A method of cooling an aircraft engine compartment

Abstract

The application discloses an aero-engine cabin cooling method and belongs to the field of aero-engine cooling. In view of the fact that different kinds of electronic components in the existing engine cabin have different temperature control levels, if a direct ventilation cooling mode is adopted to obtain cabin temperature meeting the temperature control requirement, the cooling air flow needs to be increased or the cooling air temperature needs to be reduced, which not only faces the problem of insufficient ram air heat sink capacity, but also reduces the performance of the aircraft. The application provides the aero-engine cabin cooling method, which can effectively solve the problems of the performance loss of the aircraft caused by the increase of the cooling air flow or the reduction of the cooling air temperature and the insufficient heat sink capacity and the like while ensuring the temperature control of the electronic components.

Description

Technical Field

[0001] This invention belongs to the field of aircraft engine cooling, and specifically relates to a method for cooling an aircraft engine compartment. Background Technology

[0002] The aircraft engine nacelle houses electronic components that ensure the engine's normal operation, such as electrical systems and control units. Due to limitations in their functions and performance, these components have varying temperature limits. For example, the oil pump's temperature limit is 350K, and the differential pressure sensor's is 400K. However, overall, the temperature limit of all electronic components does not exceed 400K. The aircraft engine nacelle is affected by aerodynamic heat from the skin, engine casing, and electronic equipment, resulting in high internal temperatures. If there is no effective cooling system, the high temperature inside the nacelle will exceed the temperature limits that the electronic components can withstand, causing malfunctions or damage, and in severe cases, affecting the engine's operational safety. Currently, ram air is commonly introduced from outside the aircraft to dissipate heat from the engine compartment. However, most electronic components in the engine compartment are arranged around their respective accessories based on proximity, and different electronic components have different temperature limits. To ensure the normal operation of these electronic components, the engine compartment temperature must be controlled at the lowest possible temperature among the extreme temperatures of different types of electronic components. For example, if the lowest extreme temperature limit for the aforementioned components is 350K and the highest is 400K, then the engine compartment temperature needs to be controlled at 350K. However, aircraft engine compartments are relatively large. To achieve a compartment temperature level that meets the safe operating temperature of electronic components, it is necessary to increase the flow rate of cooling air or decrease its temperature. Both of these methods will lead to performance losses for the aircraft: on the one hand, excessive cooling air flow will affect the aircraft's aerodynamic performance; on the other hand, decreasing the cooling air temperature will increase the aircraft's workload.

[0003] A turbine generator is an emergency energy source. In emergencies where an aircraft loses its main and auxiliary power, it extracts the kinetic energy of ram air to provide emergency hydraulic or electrical power to critical aircraft systems to maintain the aircraft's maneuverability. When ram air passes through the turbine generator, its extremely high enthalpy is converted into kinetic energy, and its temperature decreases. The cooled ram air is usually discharged into the outside atmosphere, which undoubtedly wastes cooling air. Therefore, it can be considered as a cooling source for the engine nacelle.

[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] Given the varying temperature control levels of different electronic components within existing engine nacelles, directly ventilating and cooling the engine nacelle to achieve the required temperature necessitates either increasing the cooling airflow or decreasing the cooling air temperature. This not only faces the problem of insufficient ram air heat sink capacity but also reduces aircraft performance. This invention provides an engine nacelle cooling method that effectively solves the performance loss and insufficient heat sink capacity issues caused by increasing cooling airflow or decreasing cooling air temperature while ensuring temperature control of electronic components. Based on this objective, the solution provided by this invention is as follows:

