Aircraft turbo refrigeration control system and method

Abstract

The present application relates to aircraft turbine refrigeration control system and method. The aircraft turbine refrigeration control system comprises outlet pressure difference sensor, inlet mass flow sensor, condenser mass flow sensor, air-water separator mass flow sensor and controller; the controller is configured to: when the pressure difference between turbine outlet and cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow is greater than the sum of condenser outlet air mass flow and air-water separator outlet mass flow; when the inlet air mass flow is greater than the sum of outlet mass flow, determine that the turbine outlet is icing, and implement ice melting operation; when the inlet air mass flow is equal to the sum of outlet mass flow, determine that the heat exchanger channel is dirty, and send heat exchanger maintenance alarm information. According to the above technical scheme, the present application can achieve the following beneficial technical effects: the ice blocking phenomenon can be automatically predicted, and the possibility of ice blocking can be greatly reduced through preventive measures.

Description

Technical Field

[0001] This invention relates to the field of aircraft turbine refrigeration, and more particularly to an aircraft turbine refrigeration control system and control method. Background Technology

[0002] Aircraft air conditioning systems (i.e., aircraft turbine cooling systems) are primarily used to maintain a stable air environment within the sealed cabin under various flight conditions, ensuring the safety and comfort of passengers and pilots, and ensuring the normal operation of electronic equipment. The operational stability of aircraft air conditioning systems is a crucial indicator for evaluating the overall performance of modern civil aircraft and the quality of airlines. Aircraft air conditioning systems are complex, involving numerous components; malfunction of any component can cause system failure, resulting in significant harm to pilots and passengers, and even catastrophic consequences.

[0003] When an aircraft's air conditioning system operates on the ground and at low altitudes, especially under high temperature and high humidity conditions, the air has a very high moisture content. As the air expands and cools, it will release moisture. Since the turbine's outlet temperature is usually below 0°C, the released water is very likely to freeze at the turbine outlet, causing ice blockage inside.

[0004] In existing technologies, ice blockage is determined by monitoring the pressure difference between the turbine outlet and the cabin. If the pressure difference exceeds a set value and persists for a certain period, ice blockage is considered to have occurred; that is, ice blockage is only identified when the turbine outlet reaches a certain level of icing. Once ice blockage occurs, the controller adjusts the ram air damper and temperature control valve to increase the system outlet temperature and eliminate the blockage. However, during turbine outlet icing, the increased turbine outlet pressure reduces performance, decreases air supply, and raises air supply temperature, affecting the cabin temperature and potentially preventing it from reaching the target value. In other words, the current "remedial" measures cannot eliminate the impact of turbine outlet icing on cabin temperature control. Furthermore, the heat exchanger channels in the aircraft turbine cooling system are millimeter-scale structures. Over long-term operation, dust and particles from the air accumulate in these channels, increasing resistance and potentially causing blockages. Current system control logic cannot clearly distinguish between ice blockage and blockage conditions, potentially leading to misjudgments and erroneous commands that could jeopardize flight safety. Summary of the Invention

[0005] One objective of this invention is to provide an aircraft turbine cooling control system and method that overcomes the shortcomings of the prior art, can automatically predict ice blockage, and significantly reduce the possibility of ice blockage through preventive measures.

[0006] The above-mentioned objectives of the present invention are achieved by an aircraft turbine refrigeration control system, which includes an outlet differential pressure sensor, an inlet mass flow sensor, a condenser mass flow sensor, a gas-liquid separator mass flow sensor, and a controller.

[0007] The outlet differential pressure sensor is installed at the outlet of the aircraft turbine cooling system to monitor the pressure difference between the turbine outlet and the cabin.

[0008] The inlet mass flow sensor is installed on the inlet pipe of the aircraft turbine cooling system to monitor the mass flow of air entering the aircraft turbine cooling system.

[0009] The condenser mass flow sensor is installed on the cold side outlet pipe of the condenser of the aircraft turbine refrigeration system to monitor the mass flow rate of air flowing out of the aircraft turbine refrigeration system through the condenser.

[0010] The mass flow sensor of the gas-water separator is installed on the outlet pipe of the gas-water separator of the aircraft turbine refrigeration system to monitor the mass flow rate of the gas-water separator flowing out of the aircraft turbine refrigeration system.

