Aero-engine cabin cooling method

Abstract

The invention discloses an aero-engine cabin cooling method and belongs to the field of aero-engine cooling. The temperature control levels of different types of electronic components in an existing engine compartment are different, if the mode of directly ventilating and cooling the engine compartment is adopted to obtain the compartment temperature meeting the temperature control requirement, the cooling air flow needs to be increased or the temperature of cooling air needs to be reduced, and therefore the problem that the ram air heat sink capacity is insufficient is solved. The invention provides an engine compartment cooling method, aiming at the problems that the temperature of electronic components is controlled, and the problems that the performance of the aircraft is lost and the heat sink capacity is insufficient due to the fact that the cooling air flow needs to be increased or the cooling air temperature needs to be reduced are effectively solved.

Description

Technical Field

[0001] The invention belongs to the field of aircraft engine cooling, and in particular relates to an aircraft engine cabin cooling method. Background Art

[0002] The aircraft engine compartment is equipped with electronic components that ensure the normal operation of the engine, such as electrical systems and control units. Due to the limitations of the functions and performance of the components, the temperature limits of the electronic components are inconsistent. For example, the temperature limit of the lubricating oil pump is 350K, and the temperature limit of the differential pressure sensor is 400K. However, in general, the temperature limit of all electronic components does not exceed 400K. The aircraft engine compartment is affected by the aerodynamic heat of the skin, the heat of the engine barrel, and the heat of the electronic equipment, resulting in a high temperature in the compartment. If there is no effective cooling method in the compartment, the high temperature in the compartment will exceed the temperature limit that the electronic components can withstand, causing the electronic components to work abnormally or be damaged, which will seriously affect the safe operation of the engine. At present, the engine compartment is often cooled by introducing ram air from outside the aircraft. However, most of the electronic components in the engine compartment are arranged around the corresponding accessories based on the principle of proximity and displayed in the engine compartment. Different electronic components can withstand different temperature limits. If the normal operation of the electronic components in the engine compartment is to ensure, the engine compartment temperature must be controlled to the lowest temperature value among the extreme temperatures of different types of electronic components. For example, if the lowest extreme temperature of the above components is 350K and the highest extreme temperature is 400K, then the engine compartment needs to be controlled at 350K. However, the volume of the aircraft engine compartment is large. To obtain a cabin temperature level that meets the safe operating temperature of the electronic components, it is necessary to increase the flow rate of the cooling air or reduce the temperature of the cooling air. Both of the above methods will cause performance loss of the aircraft: on the one hand, excessive cooling air flow will affect the aerodynamic performance of the aircraft; on the other hand, reducing the cooling air temperature will increase the additional burden on the aircraft.

[0003] The turbogenerator is an emergency energy source. In an emergency situation where the aircraft loses its main power and auxiliary power, it extracts the kinetic energy of the ram air and provides emergency hydraulic or emergency power to the aircraft's key systems to maintain the aircraft's maneuverability. When the ram air passes through the turbogenerator, the extremely high enthalpy is converted into kinetic energy, and the temperature is reduced. The cooled ram air is generally discharged into the outside atmosphere, which undoubtedly causes a waste of cooling air. Therefore, it can be considered as a cooling source for the engine compartment.

[0004] In summary, it is necessary to explore new cooling solutions to meet the temperature control requirements of electronic components with different temperature resistance levels in the engine compartment while reducing the loss of aircraft performance caused by bleed air. Summary of the invention

[0005] In view of the different temperature control levels of different types of electronic components in the existing engine compartment, if the engine compartment is directly ventilated and cooled to obtain a compartment temperature that meets the temperature control requirements, it is necessary to increase the cooling air flow or reduce the cooling air temperature, which not only faces the problem of insufficient ram air heat sink capacity, but also reduces the performance of the aircraft. The present invention provides an engine compartment cooling method, which ensures the temperature control of electronic components while effectively solving the problems of aircraft performance loss and insufficient heat sink capacity caused by increasing the cooling air flow or reducing the cooling air temperature. Based on this purpose, the scheme provided by the present invention is as follows:

[0006] A method for cooling an aircraft engine compartment, which is implemented by an aircraft engine compartment cooling system. The aircraft engine compartment cooling system comprises an air bleed device 1, a regulating valve 2, a turbine generator 3, an exhaust gas collecting device 4, a supercharger 5, an air-to-air heat exchanger 6, an electronic compartment A7, an electronic equipment A8, an electronic compartment B9, an electronic equipment B10, an engine compartment 11, an ejector 12, an engine barrel 13, a phase-change heat storage heat exchanger 14, and an icing component 15.