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

[0007] The bleed air device 1, turbine generator 3, and exhaust gas collection device 4 are connected in sequence via pipelines. A regulating valve 2 is installed between the bleed air device 1 and the turbine generator 3. The exhaust gas collection device 4 has two branches. One branch is connected to the turbocharger 5, and a regulating valve 2 is installed on the branch between the two. The other branch has only one regulating valve 2. The two branches are connected to the air-to-air heat exchanger 6 via pipelines. The air-to-air heat exchanger 6, electronics compartment A7, and electronics compartment B9 are connected in sequence via pipelines. Electronic compartment A7 and electronics compartment B9 are respectively equipped with electronic equipment A8 and electronic equipment B10. Electronic compartment A7, electronic compartment B9, engine housing 13, and phase change heat storage heat exchanger 1 are also mentioned. All four are located inside the engine compartment 11; the outlet of the electronics compartment B9 is located inside the engine compartment 11, and the outlet of the engine compartment 11 is connected in sequence 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-to-air heat exchanger 6 via pipes. A regulating valve 2 is installed 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-to-air heat exchanger 6. The engine cylinder 13 is connected in parallel with the phase change heat storage heat exchanger 14 inside the engine compartment 11; the icing component is connected in parallel with the phase change heat storage heat exchanger 14 outside the engine compartment 11.

[0008] Furthermore, electronic compartments A7 and B9 are located at the rear of engine compartment 11, and the outlet of engine compartment 11 is located at the front of engine compartment 11.

[0009] The specific cooling method for the aircraft engine compartment is as follows: The exhaust gas discharged from the turbine generator serves as a cold source. The cold source gas drawn from the bleed air device 1 is introduced into the turbine generator 3 after the flow rate is regulated by the regulating valve 2 on the pipeline. After the turbine generator 3 expands and cools down by doing work, if the pressure meets the requirements, 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 requirements, the regulating valve 2 between the turbine generator 3 and the supercharger 5 is opened to pressurize the gas through the supercharger 5. Then it 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 electronics compartment A7 and electronics compartment B9 in sequence to cool the electronic equipment A8 and electronic equipment B10 respectively before being 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 its pipeline with the air-to-air heat exchanger 6 are opened to introduce 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 rear of the engine compartment 11 to the front of the engine compartment 11 under the action of the ejector 12. After enhancing the convective heat exchange of 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 casing 13 through the ejector 12. The high-temperature heat source absorbed and stored in the phase change heat storage heat exchanger 14 from the engine casing 13 is carried away. The heated exhaust gas enters the phase change heat storage heat exchanger 14 connected in parallel with the icing component 15. After the phase change heat storage heat exchanger 14 absorbs heat, it is transferred to the icing component 15. The temperature is low. The cooled exhaust gas enters the air-to-air heat exchanger 6 through the regulating valve 2 to recool 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 cold source enables the reuse of exhaust gas, increases the available air heat sink, and reduces the loss of aircraft performance caused by additional ram air bleed air.

[0012] 2) By introducing a turbocharger and an air-to-air heat exchanger, the pressure and temperature of the low-temperature air discharged from the turbine generator are readjusted in a timely manner to meet the cooling air requirements of the cabin temperature control level at different times.

[0013] 3) Based on the temperature resistance level of the components, the components are classified and arranged in the electronic compartments set up in the engine compartment. The "compartment-within-a-compartment" sealing method is adopted to control the temperature of the electronic equipment in the electronic compartment according to the temperature resistance level. This reduces the waste of cooling fluid caused by the traditional arrangement method. At the same time, the nested electronic compartments are arranged at the rear of the engine compartment, which facilitates the introduction of the cooling air after cooling the electronic compartments into the front of the engine compartment for recirculation, so as to cool other pipeline equipment in the engine compartment.