[0011] The controller is connected to the outlet differential pressure sensor, the inlet mass flow sensor, the condenser mass flow sensor, and the gas-liquid separator mass flow sensor. The controller is configured to:

[0012] When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0013] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed.

[0014] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

[0015] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: it can automatically predict ice blockage and significantly reduce the possibility of ice blockage through preventive measures; it can accurately distinguish between ice blockage and dirt blockage, thereby taking targeted measures.

[0016] Preferably, the first differential pressure setting is 12 to 15 kPa.

[0017] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: by setting an appropriate first differential pressure value, it can predict the ice blockage phenomenon in advance and reduce the possibility of ice blockage by a greater extent.

[0018] Preferably, the de-icing operation includes: increasing the opening of the temperature control valve or decreasing the opening of the ram air damper.

[0019] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: by using a suitable de-icing operation method, it can promptly melt a small amount of ice at the turbine outlet when it is anticipated that ice blockage may occur, thereby greatly reducing the possibility of ice blockage.

[0020] Preferably, the controller is further configured to: when the pressure difference between the turbine outlet and the cabin is greater than a second pressure difference setting value and less than a first pressure difference setting value, wherein the second pressure difference setting value is lower than the first pressure difference setting value, it is also determined whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate;

[0021] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a turbine outlet icing warning message is sent.

[0022] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a heat exchanger channel blockage warning message is sent.

[0023] Preferably, the controller is also configured to send a heat exchanger maintenance alarm message after the pressure difference between the turbine outlet and the cabin has exceeded a third pressure difference set value for a certain period of time.

[0024] According to the above technical solution, the aircraft turbine refrigeration control system of the present invention can achieve the following beneficial technical effects: it can promptly identify dirt blockage and promptly send heat exchanger maintenance alarm information.

[0025] Preferably, the aircraft turbine refrigeration system includes a compressor, an expander, a primary heat exchanger, a main heat exchanger, a regenerator, a condenser, and a gas-liquid separator.

[0026] The aircraft turbine refrigeration process includes: air from the inlet of the aircraft turbine refrigeration system enters the hot side of the primary heat exchanger, is cooled by ram air and then splits into two paths. One path enters the compressor, the hot side of the main heat exchanger, the hot side of the regenerator, the hot side of the condenser, the gas-liquid separator, the cold side of the regenerator, and the expander in sequence. Then it merges with the other path of air through the temperature control valve and is discharged from the aircraft turbine refrigeration system through the cold side of the condenser.

[0027] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: through appropriate aircraft turbine cooling system layout and aircraft turbine cooling process design, it can better automatically predict ice blockage and greatly reduce the possibility of ice blockage.

[0028] The above-mentioned objectives of the present invention are also achieved by an aircraft turbine cooling control method, the aircraft turbine cooling control method comprising:

[0029] Monitor the pressure difference between the turbine outlet and the cabin, monitor the inlet air mass flow rate of the aircraft turbine cooling system, monitor the condenser outlet air mass flow rate of the aircraft turbine cooling system, and monitor the gas-water separator outlet mass flow rate of the aircraft turbine cooling system.

[0030] When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0031] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed.

[0032] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

[0033] Preferably, the first differential pressure setting is 12 to 15 kPa.

[0034] According to the above technical solution, the aircraft turbine cooling control method of the present invention can achieve the following beneficial technical effects: by setting an appropriate first differential pressure value, ice blockage can be predicted in advance, and the possibility of ice blockage can be reduced significantly.

[0035] Preferably, the de-icing operation includes: increasing the opening of the temperature control valve or decreasing the opening of the ram air damper.

[0036] According to the above technical solution, the aircraft turbine cooling control method of the present invention can achieve the following beneficial technical effects: by using a suitable de-icing operation method, it can promptly melt a small amount of ice at the turbine outlet when it is anticipated that ice blockage may occur, thereby greatly reducing the possibility of ice blockage.

[0037] Preferably, when the pressure difference between the turbine outlet and the cabin is greater than the second pressure difference setting value and less than the first pressure difference setting value, wherein the second pressure difference setting value is lower than the first pressure difference setting value, it is also determined whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0038] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a turbine outlet icing warning message is sent.