[0007] The air induction device 1, the turbine generator 3, and the exhaust gas collecting device 4 are connected in sequence through pipelines, and a regulating valve 2 is arranged between the air induction device 1 and the turbine generator 3; the exhaust gas collecting device 4 is divided into two branches, one branch is connected to the supercharger 5, and a regulating valve 2 is arranged on the branch between the two, and only one regulating valve 2 is arranged on the other branch, and the two branches are connected to the air-air heat exchanger 6 through pipelines after being collected; the air-air heat exchanger 6, the electronic compartment A7, and the electronic compartment B9 are connected in sequence through pipelines; the electronic compartment A7 and the electronic compartment B9 are respectively equipped with electronic equipment A8 and electronic equipment B10; the electronic compartment A7, the electronic compartment B9, the engine barrel 13, the phase change heat storage heat exchanger 1 4 are all located in the engine compartment 11; the outlet of the electronic compartment B9 is located in the engine compartment 11, and the outlet of the engine compartment 11 is connected to the ejector 12, the phase change heat storage heat exchanger 14 inside the engine compartment 11, the phase change heat storage heat exchanger 14 outside the engine compartment 11, and the air-air heat exchanger 6 in sequence through pipelines, wherein a regulating valve 2 is arranged between the ejector 12 and the phase change heat storage heat exchanger 14 inside the engine compartment 11, and between the phase change heat storage heat exchanger 14 outside the engine compartment 11 and the air-air heat exchanger 6; the engine barrel 13 is connected in parallel with the phase change heat storage heat exchanger 14 inside the engine compartment 11; and the icing component is connected in parallel with the phase change heat storage heat exchanger 14 outside the engine compartment 11.

[0008] Furthermore, the electronic compartment A7 and the electronic compartment B9 are arranged at the rear of the engine compartment 11 , and the exit of the engine compartment 11 is arranged at the head of the engine compartment 11 .

[0009] The specific method for cooling the aircraft engine cabin is as follows: the exhaust gas discharged by the turbine generator is used as a cold source, and the cold source gas drawn out by the air induction device 1 is introduced into the turbine generator 3 after the flow rate is adjusted by the regulating valve 2 on the pipeline. After the turbine generator 3 expands and cools down due to work, if the pressure meets the requirement, the regulating valve 2 on the pipeline between the turbine generator 3 and the air-to-air heat exchanger 6 is opened to allow the exhaust gas to enter the air-to-air heat exchanger 6. If the pressure does not meet the requirement, the regulating valve 2 between the turbine generator 3 and the supercharger 5 is opened to increase the pressure through the supercharger 5. And then enters the air-air heat exchanger 6; if the temperature of the exhaust gas entering the air-air heat exchanger 6 meets the requirements, it will enter the electronic compartment A7 and the electronic compartment B9 in turn to cool the electronic equipment A8 and the electronic equipment B10 respectively, and then be discharged into the engine compartment 11; if the temperature does not meet the requirements, the phase change heat storage heat exchanger 14 outside the engine compartment 11 and the regulating valve 2 on the pipeline between it and the air-air heat exchanger 6 will be opened to introduce the cooled exhaust gas into the air-air heat exchanger 6 to cool the cold source gas of the turbine generator 3. The exhaust gas entering the engine compartment 11 flows from the tail of the engine compartment 11 to the head of the engine compartment 11 under the action of the ejector 12, and after enhanced convective heat exchange with other equipment in the engine compartment 11, it is discharged into the phase change heat storage heat exchanger 14 connected in parallel with the engine barrel 13 through the ejector 12, and the high-temperature heat source absorbed from the engine barrel 13 and stored in the phase change heat storage heat exchanger 14 is taken away. The heated exhaust gas enters the phase change heat storage heat exchanger 14 connected in parallel with the icing component 15, and the heat is absorbed by the phase change heat storage heat exchanger 14 and then transferred to the icing component 15. The temperature is relatively low. The cooled exhaust gas enters the air-to-air heat exchanger 6 through the regulating valve 2 as appropriate to re-cool the exhaust gas discharged from the turbine generator 3.

