An on-board liquid cooling system adaptive combination self-boosting expansion tank

Abstract

The application discloses an adaptive combined self-boosting expansion tank of an airborne liquid cooling system. The expansion tank comprises an expansion shell (1), an inner cavity of the expansion shell (1) is divided into a liquid storage cavity (3) and a static pressure cavity (4) by a large piston (2), the static pressure cavity (4) is communicated with the atmosphere, and the liquid storage cavity (3) is communicated with a liquid cooling pump inlet (22) at an outlet thereof; the large piston (2) is further provided with a boosting cavity (6) on a side close to the static pressure cavity (4), the boosting cavity (6) is provided with a small piston (7) and a reset spring (8) therein; a liquid cooling pump outlet (20) is communicated with the boosting cavity (6) through a liquid guiding pressure stabilizer (9), and the boosting cavity (6) is further communicated with the liquid cooling pump inlet (22) through a constant diameter hole (10). The application can ensure that the self-boosting pressure of the airborne liquid cooling system is stably kept in a specified boosting value (100-200) kPa (absolute pressure) range under different flight altitudes, different outlet pressure changes, different loads and different flow rates.

Description

Technical Field

[0001] This invention belongs to the technical field of airborne liquid cooling systems, specifically relating to an adaptive combined self-pressurizing expansion tank for an airborne liquid cooling system. Background Technology

[0002] Currently, in order to prevent cavitation of the liquid cooling pump in airborne liquid cooling systems, the boosting pressure is generally within (100-200) kPa (absolute pressure). The expansion tanks used all require pressurization. The main pressurization structures of expansion tanks include gravity pressurization, spring pressurization, and priming pressurization. Each pressurization method has certain drawbacks. For example, for expansion tanks with larger diameters, the springs would be too heavy to maintain the boosting pressure, which is unacceptable for airborne products. When using a priming self-pressurization structure, the weight is relatively light, but there are problems such as piston non-reset and longer ground maintenance time. In addition, it is not suitable for liquid cooling systems with high flow rates and multiple operating conditions. When pressurizing, it is impossible to guarantee that the boosting pressure is stable within the (100-200) kPa (absolute pressure) range. Summary of the Invention

[0003] The purpose of this invention is to provide an adaptive combined self-pressurizing expansion tank for an airborne liquid cooling system. This invention can ensure that the self-pressurizing pressure of the airborne liquid cooling system remains stable within a specified pressurization value (100-200) kPa (absolute pressure) range under different flight altitudes, different outlet pressure variations, different loads, and different flow rates.

[0004] The technical solution of the present invention is: an adaptive combined self-pressurizing expansion tank for an airborne liquid cooling system, comprising an expansion shell, the inner cavity of which is divided into a liquid storage chamber and a static pressure chamber by a large piston, the static pressure chamber being connected to the atmosphere, and the outlet of the liquid storage chamber being connected to the inlet of the liquid cooling pump; a pressurizing chamber is also provided on the side of the large piston near the static pressure chamber, and a small piston and a return spring are provided in the pressurizing chamber; the outlet of the liquid cooling pump is connected to the pressurizing chamber via a liquid priming regulator, and the pressurizing chamber is also connected to the inlet of the liquid cooling pump via a sizing hole.

[0005] In the aforementioned airborne liquid cooling system adaptive combination self-pressurization expansion tank, the outlet of the liquid cooling pump is also connected to external system equipment.

[0006] In the aforementioned airborne liquid cooling system adaptive combination self-pressurization expansion tank, the system equipment outlet is also connected to a gas-liquid separator via a return port, and the gas-liquid separator is connected to the liquid storage chamber via a coolant compensation channel; the gas-liquid separator is also connected to the liquid discharge / venting port of the liquid storage chamber.

[0007] In the aforementioned airborne liquid cooling system adaptive combination self-pressurization expansion tank, the liquid priming regulator includes a pressure stabilizing housing, which is divided into chamber A and chamber B. Chambers A and B are coaxially arranged and connected to each other through a valve hole. Chambers A and B are respectively provided with valve seat A and valve seat B. The opposite surfaces of valve seats A and B are separated by a push rod passing through the valve hole. Chamber B is connected to the pressurization chamber, and chamber A is connected to the outlet of the liquid cooling pump.

[0008] In the aforementioned airborne liquid cooling system adaptive combination self-pressurization expansion tank, the liquid cooling pump is axially mounted in the inner cavity of the small piston.