[0039] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a heat exchanger channel blockage warning message is sent.

[0040] Preferably, a heat exchanger maintenance alarm is also sent after the pressure difference between the turbine outlet and the cabin exceeds the third pressure difference setting value for a certain period of time.

[0041] According to the above technical solution, the aircraft turbine cooling control method of the present invention can achieve the following beneficial technical effects: it can promptly identify dirt blockage and promptly send heat exchanger maintenance alarm information.

[0042] Preferably, the aircraft turbine refrigeration system includes a compressor, an expander, a primary heat exchanger, a main heat exchanger, a regenerator, a condenser, and a gas-liquid separator.

[0043] The aircraft turbine refrigeration process includes: air from the inlet of the aircraft turbine refrigeration system enters the hot side of the primary heat exchanger, is cooled by ram air and then splits into two paths. One path enters the compressor, the hot side of the main heat exchanger, the hot side of the regenerator, the hot side of the condenser, the gas-liquid separator, the cold side of the regenerator, and the expander in sequence. Then it merges with the other path of air through the temperature control valve and is discharged from the aircraft turbine refrigeration system through the cold side of the condenser.

[0044] According to the above technical solution, the aircraft turbine cooling control method of the present invention can achieve the following beneficial technical effects: through appropriate aircraft turbine cooling system layout and aircraft turbine cooling process design, it can better automatically predict ice blockage and greatly reduce the possibility of ice blockage. Attached Figure Description

[0045] Figure 1 This is a flowchart of an aircraft turbine cooling control method according to an embodiment of the present invention.

[0046] Figure 2 This is a schematic diagram of an aircraft turbine cooling control system according to an embodiment of the present invention. Detailed Implementation

[0047] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0048] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The terms "an" or "a" and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms "comprising" or "including" and similar terms mean that the element or object preceding "comprising" or "including" encompasses the element or object listed following "comprising" or "including" and its equivalents, and do not exclude other elements or objects. The terms "connected" or "linked" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0049] Figure 1 This is a flowchart of an aircraft turbine cooling control method according to an embodiment of the present invention. Figure 2 This is a schematic diagram of an aircraft turbine cooling control system according to an embodiment of the present invention.

[0050] like Figures 1 to 2 As shown, according to an embodiment of the present invention, an aircraft turbine refrigeration control system includes an outlet differential pressure sensor, an inlet mass flow sensor, a condenser mass flow sensor, a gas-water separator mass flow sensor, and a controller.

[0051] The outlet differential pressure sensor is installed at the outlet of the aircraft turbine cooling system to monitor the pressure difference between the turbine outlet and the cabin.

[0052] The imported mass flow sensor is installed on the inlet pipe of the aircraft turbine cooling system to monitor the mass flow rate of air entering the aircraft turbine cooling system (i.e., the inlet air mass flow rate).

[0053] The condenser mass flow sensor is installed on the cold side outlet pipe of the condenser in the aircraft turbine refrigeration system to monitor the mass flow rate of air flowing out of the aircraft turbine refrigeration system through the condenser (i.e., the mass flow rate of air at the condenser outlet).

[0054] The mass flow sensor of the gas-water separator is installed on the outlet pipe of the gas-water separator in the aircraft turbine cooling system (i.e., on the pipe from the gas-water separator to the water jet in the aircraft turbine cooling system) to monitor the mass flow rate of the gas-water separator flowing out of the aircraft turbine cooling system (i.e., the mass flow rate of the gas-water separator outlet).

[0055] The controller is connected to the outlet differential pressure sensor, the inlet mass flow sensor, the condenser mass flow sensor, and the gas-liquid separator mass flow sensor. The controller is configured as follows:

[0056] When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0057] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed.

[0058] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

[0059] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: it can automatically predict ice blockage and significantly reduce the possibility of ice blockage through preventive measures; it can accurately distinguish between ice blockage and dirt blockage, thereby taking targeted measures.

