Heat dissipation system

Abstract

To provide a heat dissipation system for properly dissipating heat generated in an aircraft while suppressing deterioration in flight performance of the aircraft.SOLUTION: In this heat dissipation system for dissipating heat generated in an aircraft, the aircraft has an intake flow path for circulating air taken in from an intake duct toward an engine, and includes a heat exchanger which is provided in a space formed between the intake flow path and the engine and which is fixed to an inner wall side of the intake flow path with a gap provided between the heat exchanger and the engine.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to aircraft heat rejection systems. [Background technology]

[0002] BACKGROUND ART Conventionally, as a heat exhaust system for an aircraft, an aircraft-mounted refrigeration unit in which a heat exchanger is disposed at an external exhaust port for discharging pressurized air inside the aircraft has been known (see, for example, Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Publication No. 1-144763 Summary of the Invention [Problem to be solved by the invention]

[0004] Electronic devices installed on aircraft are required to have improved performance, and as performance improves, the amount of heat generated increases, which in turn increases the required cooling performance. To increase cooling performance, it is necessary to enlarge the opening of the air intakes installed on the aircraft in order to increase the amount of air taken into the aircraft. However, enlarging the opening of the air intakes may reduce the aircraft's flight performance.

[0005] Therefore, an object of the present disclosure is to provide a heat dissipation system that can appropriately dissipate heat generated by an aircraft while suppressing a decline in the aircraft's flight performance. [Means for solving the problem]

[0006] The heat dissipation system disclosed herein is a heat dissipation system that dissipates heat generated in an aircraft, wherein the aircraft has an intake flow path that circulates air taken in from an intake duct toward an engine, and is equipped with a heat exchanger that is provided in a space formed between the intake flow path and the engine and is fixed to the inner wall side of the intake flow path with a gap between it and the engine. [Effects of the Invention]

[0007] According to the present disclosure, heat generated by an aircraft can be appropriately discharged while suppressing a decrease in the aircraft's flight performance. [Brief explanation of the drawings]

[0008] [Figure 1] FIG. 1 is a diagram relating to a heat exhaust system according to a first embodiment. [Figure 2] FIG. 2 is a side view schematically showing the periphery of a heat exchanger of the heat exhaust system. [Figure 3] FIG. 3 is a cross-sectional view schematically showing the periphery of a heat exchanger of the heat exhaust system. [Figure 4] FIG. 4 is a diagram relating to a heat exhaust system according to the second embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0009] Hereinafter, embodiments of the present disclosure will be described in detail with reference to the drawings. However, this disclosure is not limited to these embodiments. Furthermore, the components in the following embodiments include those that are easily replaceable by those skilled in the art, or those that are substantially identical. Furthermore, the components described below can be combined as appropriate, and when there are multiple embodiments, the respective embodiments can also be combined.

[0010] [First embodiment] The heat exhaust system according to the first embodiment is a system for exhausting heat generated in an aircraft. The heat exhaust system will be described with reference to FIG.

[0011] (Thermal Management System) Fig. 1 is a diagram of a heat exhaust system according to a first embodiment. As shown in Fig. 1, the heat exhaust system 10 is, for example, an air cycle air conditioning system (ACS). The heat exhaust system 10 extracts air taken in by an engine 5 of an aircraft, cools the extracted air, and then supplies it as conditioned air to a pressurized space inside the aircraft.

[0012] The heat exhaust system 10 includes an extraction line 21, a heat exchanger 22, an air supply line 23, a cooling system 24, a bypass line 25, and a flow control valve 26.

[0013] The bleed air line 21 is a line that leads from the engine 5 to the heat exchanger 22, and serves as a flow path for circulating air bled from the engine 5 to the heat exchanger 22. The heat exchanger 22 is a heat exchanger that cools the air bled through the bleed air line. The heat exchanger 22 is attached to an engine bay 6 that houses the engine 5. The engine bay 6 is connected to an intake duct (air intake duct) 7 of the aircraft, and serves as part of an intake flow path that circulates air from the intake duct 7 toward the engine 5.