[0009] In the aforementioned airborne liquid cooling system's adaptive combined self-pressurizing expansion tank, during liquid injection of the integrated liquid supply component:

[0010] When filling the airborne liquid cooling system, first open the drain / vent port. The ground filling vehicle fills the system with coolant from the liquid cooling pump outlet. After circulating through the system equipment, the coolant enters the return port of the adaptive combined expansion tank. Under the pressure of the external filling vehicle, the coolant enters the storage chamber of the expansion shell through the coolant compensation channel. Under the pressure, the coolant pushes the large piston to the left, causing the storage chamber to continuously increase and the static pressure chamber to continuously decrease. At the same time, it compresses the return spring and the volume of the pressure boosting chamber until the coolant fills the entire inner cavity of the expansion shell. At this time, the entire inner cavity of the expansion shell is the storage chamber, and the end face M of the large piston is in contact with the end face N of the filter housing. Meanwhile, excess liquid is discharged to the outside of the machine through the drain / vent port. After filling, close the drain / vent port.

[0011] In the aforementioned airborne liquid cooling system, the coolant flowing out of the storage chamber is pressurized by the liquid cooling pump and then divided into two paths. One path is normally supplied to the external system equipment, and the other path enters the pressurization chamber after passing through the liquid priming regulator. The stabilization effect of the liquid priming regulator ensures that the coolant in the pressurization chamber is always kept within a preset range, thus ensuring the pressure in the pressurization chamber is stable, and in turn ensuring the pressure flowing from the storage chamber into the liquid cooling pump inlet is stable.

[0012] In the aforementioned airborne liquid cooling system's adaptive combination self-pressurization expansion tank, the stabilization process is as follows: Coolant from the liquid cooling pump outlet continuously flows into the pressurization chamber, causing the pressure in the interconnected pressurization chamber and chamber B to continuously increase. This pressure acts on valve seat B, gradually moving it away from the valve orifice. Simultaneously, the push rod moves to release valve seat A, which gradually approaches the valve orifice until it blocks it. Coolant in chamber B and the pressurization chamber gradually flows into the liquid cooling pump inlet through the sizing orifice. At this point, the pressure in the pressurization chamber gradually decreases, and valve seat B gradually approaches the valve orifice again. Simultaneously, the push rod pushes valve seat A away from the valve orifice, reconnecting chambers A and B. Coolant from the liquid cooling pump outlet causes the pressure in chamber B and the pressurization chamber to gradually increase again. Repeating this process, as the liquid cooling pump pressurizes to the preset pressure range, valve seats A and B continuously float to establish a dynamic balance, ensuring the pressurization chamber pressure remains stable within the specified range.

[0013] The advantages of this invention are as follows: First, it ensures that the self-pressurization pressure of the airborne liquid cooling system in an aircraft remains stable within a specified pressurization value (100-200) kPa (absolute pressure) range under different flight altitudes, varying outlet pressures, loads, and flow rates. This guarantees the stability of the inlet pressure (i.e., pressurization value) of the liquid cooling pump in the airborne liquid cooling system. Second, by ensuring stable outlet pressure within this range, water hammer phenomena can be prevented, effectively improving system durability and reliability. Third, regardless of changes in aircraft attitude and flight altitude, this invention ensures that the system pressurization value remains stable within a certain range, preventing cavitation of the liquid cooling pump in the airborne liquid cooling system, improving the reliability and lifespan of the liquid cooling pump, and thus enhancing system reliability.

[0014] This invention employs a spring + liquid-pressurizing structure, which can reduce product weight on the one hand, and the spring can reset the piston on the other hand, reducing ground maintenance time.

[0015] This invention, by setting up a drain / vent, facilitates the discharge of excess liquid during ground-based filling, while simultaneously venting the gas separated by the gas-liquid separator outside the machine.

[0016] By setting up a liquid priming pressure stabilizer, this invention can ensure that the boosting pressure P3 of the boosting chamber remains stable when the flow rate and outlet pressure of the liquid cooling pump change.

[0017] This invention improves integration and reduces product weight through the integrated design of the pressurization chamber and the large piston of the expansion tank. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the present invention;

[0019] Figure 2 This is a schematic diagram illustrating the principle of the present invention;

[0020] Figure 3 This is a schematic diagram of a liquid-priming voltage regulator.