[0060] Specifically, during stable system operation, the mass of the working fluid flowing into the system is equal to the mass of the working fluid flowing out. When the mass flow rate of the working fluid flowing into the system is greater than the mass flow rate of the working fluid flowing out, it indicates that a certain mass of working fluid is trapped inside the system. When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setpoint, and the inlet mass flow rate is greater than the outlet mass flow rate, it indicates that water has frozen and is trapped between the turbine outlet and the condenser outlet. In this case, turbine outlet freezing is determined, and de-icing is performed. When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setpoint, and the inlet mass flow rate is equal to the outlet mass flow rate, it indicates that blockage has occurred. In this case, heat exchanger channel blockage is determined, and a heat exchanger maintenance alarm message is sent to remind the system to clean the blockage as soon as possible.

[0061] Existing systems monitor the pressure difference between the turbine outlet and the cabin. When the pressure difference exceeds a set value, they determine that icing has occurred and then adjust the system temperature control valve and ram air damper to increase the turbine outlet temperature and eliminate the icing. The occurrence of icing increases the risk of system operation and reduces aircraft comfort. When the system experiences fouling, the pressure difference gradually increases, and may even exceed the set value for icing, causing the system to misinterpret the situation and resulting in inaccurate system status monitoring. Existing systems eliminate icing by forcibly and significantly increasing the outlet temperature, which is mismatched with the aircraft's requirements, leading to system instability and fluctuations in system operating parameters. The aircraft turbine cooling control system of this invention can automatically predict icing and significantly reduce its likelihood through preventative measures. It can accurately distinguish between icing and fouling, allowing for targeted measures to improve system safety, the accuracy of monitoring logic, the stability of status parameters, and aircraft comfort.

[0062] In some embodiments, such as Figures 1 to 2 As shown, the first differential pressure setting is 12-15 kPa.

[0063] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: By using a suitable first differential pressure setting value, ice blockage can be predicted in advance, significantly reducing the possibility of ice blockage. Since the first differential pressure setting value in the present invention is much lower than the differential pressure setting value used in the prior art to determine ice blockage (the differential pressure setting value used in the prior art to determine ice blockage is usually around 19 kPa), the present invention can predict ice blockage in advance and take de-icing operations in advance when the system is icing but not yet experiencing ice blockage, significantly reducing the possibility of ice blockage (or even eliminating it). Furthermore, the present invention performs corresponding control when the system is icing but not yet experiencing ice blockage, avoiding large fluctuations in system and air temperature, flow rate, pressure, and other state parameters, thereby improving the safety of system operation, the stability of state parameters, and aircraft comfort.

[0064] In some embodiments, such as Figures 1 to 2 As shown, the de-icing operation includes: increasing the opening of the temperature control valve or decreasing the opening of the ram air damper.

[0065] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: by using a suitable de-icing operation method, it can promptly melt a small amount of ice at the turbine outlet when it is anticipated that ice blockage may occur, thereby greatly reducing the possibility of ice blockage.

[0066] In some embodiments, such as Figures 1 to 2As shown, the controller is also configured to: when the pressure difference between the turbine outlet and the cabin is greater than the second pressure difference setting value and less than the first pressure difference setting value, wherein the second pressure difference setting value is lower than the first pressure difference setting value, it is also determined whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0067] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a turbine outlet icing warning message is sent.

[0068] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a heat exchanger channel blockage warning message is sent.

[0069] For example, if the first differential pressure setting is a value between 12 and 15 kPa, the second differential pressure setting can be a value between 7 and 12 kPa.

[0070] In some embodiments, such as Figures 1 to 2 As shown, the controller is also configured to send a heat exchanger maintenance alarm message after the pressure difference between the turbine outlet and the cabin exceeds the third pressure difference set value for a certain period of time.

[0071] According to the above technical solution, the aircraft turbine refrigeration control system of the present invention can achieve the following beneficial technical effects: it can promptly identify dirt and blockage phenomena and send heat exchanger maintenance alarm information in a timely manner. That is to say, when the outlet differential pressure sensor detects that the outlet differential pressure is greater than the third differential pressure set value for a certain period of time, it indicates that the dust and dirt on the cold side of the condenser are serious, the flow area is reduced, and blockage is very likely to occur. Cleaning is required to ensure the safe and stable operation of the system and reduce the possibility of blockage.