[0014] 4) Introducing a phase change heat storage heat exchanger utilizes the property that the temperature remains constant when the solid-liquid phase change material melts and absorbs heat. The heat of the engine casing is stored in the phase change material, reducing the radiation and convection heat dissipation of the engine casing to the engine compartment and electronics compartment, thereby reducing the amount of cooling fluid used. Utilizing the property that the solid-liquid phase change material absorbs heat and remains constant when it solidifies, the heat of the air is stored in the phase change material and transferred to the icing components. This serves to prevent icing while also lowering the air temperature. The cooled air is then used to cool the exhaust of the turbine engine as needed, achieving the recycling of cooling air. Attached Figure Description

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

[0016] In the diagram, 1-Break air device, 2-Regulating valve, 3-Turbine generator, 4-Exhaust gas collection device, 5-Supercharger, 6-Air-to-air heat exchanger, 7-Electronics compartment A, 8-Electronics device A, 9-Electronics compartment B, 10-Electronics device B, 11-Engine compartment, 12-Ejector, 13-Engine housing, 14-Phase change heat storage heat exchanger, 15-Icing component. Detailed Implementation

[0017] The present invention will be further described below with reference to embodiments and accompanying drawings. These embodiments are intended to explain the present invention and should not be construed as limiting the invention.

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

[0019] The bleed air device 1, turbine generator 3, and exhaust gas collection device 4 are connected in sequence via pipelines. A regulating valve 2 is installed between the bleed air device 1 and the turbine generator 3. The exhaust gas collection device 4 has two branches. One branch is connected to the turbocharger 5, and a regulating valve 2 is installed on the branch between the two. The other branch has only one regulating valve 2. The two branches are connected to the air-to-air heat exchanger 6 via pipelines. The air-to-air heat exchanger 6, electronics compartment A7, and electronics compartment B9 are connected in sequence via pipelines. Electronic compartment A7 and electronics compartment B9 are respectively equipped with electronic equipment A8 and electronic equipment B10. Electronic compartment A7, electronic compartment B9, engine housing 13, and phase change heat storage heat exchanger 1 are also mentioned. All four are located inside the engine compartment 11; the outlet of the electronics compartment B9 is located inside the engine compartment 11, and the outlet of the engine compartment 11 is connected in sequence 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-to-air heat exchanger 6 via pipes. A regulating valve 2 is installed 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-to-air heat exchanger 6. The engine cylinder 13 is connected in parallel with the phase change heat storage heat exchanger 14 inside the engine compartment 11; the icing component is connected in parallel with the phase change heat storage heat exchanger 14 outside the engine compartment 11.

[0020] Electronics compartments A7 and B9 are located at the rear of engine compartment 11, and the exit of engine compartment 11 is located at the front of engine compartment 11.

[0021] Let T1 represent the temperature control temperature of electronic compartment A7, T2 represent the temperature control temperature of electronic compartment B9, and T3 represent the temperature control temperature of engine compartment 11; T1 < T2 < T3.

[0022] The engine casing 13 refers to the location of the combustion chamber; the air-to-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, with air inside the tube bundle and solid-liquid phase change material wrapped around the outside of the tube bundle, and elastic material filling the space between the phase change material and the tube bundle to balance the volume change of the phase change material during heat absorption and release.

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

[0024] The specific cooling method for the aircraft engine compartment is as follows: The exhaust gas discharged from the turbine generator serves as a cold source. The cold source gas drawn from the bleed air device 1 is introduced into the turbine generator 3 after the flow rate is regulated by the regulating valve 2 on the pipeline. After the turbine generator 3 expands and cools down by doing work, if the pressure meets the requirements, 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 requirements, the regulating valve 2 between the turbine generator 3 and the supercharger 5 is opened to pressurize the gas through the supercharger 5. Then it 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 electronics compartment A7 and electronics compartment B9 in sequence to cool the electronic equipment A8 and electronic equipment B10 respectively before being 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 its pipeline with the air-to-air heat exchanger 6 are opened to introduce 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 rear of the engine compartment 11 to the front of the engine compartment 11 under the action of the ejector 12. After enhancing the convective heat exchange of 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 casing 13 through the ejector 12. The high-temperature heat source absorbed and stored in the phase change heat storage heat exchanger 14 from the engine casing 13 is carried away. The heated exhaust gas enters the phase change heat storage heat exchanger 14 connected in parallel with the icing component 15. After the phase change heat storage heat exchanger 14 absorbs heat, it is transferred to the icing component 15. The temperature is low. The cooled exhaust gas enters the air-to-air heat exchanger 6 through the regulating valve 2 to recool the exhaust gas discharged from the turbine generator 3.