[0021] Reference numerals: 1-Expansion shell, 2-Large piston, 3-Liquid storage chamber, 4-Static pressure chamber, 5-Liquid cooling pump, 6-Pressure boosting chamber, 7-Small piston, 8-Reset spring, 9-Liquid priming regulator, 10-Sizing hole, 11-Adaptive combined expansion tank return port, 12-Gas-liquid separator, 13-Coolant compensation channel, 14-Drain / vent port, 15-Pressure stabilizing shell, 16-Valve hole, 17-Valve seat A, 18-Valve seat B, 19-Push rod, 20-Liquid cooling pump outlet, 21-Filter shell, 22-Liquid cooling pump inlet. Detailed Implementation

[0022] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.

[0023] Example 1. An adaptive combined self-pressurizing expansion tank for an airborne liquid cooling system, wherein a liquid cooling pump 5, a gas-liquid separator 12, a liquid priming regulator 9, and a small piston 7 are mounted on a filter housing 21 and extend into a pressurizing chamber 6 formed by the wall of a large piston 2. The large piston 2 is mounted inside an expansion housing 1. A return spring 8 is mounted inside the pressurizing chamber 6, with one end pressing against the bottom surface H of the large piston 2 and the other end pressing against the end face G of the small piston 7.

[0024] The function of the liquid priming regulator 9 is to ensure the booster pressure P03 in the booster chamber when the flow rate and outlet pressure of the liquid cooling pump change. The function of the return spring 8 is to ensure the large piston 2 returns to its original position when the priming pressure disappears. Simultaneously, the spring force generated by the return spring 8 presses on the end face H of the large piston, pressurizing the reservoir 3. The function of the large piston 2 is to transfer the pressure in the booster chamber 6 and the force generated by the return spring 8 to the coolant in the reservoir, thereby boosting the liquid cooling pump inlet 22. The movement of the large piston 2 compensates for the coolant level in the system and also seals the coolant within the system. The function of the small piston 7 is to seal the pressure in the booster chamber 6 and simultaneously boost the pressure on the large piston.

[0025] For details, please refer to [link / details]. Figure 1-3 The system includes an expansion shell 1, whose inner cavity is divided into a liquid storage chamber 3 and a static pressure chamber 4 by a large piston 2. The static pressure chamber 4 is connected to the atmosphere, and the outlet of the liquid storage chamber 3 is connected to the inlet 22 of the liquid cooling pump. A pressure boosting chamber 6 is also provided on the side of the large piston 2 near the static pressure chamber 4. The pressure boosting chamber 6 is provided with a small piston 7 and a return spring 8. The outlet 20 of the liquid cooling pump is connected to the pressure boosting chamber 6 via a liquid priming and pressure stabilizing device 9. The pressure boosting chamber 6 is also connected to the inlet 22 of the liquid cooling pump via a sizing hole 10.

[0026] The aforementioned liquid cooling pump outlet 20 is also connected to external system equipment.

[0027] The system equipment outlet is also connected to the gas-liquid separator 12 via the return port 11. The gas-liquid separator 12 is connected to the liquid storage chamber 3 via the coolant compensation channel 13. The gas-liquid separator 12 is also connected to the drain / vent port 14 of the liquid storage chamber 3.

[0028] The aforementioned liquid-priming pressure regulator 9 includes a pressure-stabilizing housing 15, which is divided into chamber A and chamber B. Chambers A and B are coaxially arranged and connected by a valve hole 16. Chambers A and B are respectively provided with valve seats A17 and B18. The opposite surfaces of valve seats A and B are opened by a push rod 19 passing through the valve hole 16. Chamber B is connected to the pressure boosting chamber 6, and chamber A is connected to the liquid cooling pump outlet 20.

[0029] The aforementioned liquid-cooled pump 5 is mounted axially inside the small piston.

[0030] The aforementioned adaptive combined self-pressurizing expansion tank structure for airborne liquid cooling system includes the following working steps:

[0031] 1. When the integrated liquid supply assembly is filling:

[0032] When filling the airborne liquid cooling system, first open the drain / vent port 14. The ground refueling vehicle fills the system with coolant through the liquid cooling pump outlet 20. The liquid cooling pump outlet 20 is equipped with a one-way valve 105 to ensure that the coolant being filled does not enter the pump body through the outlet 20, thus ensuring one-way circulation of the system liquid and venting any gas within the system during ground refueling. The filled coolant circulates through the system equipment and then enters the adaptive combined expansion tank return port 11. Due to the external refueling vehicle pressure, the coolant flows through the coolant compensation channel... The coolant enters the liquid storage chamber 3 of the expansion shell 1 through channel 1. Under pressure, the coolant pushes the large piston 2 to the left, causing the liquid storage chamber 3 to continuously increase and the static pressure chamber 4 to continuously decrease. At the same time, the return spring 8 and the pressure boosting chamber 6 are compressed until the coolant fills the entire inner cavity of the expansion shell 1. At this time, the entire inner cavity of the expansion shell 1 is the liquid storage chamber 3. The end face M of the large piston 2 is in contact with the end face N of the filter housing 21. Meanwhile, excess liquid is discharged out of the tank through the drain / vent port 14. After filling, the drain / vent port 14 is closed.

