion system |
| CN114364232B (en) * | 2022-01-27 | 2023-03-03 | 南京航空航天大学 | Aircraft distributed pump-drive two-phase cooling system |
-
2022
- 2022-01-27 CN CN202210097756.7A patent/CN114364232B/en active Active
- 2022-05-19 WO PCT/CN2022/093801 patent/WO2023142314A1/en unknown
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN208590199U (en) * | 2018-05-21 | 2019-03-08 | 北京空间飞行器总体设计部 | A kind of cooling system driving two-phase fluid circuit based on compressor and pump |
| CN110822961A (en) * | 2019-11-26 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Two-phase fluid cooling system |
| CN112292004A (en) * | 2020-10-27 | 2021-01-29 | 株洲中车时代电气股份有限公司 | Pump-driven two-phase cooling system and working method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114364232A (en) | 2022-04-15 |
| WO2023142314A1 (en) | 2023-08-03 |
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