[0010] Compared with the prior art, the present invention has the following advantages:

[0011] 1) Using the exhaust gas from the turbine generator as a cooling source to achieve the reuse of the exhaust gas, increase the available air heat sink, and reduce the loss of aircraft performance caused by additional ram air bleed;

[0012] 2) Introducing a supercharger and air-to-air heat exchanger to timely readjust the pressure and temperature of the low-temperature air discharged from the turbine generator, thus meeting the demand for cooling air at the cabin temperature control level at different times;

[0013] 3) According to the temperature resistance level of the components, the components are classified and arranged in the electronic compartment set in the engine compartment. The "cabin-in-cabin" sealing method is adopted to control the temperature according to the temperature resistance level of the electronic equipment in the electronic compartment, thereby reducing the waste of cooling medium caused by the traditional arrangement method. At the same time, the nested electronic compartment is arranged at the tail of the engine compartment, which is convenient for introducing the cooling air after cooling the electronic compartment into the head of the engine compartment for recirculation to cool other pipeline equipment in the engine compartment;

[0014] 4) Introduce a phase-change heat storage heat exchanger, and utilize the property that the solid-liquid phase change material absorbs heat while maintaining a constant temperature when it melts, so as to store the heat of the engine barrel in the phase change material, reduce the radiation and convection heat dissipation of the engine barrel to the engine compartment and the electronic compartment, and thus reduce the amount of cooling medium used; utilize the property that the solid-liquid phase change material absorbs heat while maintaining a constant temperature when it solidifies, and store the heat of the air in the phase change material and transfer it to the icing parts, which is used for anti-icing while also reducing the temperature of the air. The cooled air can be used to cool the exhaust gas of the turbine engine as needed, thus realizing the recycling and reuse of the cooling air. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the composition of an engine compartment cooling system of the present invention;

[0016] In the figure, 1-air induction device, 2-regulating valve, 3-turbine generator, 4-exhaust collecting device, 5-supercharger, 6-air-air heat exchanger, 7-electronic compartment A, 8-electronic equipment A, 9-electronic compartment B, 10-electronic equipment B, 11-engine compartment, 12-ejector, 13-engine barrel, 14-phase change heat storage heat exchanger, 15-icing component. DETAILED DESCRIPTION

[0017] The present invention is further described below in conjunction with the examples and drawings. The examples are intended to explain the present invention and should not be construed as limiting the present invention.

[0018] like Figure 1 As shown, a method for cooling an aircraft engine compartment is implemented by an aircraft engine compartment cooling system, and the aircraft engine compartment cooling system includes an air bleed device 1, a regulating valve 2, a turbine generator 3, an exhaust gas collecting device 4, a supercharger 5, an air-to-air heat exchanger 6, an electronic compartment A7, an electronic equipment A8, an electronic compartment B9, an electronic equipment B10, an engine compartment 11, an ejector 12, an engine barrel 13, a phase change heat storage heat exchanger 14, and an icing component 15.

[0019] The air induction device 1, the turbine generator 3, and the exhaust gas collecting device 4 are connected in sequence through pipelines, and a regulating valve 2 is arranged between the air induction device 1 and the turbine generator 3; the exhaust gas collecting device 4 is divided into two branches, one branch is connected to the supercharger 5, and a regulating valve 2 is arranged on the branch between the two, and only one regulating valve 2 is arranged on the other branch, and the two branches are connected to the air-air heat exchanger 6 through pipelines after being collected; the air-air heat exchanger 6, the electronic compartment A7, and the electronic compartment B9 are connected in sequence through pipelines; the electronic compartment A7 and the electronic compartment B9 are respectively equipped with electronic equipment A8 and electronic equipment B10; the electronic compartment A7, the electronic compartment B9, the engine barrel 13, the phase change heat storage heat exchanger 1 4 are all located in the engine compartment 11; the outlet of the electronic compartment B9 is located in the engine compartment 11, and the outlet of the engine compartment 11 is connected to the ejector 12, the phase change heat storage heat exchanger 14 inside the engine compartment 11, the phase change heat storage heat exchanger 14 outside the engine compartment 11, and the air-air heat exchanger 6 in sequence through pipelines, wherein a regulating valve 2 is arranged between the ejector 12 and the phase change heat storage heat exchanger 14 inside the engine compartment 11, and between the phase change heat storage heat exchanger 14 outside the engine compartment 11 and the air-air heat exchanger 6; the engine barrel 13 is connected in parallel with the phase change heat storage heat exchanger 14 inside the engine compartment 11; and the icing component is connected in parallel with the phase change heat storage heat exchanger 14 outside the engine compartment 11.