[0072] Preferably, the third differential pressure setting value is lower than the first differential pressure setting value. For example, if the first differential pressure setting value is between 12 and 15 kPa, the third differential pressure setting value can be between 7 and 12 kPa. For example, if the first differential pressure setting value is 12 kPa, the third differential pressure setting value can be 7 kPa; if the first differential pressure setting value is 13 kPa, the third differential pressure setting value can be 8 kPa; if the first differential pressure setting value is 14 kPa, the third differential pressure setting value can be 9 kPa; and so on. Of course, the specific values ​​of the above-mentioned differential pressure setting values ​​are merely preferred values ​​for the aircraft turbine cooling control system of this application. Those skilled in the art can understand, based on the disclosure of this application, that other suitable differential pressure setting values ​​can also be used without departing from the protection scope of the claims of this application.

[0073] Ideally, this period can last from 1 to 3 weeks.

[0074] Preferably, the third differential pressure setting value can be equal to the second differential pressure setting value; or the third differential pressure setting value may not be equal to the second differential pressure setting value.

[0075] In some embodiments, such as Figures 1 to 2 As shown, the aircraft turbine refrigeration system includes a compressor, expander, primary heat exchanger, main heat exchanger, regenerator, condenser, and gas-liquid separator.

[0076] The aircraft turbine refrigeration process includes: the air from the aircraft turbine refrigeration system enters the hot side of the primary heat exchanger, is cooled by ram air and then splits into two paths. One path enters the compressor, the hot side of the main heat exchanger, the hot side of the regenerator, the hot side of the condenser, the gas-liquid separator, the cold side of the regenerator, and the expander in sequence. Then it merges with the other path of air through the temperature control valve and is discharged from the aircraft turbine refrigeration system through the cold side of the condenser.

[0077] According to the above technical solution, the aircraft turbine cooling control system of the present invention can achieve the following beneficial technical effects: through appropriate aircraft turbine cooling system layout and aircraft turbine cooling process design, it can better automatically predict ice blockage and greatly reduce the possibility of ice blockage.

[0078] In some embodiments, such as Figures 1 to 2 As shown, the aircraft turbine cooling control system also includes an air-water separator temperature sensor, which is installed on the pipeline from the air-water separator to the regenerator to monitor the temperature of the air in the air-water separator. The controller is also configured to maintain the temperature of the air in the air-water separator above the anti-icing temperature setpoint, thereby preventing the air-water separator from icing. Preferably, this anti-icing temperature setpoint is typically around 5°C.

[0079] like Figures 1 to 2 As shown, according to an embodiment of the present invention, an aircraft turbine cooling control method includes:

[0080] Monitor the pressure difference between the turbine outlet and the cabin, monitor the inlet air mass flow rate of the aircraft turbine cooling system, monitor the condenser outlet air mass flow rate of the aircraft turbine cooling system, and monitor the gas-water separator outlet mass flow rate of the aircraft turbine cooling system.

[0081] When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate.

[0082] When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed.

[0083] When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

[0084] According to the above technical solution, the aircraft turbine cooling control method of the present invention can achieve the following beneficial technical effects: it can automatically predict ice blockage and significantly reduce the possibility of ice blockage through preventive measures; it can accurately distinguish between ice blockage and dirt blockage, thereby taking targeted measures.

[0085] The specific embodiments of the present invention have been described above. However, those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. An aircraft turbine refrigeration control system, the aircraft turbine refrigeration control system comprising an outlet differential pressure sensor, an inlet mass flow sensor, a condenser mass flow sensor, a gas-liquid separator mass flow sensor, and a controller; in, The outlet differential pressure sensor is installed at the outlet of the aircraft turbine cooling system to monitor the pressure difference between the turbine outlet and the cabin. The imported mass flow sensor is installed on the inlet pipe of the aircraft turbine cooling system to monitor the mass flow of air entering the aircraft turbine cooling system. The condenser mass flow sensor is installed on the cold side outlet pipe of the condenser of the aircraft turbine refrigeration system to monitor the mass flow rate of air flowing out of the aircraft turbine refrigeration system through the condenser. The mass flow sensor of the gas-water separator is installed on the outlet pipe of the gas-water separator of the aircraft turbine refrigeration system to monitor the mass flow rate of the gas-water separator flowing out of the aircraft turbine refrigeration system. The controller is connected to the outlet differential pressure sensor, the inlet mass flow sensor, the condenser mass flow sensor, and the gas-liquid separator mass flow sensor. The controller is configured to: When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate. When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed. When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

2. The aircraft turbine cooling control system as described in claim 1, characterized in that, The first differential pressure setting value is 12-15 kPa.