[0014] Here, the arrangement of the heat exchanger 22 will be described with reference to Figs. 2 and 3. Fig. 2 is a side view that schematically shows the periphery of the heat exchanger of the heat exhaust system. Fig. 3 is a cross-sectional view that schematically shows the periphery of the heat exchanger of the heat exhaust system. Fig. 2 is a cross-section taken along the air flow direction, and Fig. 3 is a cross-section taken along a plane perpendicular to the air flow direction. As shown in Fig. 2, the heat exchanger 22 is arranged in a space formed between the engine bay 6 and the engine 5, and is fixed to the inner wall side of the engine bay 6. Therefore, a gap is formed between the heat exchanger 22 and the engine 5, and air flows through this gap.

[0015] As shown in Fig. 3, the engine bay 6 has a circular flow passage cross section. The heat exchanger 22 is provided in an arc shape along the inner wall of the engine bay 6. In this case, components 8 attached to the engine 5 are provided on the engine 5 so as to protrude downward (toward the lower side in Fig. 3) from the engine 5. Therefore, the heat exchanger 22 is provided so as to extend from one side surface of the engine bay 6, passing through the upper part, to the other side surface, so as to avoid the components 8. The heat exchanger 22 may be divided into multiple parts, for example, it may be divided into left and right parts centered on the center of the engine bay 6.

[0016] Furthermore, although a single heat exchanger 22 is disposed in the engine bay 6 in the first embodiment, multiple heat exchangers 22 may be disposed in the engine bay 6. The multiple heat exchangers 22 may include a water-cooled heat exchanger through which a liquid-phase refrigerant flows, an air-cooled heat exchanger through which a gas-phase refrigerant flows, and an oil-cooled heat exchanger through which oil such as lubricating oil or hydraulic oil flows. In this case, water-cooled heat exchangers are mainly used at temperatures below 100°C, which is the boiling point of water, while the bleed air passing through air-cooled heat exchangers often reaches temperatures above 100°C. Therefore, by disposing the water-cooled heat exchanger upstream of the engine bay 6 in the direction of air flow, efficient cooling is possible.

[0017] The heat exchanger 22 cools the air flowing through the extraction line 21 by exchanging heat between the air flowing through the extraction line 21 and the air taken in from the intake duct 7.

[0018] The air supply line 23 is a line leading from the heat exchanger 22 to the pressurized space, and serves as a flow path for circulating air exhausted from the heat exchanger 22 into the pressurized space. Electronic devices that generate heat in the aircraft are installed in the pressurized space, and the air supplied to the pressurized space is used to cool the electronic devices. The cooling system 24 is installed in the air supply line 23 and cools the air circulating through the air supply line 23. The cooling system 24 is, for example, a heat exchanger that exchanges heat with air taken in from the intake duct 7. The air supplied to the pressurized space where the electronic devices are installed is used to regulate the temperature of the aircraft's cockpit and cool the electronic devices, thereby appropriately dissipating heat generated in the aircraft. Therefore, it is not necessary to enlarge the opening of the air intake, which was necessary in conventional technology, to generate air for regulating the cockpit temperature and cooling the electronic devices, and it is therefore possible to appropriately dissipate heat generated in the aircraft while suppressing a decrease in the aircraft's flight performance.

[0019] The bypass line 25 is connected to the bleed air line 21 and is a line that bypasses the heat exchanger 22. A flow rate control valve 26 is provided in the bleed air line 21 and adjusts the flow rate of air flowing through the bypass line 25. The bypass line 25 causes the air in the bleed air line 21 to flow while bypassing the heat exchanger 22 when the temperature of the air flowing in from the intake duct 7 is high and it is difficult for the heat exchanger 22 to sufficiently cool the air flowing through the bleed air line 21.

[0020] In the above-described exhaust heat system 10, the air taken in from the intake duct 7 for use in the engine 5 can also be used to cool the heat exchanger 22.

[0021] [Second embodiment] Next, a heat exhaust system 30 according to a second embodiment will be described with reference to Fig. 4. Fig. 2 is a diagram of the heat exhaust system according to the second embodiment. In the second embodiment, to avoid redundant description, only parts different from the first embodiment will be described, and parts having the same configuration as the first embodiment will be described using the same reference numerals.

[0022] In the second embodiment, the heat exhaust system 30 has a heat exchanger 22 of the heat exhaust system 10 provided in a branch passage 31 branching off from the intake duct 7, and the branch passage 31 has a movable vane 32 that adjusts the air flow rate.