[0020] The electronic compartment A7 and the electronic compartment B9 are arranged at the rear of the engine compartment 11 , and the exit of the engine compartment 11 is arranged at the head of the engine compartment 11 .

[0021] Assume T 1 Indicates the temperature control temperature of the electronic compartment A7, T 2 Indicates the temperature control temperature of the electronic compartment B9, T 3 represents the temperature control temperature of the engine compartment 11; T 1 <T 2 <T 3 .

[0022] The engine barrel 13 refers to the location of the combustion chamber; the air-air heat exchanger 6 is a shell and tube heat exchanger; the phase change heat storage heat exchanger 14 is a tube bundle heat exchanger, the tube bundle is filled with air, the outside of the tube bundle is wrapped with solid-liquid phase change material, and the space between the phase change material and the tube bundle is filled with elastic material to balance the volume change of the phase change material during heat absorption and heat release.

[0023] The icing component 15 is a component or structure on the aircraft that is prone to icing.

[0024] The specific method for cooling the aircraft engine cabin is as follows: the exhaust gas discharged by the turbine generator is used as a cold source, and the cold source gas drawn out by the air induction device 1 is introduced into the turbine generator 3 after the flow rate is adjusted by the regulating valve 2 on the pipeline. After the turbine generator 3 expands and cools down due to work, if the pressure meets the requirement, the regulating valve 2 on the pipeline between the turbine generator 3 and the air-to-air heat exchanger 6 is opened to allow the exhaust gas to enter the air-to-air heat exchanger 6. If the pressure does not meet the requirement, the regulating valve 2 between the turbine generator 3 and the supercharger 5 is opened to increase the pressure through the supercharger 5. And then enters the air-air heat exchanger 6; if the temperature of the exhaust gas entering the air-air heat exchanger 6 meets the requirements, it will enter the electronic compartment A7 and the electronic compartment B9 in turn to cool the electronic equipment A8 and the electronic equipment B10 respectively, and then be discharged into the engine compartment 11; if the temperature does not meet the requirements, the phase change heat storage heat exchanger 14 outside the engine compartment 11 and the regulating valve 2 on the pipeline between it and the air-air heat exchanger 6 will be opened to introduce the cooled exhaust gas into the air-air heat exchanger 6 to cool the cold source gas of the turbine generator 3. The exhaust gas entering the engine compartment 11 flows from the tail of the engine compartment 11 to the head of the engine compartment 11 under the action of the ejector 12, and after enhanced convective heat exchange with other equipment in the engine compartment 11, it is discharged into the phase change heat storage heat exchanger 14 connected in parallel with the engine barrel 13 through the ejector 12, and the high-temperature heat source absorbed from the engine barrel 13 and stored in the phase change heat storage heat exchanger 14 is taken away. The heated exhaust gas enters the phase change heat storage heat exchanger 14 connected in parallel with the icing component 15, and the heat is absorbed by the phase change heat storage heat exchanger 14 and then transferred to the icing component 15. The temperature is relatively low. The cooled exhaust gas enters the air-to-air heat exchanger 6 through the regulating valve 2 as appropriate to re-cool the exhaust gas discharged from the turbine generator 3.