3. The aircraft turbine cooling control system as described in claim 1, characterized in that, The ice-melting operation includes: increasing the opening of the temperature control valve or decreasing the opening of the ram air damper.

4. The aircraft turbine cooling control system as described in claim 1, characterized in that, The controller is also configured to: when the pressure difference between the turbine outlet and the cabin is greater than a second pressure difference setting value and less than a first pressure difference setting value, wherein the second pressure difference setting value is lower than the first pressure difference setting value, it is also determined whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate. When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a turbine outlet icing warning message is sent. When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a heat exchanger channel blockage warning message is sent.

5. The aircraft turbine cooling control system as described in claim 1, characterized in that, The controller is also configured to send a heat exchanger maintenance alarm message after the pressure difference between the turbine outlet and the cabin has exceeded the third pressure difference set value for a certain period of time.

6. The aircraft turbine cooling control system as described in claim 1, characterized in that, The aircraft turbine refrigeration system includes a compressor, an expander, a primary heat exchanger, a main heat exchanger, a regenerator, a condenser, and a gas-liquid separator. The aircraft turbine refrigeration process includes: air from the inlet of the aircraft turbine refrigeration system enters the hot side of the primary heat exchanger, is cooled by ram air and then splits into two paths. One path enters the compressor, the hot side of the main heat exchanger, the hot side of the regenerator, the hot side of the condenser, the gas-liquid separator, the cold side of the regenerator, and the expander in sequence. Then it merges with the other path of air through the temperature control valve and is discharged from the aircraft turbine refrigeration system through the cold side of the condenser.

7. A method for controlling aircraft turbine cooling, comprising: Monitor the pressure difference between the turbine outlet and the cabin, monitor the inlet air mass flow rate of the aircraft turbine cooling system, monitor the condenser outlet air mass flow rate of the aircraft turbine cooling system, and monitor the gas-water separator outlet mass flow rate of the aircraft turbine cooling system. When the pressure difference between the turbine outlet and the cabin is greater than the first pressure difference setting value, determine whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate. When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, it is determined that the turbine outlet is icing up, and de-icing operation is performed. When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, the heat exchanger channel is determined to be clogged, and a heat exchanger maintenance alarm message is sent.

8. The aircraft turbine cooling control method as described in claim 7, characterized in that, The first differential pressure setting value is 12-15 kPa.

9. The aircraft turbine cooling control method as described in claim 7, characterized in that, The ice-melting operation includes: increasing the opening of the temperature control valve or decreasing the opening of the ram air damper.

10. The aircraft turbine cooling control method as described in claim 7, characterized in that, When the pressure difference between the turbine outlet and the cabin is greater than the second pressure difference setting value and less than the first pressure difference setting value, wherein the second pressure difference setting value is lower than the first pressure difference setting value, it is also determined whether the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate. When the inlet air mass flow rate is greater than the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a turbine outlet icing warning message is sent. When the inlet air mass flow rate equals the sum of the condenser outlet air mass flow rate and the gas-water separator outlet mass flow rate, a heat exchanger channel blockage warning message is sent.

11. The aircraft turbine cooling control method as described in claim 7, characterized in that, When the pressure difference between the turbine outlet and the cabin exceeds the third pressure difference setting value for a certain period of time, a heat exchanger maintenance alarm message is also sent.

12. The aircraft turbine cooling control method as described in claim 7, characterized in that, The aircraft turbine refrigeration system includes a compressor, an expander, a primary heat exchanger, a main heat exchanger, a regenerator, a condenser, and a gas-liquid separator. The aircraft turbine refrigeration process includes: air from the inlet of the aircraft turbine refrigeration system enters the hot side of the primary heat exchanger, is cooled by ram air and then splits into two paths. One path enters the compressor, the hot side of the main heat exchanger, the hot side of the regenerator, the hot side of the condenser, the gas-liquid separator, the cold side of the regenerator, and the expander in sequence. Then it merges with the other path of air through the temperature control valve and is discharged from the aircraft turbine refrigeration system through the cold side of the condenser.

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