[0033] 2. When the integrated liquid supply assembly is working:

[0034] Step 1: When the liquid supply assembly is in ground venting operation, start the liquid cooling pump 5. This achieves both liquid circulation venting and drainage functions, and self-pressurization. At this time, the gas in the system coolant is separated by the gas-liquid separator 12 in the integrated liquid supply assembly. When the gas is collected to a certain extent, open the drain / vent port 14, and at the same time, a portion of the liquid in the expansion tank is discharged outside the machine. This cycle is repeated multiple times until the liquid in the expansion tank is discharged to the specified level.

[0035] Secondly, after the liquid cooling pump 5 is started, the pressure P0 generated by the high-pressure coolant enters the A chamber of the liquid priming regulator 9 through the liquid cooling pump outlet 20. After being regulated by the valve seat A17, push rod 19, valve seat B18, and valve hole 16, it flows through the B chamber and then enters the pressurization chamber 6 to pressurize the large piston 2. At the same time, under the action of the large piston 2, the coolant in the liquid storage chamber 3 is pressurized, thereby realizing the pressurization of the liquid cooling pump inlet 22.

[0036] Step 2: After the system is purged, when the aircraft takes off and lands, the integrated liquid supply component works, that is, the liquid cooling pump 5 is started. On the one hand, the pressure P0 generated by the high-pressure coolant returns to the liquid cooling system supply and return port 11 through the liquid cooling pump outlet 20 and the system equipment, realizing the circulation of the system coolant. On the other hand, the pressure P0 generated by the high-pressure coolant enters the A chamber of the liquid priming regulator 9 through the liquid cooling pump outlet 20. After being regulated by the valve seat A17, the push rod 19, the valve seat B18, and the valve hole 16, it flows through the B chamber and then enters the pressurization chamber 6 to pressurize the large piston 2. At the same time, under the action of the large piston 2, the coolant in the liquid storage chamber 3 is pressurized, thereby realizing the pressurization of the liquid cooling pump inlet 22.

[0037] Step 3: The working status of the aircraft in various attitudes. When the aircraft performs different attitude actions, such as roll, roll, climb, and dive, repeat step 2 to ensure the use requirements of the aircraft in various attitudes.

[0038] The voltage stabilization process of the liquid-priming regulator:

[0039] The voltage stabilization steps are as follows:

[0040] Step ①: Initially, the liquid priming regulator 9 is in the open state, meaning chambers A and B are connected. When the liquid cooling pump 5 is started, it outputs pressure ΔP. The pressure P0 of the No. 65 coolant at the outlet 20 of the liquid cooling pump enters chamber A, generating pressure P01. P0 = P01. After pressure regulation in the liquid priming regulator 9, the coolant enters chamber B. Since the area S3 of the valve hole 16 is smaller than the area S4 of the valve seat B18, as the pressure P03 in chamber B gradually increases, the flow area between chambers A and B gradually decreases. When the specified pressure P03 is reached, i.e., when P03 satisfies the following relationship, the valve seat A17 closes the valve hole 16.

[0041] F=(P01*S3+F1+P03- P4)*S4. (1)

[0042] When valve seat A17 is closed, P03 will drop, and at the same time valve seat A17 will gradually open, repeating the cycle. At this time, the pressure of P03 is the boosting pressure, realizing the self-pressurization of the expansion tank.

[0043] When adjusting P03 to P3 on the ground, P03 should satisfy the following relationship:

[0044] F=(P01*S3+F1+(P03- P4))*S4 (2)

[0045] Step ②: When the aircraft takes off, the ground is adjusted to P03 = P3. According to Formula 1, when the atmospheric pressure of P4 decreases as the aircraft altitude increases, the pressure of P03 will increase under the condition that F remains unchanged, realizing the pressure increase and decrease function within a small range, thereby ensuring that the inlet pressure of the liquid cooling pump meets the 100-200kPa (absolute pressure) range required by P1.