Claims

1. A method for cooling an aircraft engine compartment, characterized in that: The aircraft engine cabin cooling method is implemented by an aircraft engine cabin cooling system, and the aircraft engine cabin cooling system comprises an air bleed device (1), a regulating valve (2), a turbine generator (3), an exhaust gas collecting device (4), a supercharger (5), an air-to-air heat exchanger (6), an electronic compartment A (7), an electronic device A (8), an electronic compartment B (9), an electronic device B (10), an engine compartment (11), an ejector (12), an engine barrel (13), a phase change heat storage heat exchanger (14), and an icing component (15); The air induction device (1), the turbine generator (3), and the exhaust gas collecting device (4) are connected in sequence through pipelines, and a regulating valve (2) is arranged between the air induction device (1) and the turbine generator (3); the exhaust gas collecting device (4) is divided into two branches, one branch is connected to the supercharger (5), and a regulating valve (2) is arranged on the branch between the two, and only one regulating valve (2) is arranged on the other branch, and the two branches are connected to the air-air heat exchanger (6) through pipelines after being combined; the air-air heat exchanger (6), the electronic compartment A (7), and the electronic compartment B (9) are connected in sequence through pipelines; the electronic compartment A (7) and the electronic compartment B (9) are respectively equipped with electronic equipment A (8) and electronic equipment B (10); the electronic compartment A (7), the electronic compartment B (9), the engine barrel (13), and the phase change heat storage heat exchanger (14 ) are both located in the engine compartment (11); the outlet of the electronic compartment B (9) is located in the engine compartment (11); the outlet of the engine compartment (11) is connected to the ejector (12), the phase change heat storage heat exchanger (14) inside the engine compartment (11), the phase change heat storage heat exchanger (14) outside the engine compartment (11), and the air-air heat exchanger (6) in sequence through a pipeline, wherein a regulating valve (2) is provided between the ejector (12) and the phase change heat storage heat exchanger (14) inside the engine compartment (11), and between the phase change heat storage heat exchanger (14) outside the engine compartment (11) and the air-air heat exchanger (6); the engine barrel (13) is connected in parallel with the phase change heat storage heat exchanger (14) inside the engine compartment (11); and the icing component is connected in parallel with the phase change heat storage heat exchanger (14) outside the engine compartment (11); The specific method for cooling the cabin of an aircraft engine is as follows: the exhaust gas discharged by the turbine generator is used as a cold source, and the cold source gas drawn out by the air induction device (1) is introduced into the turbine generator (3) after the flow rate is adjusted by the regulating valve (2) on the pipeline. After the turbine generator (3) expands and cools down due to work, if the pressure meets the requirement, the regulating valve (2) on the pipeline between the turbine generator (3) and the air-to-air heat exchanger (6) is opened to allow the exhaust gas to enter the air-to-air heat exchanger (6). If the pressure does not meet the requirement, the turbine generator (3) is opened to allow the exhaust gas to enter the air-to-air heat exchanger (6). The regulating valve (2) between the turbine generator (3) and the supercharger (5) is pressurized by the supercharger (5) and then enters the air-to-air heat exchanger (6); if the temperature of the exhaust gas entering the air-to-air heat exchanger (6) meets the requirements, it enters the electronic compartment A (7) and the electronic compartment B (9) in turn to cool the electronic equipment A (8) and the electronic equipment B (10) respectively, and then is discharged into the engine compartment (11); if the temperature does not meet the requirements, the phase change heat storage heat exchanger (14) outside the engine compartment (11) is opened. and a regulating valve (2) on the pipeline between the exhaust gas and the air-to-air heat exchanger (6), which introduces the cooled exhaust gas into the air-to-air heat exchanger (6) to cool the cold source gas of the turbine generator (3); the exhaust gas entering the engine compartment (11) flows from the tail of the engine compartment (11) to the head of the engine compartment (11) under the action of the ejector (12), and after strengthening the convection heat exchange with other equipment in the engine compartment (11), it is discharged into the exhaust gas connected in parallel with the engine barrel (13) through the ejector (12). The phase-change heat storage heat exchanger (14) takes away the high-temperature heat source absorbed from the engine barrel (13) and stored in the phase-change heat storage heat exchanger (14). The heated exhaust gas enters the phase-change heat storage heat exchanger (14) connected in parallel with the icing component (15). After the heat is absorbed by the phase-change heat storage heat exchanger (14), it is transferred to the icing component (15). The temperature of the cooled exhaust gas is relatively low. The cooled exhaust gas enters the air-to-air heat exchanger (6) through the regulating valve (2) as appropriate to re-cool the exhaust gas discharged from the turbine generator (3).

2. The method for cooling an aircraft engine compartment according to claim 1, characterized in that: The electronic compartment A (7) and the electronic compartment B (9) are arranged at the rear of the engine compartment (11), and the outlet of the engine compartment (11) is arranged at the head of the engine compartment (11).

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