[0023] The branch passage 31 is connected to the intake duct 7 and is disposed parallel to the engine bay 6. The movable vanes 32 adjust the flow rate of air flowing through the branch passage 31, thereby adjusting the cooling provided by the heat exchanger 22. Furthermore, by adjusting the flow rate of air flowing through the branch passage 31, the movable vanes 32 can reduce pressure loss in the engine bay 6 and the branch passage 31. The movable vanes 32 adjust the flow rate of the branch passage 31 based on the flow rate and temperature of bleed air from the engine 5 and the aircraft speed and altitude, so as to ensure sufficient cooling required by the heat exchanger 22.

[0024] As described above, the heat exhaust systems 10 and 30 according to the first and second embodiments can be understood, for example, as follows.

[0025] The heat dissipation system 10 of the first embodiment is a heat dissipation system 10, 30 that dissipates heat generated in an aircraft, the aircraft having an intake flow path (engine bay 6) that circulates air taken in from an intake duct (intake duct 7) toward an engine 5, and a heat exchanger 22 that is provided in a space formed between the intake flow path and the engine 5 and fixed to the inner wall side of the intake flow path with a gap between it and the engine 5.

[0026] With this configuration, the air taken in from the intake duct to be used for the engine 5 can also be used to cool the heat exchanger 22, eliminating the need to enlarge the opening of the intake port provided separately from the intake duct. This makes it possible to appropriately dissipate heat generated by the aircraft while suppressing a decline in the aircraft's flight performance.

[0027] As a second aspect, in the heat exhaust system 10, 30 according to the first aspect, the intake passage has a circular cross section, and the heat exchanger 22 is arranged in an arc shape along the inner wall of the intake passage.

[0028] According to this configuration, by providing the heat exchanger 22 along the inner wall of the intake passage, a suitable gap can be secured between the heat exchanger 22 and the engine 5, thereby reducing pressure loss.

[0029] As a third aspect, in the heat exhaust system 10, 30 according to the first or second aspect, the heat exchanger 22 is provided in multiple units, including a liquid-cooled heat exchanger through which a liquid phase refrigerant flows and an air-cooled heat exchanger through which a gas phase refrigerant flows, and when the liquid phase refrigerant is water, the liquid-cooled heat exchanger is positioned upstream of the intake flow path compared to the air-cooled heat exchanger.

[0030] According to this configuration, the air temperature is lower on the upstream side of the intake air flow path than on the downstream side, so the liquid-cooled heat exchanger can be cooled more effectively.

[0031] As a fourth aspect, the heat exhaust system 30 according to any one of the first to third aspects further includes a movable vane 32 that guides air toward the heat exchanger 22.

[0032] According to this configuration, by adjusting the flow rate of air supplied to the heat exchanger 22, it is possible to adjust the cooling by the heat exchanger 22 and also to reduce the pressure loss in the intake flow path. [Explanation of symbols]

[0033] 5 Engine 6. Engine Bay 7 Intake duct 8 Components 10. Heat dissipation system 21 Bleeding line 22 Heat exchanger 23 Air supply line 24 Cooling System 25 Bypass Line 26 Flow control valve 30 Heat Exhaust System 31 Branch channel 32 Movable vane

Claims

1. A heat exhaust system for exhausting heat generated by an aircraft, the aircraft has an intake flow path that distributes air taken in from an intake duct toward an engine, A heat exhaust system comprising a heat exchanger provided in a space formed between the intake passage and the engine, and fixed to an inner wall side of the intake passage with a gap provided between the intake passage and the engine.

2. The intake passage has a circular cross section, The heat exhaust system according to claim 1 , wherein the heat exchanger is provided in an arc shape along an inner wall of the intake air flow path.

3. The heat exchanger is provided in plurality, and includes a liquid-cooled heat exchanger through which a liquid-phase refrigerant flows and an air-cooled heat exchanger through which a gas-phase refrigerant flows, The heat exhaust system according to claim 1 , wherein the liquid-cooled heat exchanger is disposed upstream of the intake air flow path relative to the air-cooled heat exchanger when the liquid-phase refrigerant is water.

4. The heat rejection system of claim 1 , further comprising a movable vane that guides air toward the heat exchanger.

Images