Claims

1. A method for cooling an aircraft engine compartment, characterized in that, The aforementioned aircraft engine compartment cooling method is implemented by an aircraft engine compartment cooling system, which includes an air bleed device (1), a regulating valve (2), a turbine generator (3), an exhaust collection device (4), a supercharger (5), an air-to-air heat exchanger (6), an electronics compartment A (7), an electronic device A (8), an electronics compartment B (9), an electronic device B (10), an engine compartment (11), an ejector (12), an engine housing (13), a phase change heat storage heat exchanger (14), and an icing component (15). The bleed air device (1), turbine generator (3), and exhaust collection device (4) are connected in sequence through pipes. A regulating valve (2) is installed between the bleed air device (1) and the turbine generator (3). The exhaust collection device (4) is divided into two branches. One branch is connected to the turbocharger (5). A regulating valve (2) is installed on the branch between the two. Only one regulating valve (2) is installed on the other branch. The two branches are connected to the air-to-air heat exchanger (6) through pipes. The air-to-air heat exchanger (6), electronic compartment A (7), and electronic compartment B (9) are connected in sequence through pipes. Electronic compartment A (7) and electronic compartment B (9) are respectively equipped with electronic equipment A (8) and electronic equipment B (10). Electronic compartment A (7), electronic compartment B (9), engine cylinder (13), and phase change heat storage heat exchanger (14) All are located inside the engine compartment (11); the outlet of the electronic compartment B (9) is located inside the engine compartment (11), and the outlet of the engine compartment (11) is connected in sequence 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-to-air heat exchanger (6) through pipes. Among them, 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-to-air heat exchanger (6); the engine cylinder (13) is connected in parallel with the phase change heat storage heat exchanger (14) inside the engine compartment (11); the icing component is connected in parallel with the phase change heat storage heat exchanger (14) outside the engine compartment (11); The specific cooling method for the aircraft engine compartment is as follows: The exhaust gas discharged from the turbine generator is used as a cold source. The cold source gas drawn out by the bleed air device (1) is introduced into the turbine generator (3) after the flow rate is regulated by the regulating valve (2) on the pipeline. After the turbine generator (3) expands and cools down by doing work, if the pressure meets the requirements, 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 requirements, the turbine generator (3) is opened. The regulating valve (2) between the turbine generator (3) and the turbocharger (5) pressurizes the gas before it enters the air-to-air heat exchanger (6). The exhaust gas entering the air-to-air heat exchanger (6), if the temperature meets the requirements, enters the electronic compartment A (7) and electronic compartment B (9) in sequence to cool the electronic equipment A (8) and electronic equipment B (10) respectively before being 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 the regulating valve (2) on its pipeline with the air-to-air heat exchanger (6) 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 enhancing the convective heat exchange of other equipment in the engine compartment (11), it is discharged into the pipeline connected in parallel with the engine casing (13) via the ejector (12). The phase change heat storage heat exchanger (14) will carry away the high-temperature heat source absorbed and stored in the phase change heat storage heat exchanger (14) from the engine casing (13). The heated exhaust gas enters the phase change heat storage heat exchanger (14) connected in parallel with the icing component (15). After the phase change heat storage heat exchanger (14) absorbs heat, it is transferred to the icing component (15). The temperature is low. The cooled exhaust gas enters the air-to-air heat exchanger (6) through the regulating valve (2) as needed 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, Electronics compartment A (7) and electronic compartment B (9) are located at the rear of engine compartment (11), and the outlet of engine compartment (11) is located at the front of engine compartment (11).

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