[0046] Step ③: When the aircraft descends, according to Formula 2, when the atmospheric pressure P4 increases as the aircraft's altitude decreases, the pressure P03 will decrease under the condition that F remains constant, until the ground is reached and the adjustment value P03 = P3 is required, thereby ensuring that the inlet pressure of the liquid cooling pump meets the 100-200kPa (absolute pressure) range required by P1.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. An adaptive combined self-pressurizing expansion tank for an airborne liquid cooling system, characterized in that, The system includes an expansion shell, whose inner cavity is divided into a liquid storage chamber and a static pressure chamber by a large piston. The static pressure chamber is open to the atmosphere, and the outlet of the liquid storage chamber is connected to the inlet of the liquid-cooled pump. A pressure-boosting chamber is also located near the static pressure chamber on the side of the large piston, containing a small piston and a return spring. The outlet of the liquid-cooled pump is connected to the pressure-boosting chamber via a liquid priming regulator, and the pressure-boosting chamber is also connected to the inlet of the liquid-cooled pump via a sizing orifice. The outlet of the liquid-cooled pump is also connected to external system equipment. The outlet of the system equipment is connected to a gas-liquid separator via a return port. The liquid separator is connected to the liquid storage chamber via a coolant compensation channel; the gas-liquid separator is also connected to the drain / vent of the liquid storage chamber; the liquid-priming pressure stabilizer includes a pressure stabilizing housing, which is divided into chamber A and chamber B. Chambers A and B are coaxially arranged and connected to each other via a valve hole. Chambers A and B are respectively provided with valve seat A and valve seat B. The opposite surfaces of valve seats A and B are separated by a push rod passing through the valve hole; chamber B is connected to the pressurization chamber, and chamber A is connected to the outlet of the liquid cooling pump.

2. The adaptive combined self-pressurizing expansion tank of the airborne liquid cooling system according to claim 1, characterized in that, The liquid-cooled pump is axially mounted inside the small piston.

3. The adaptive combined self-pressurizing expansion tank of the airborne liquid cooling system according to claim 1, characterized in that, When the integrated liquid supply assembly is filling: When filling the airborne liquid cooling system, first open the drain / vent port. The ground filling vehicle fills the system with coolant from the liquid cooling pump outlet. After circulating through the system equipment, the coolant enters the return port of the adaptive combined expansion tank. Under the pressure of the external filling vehicle, the coolant enters the storage chamber of the expansion shell through the coolant compensation channel. Under the pressure, the coolant pushes the large piston to the left, causing the storage chamber to continuously increase and the static pressure chamber to continuously decrease. At the same time, it compresses the return spring and the volume of the pressure boosting chamber until the coolant fills the entire inner cavity of the expansion shell. At this time, the entire inner cavity of the expansion shell is the storage chamber, and the end face M of the large piston is in contact with the end face N of the filter housing. Meanwhile, excess liquid is discharged to the outside of the machine through the drain / vent port. After filling, close the drain / vent port.

4. The adaptive combined self-pressurizing expansion tank of the airborne liquid cooling system according to claim 1, characterized in that, The coolant flowing out of the storage chamber is pressurized by the liquid cooling pump and then divided into two paths. One path is normally supplied to the external system equipment, and the other path enters the pressurization chamber after passing through the liquid priming regulator. The stabilizing effect of the liquid priming regulator ensures that the coolant in the pressurization chamber is always kept within a preset range, thus ensuring the pressure in the pressurization chamber is stable, and in turn ensuring the pressure flowing from the storage chamber into the inlet of the liquid cooling pump is stable.

5. The adaptive combined self-pressurizing expansion tank of the airborne liquid cooling system according to claim 1, characterized in that, The stabilization process is as follows: Coolant from the liquid-cooled pump outlet continuously flows into the pressurization chamber, causing the pressure in the interconnected pressurization chamber and chamber B to continuously increase. This pressure acts on valve seat B, causing it to gradually move away from the valve orifice. Simultaneously, the push rod moves to release valve seat A, which gradually moves closer to the valve orifice until it blocks it. Coolant in chamber B and the pressurization chamber gradually flows into the liquid-cooled pump inlet through the sizing orifice. At this time, the pressure in the pressurization chamber gradually decreases, and valve seat B gradually moves closer to the valve orifice. At the same time, the push rod pushes valve seat A away from the valve orifice, and chambers A and B are reconnected. Coolant from the liquid-cooled pump outlet causes the pressure in chamber B and the pressurization chamber to gradually increase again. Repeating the above process, as the liquid-cooled pump is pressurized to the preset pressure range, valve seats A and B continuously float to continuously establish a dynamic balance, keeping the pressure in the pressurization chamber within the specified range.

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