Pre-cooling heat exchanger for aircraft and aircraft

Abstract

The present disclosure relates to the field of aircraft, and particularly provides a pre-cooling heat exchanger for aircraft and an aircraft. The pre-cooling heat exchanger comprises a shell and a heat exchanger core body obliquely arranged in the shell. The heat exchanger core body comprises at least three partition plates which are sequentially stacked and arranged at intervals. Among every three adjacent partition plates, two adjacent partition plates form an air flow channel, and the other two adjacent partition plates form a heat exchange working medium flow channel. The air flow channel is arranged along a first direction of the partition plate, and the heat exchange working medium flow channel is arranged along a second direction of the partition plate. The first direction and the second direction are perpendicular. The partition plate is a curved partition plate, so that the air flow channel is formed into a curved air flow channel. The inlet end of the curved air flow channel is inclined towards the direction of the air inlet of the shell, and the outlet end of the curved air flow channel is communicated with the air outlet of the shell. Therefore, the aerodynamic separation is inhibited to a certain extent, the uniformity of airflow distribution is improved, and the heat exchange efficiency is improved.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft technology, and in particular to a precooling heat exchanger for aircraft and an aircraft. Background Technology

[0002] The high speed of aircraft has extremely important military and civilian value, but the aerodynamic heating effect generated by aircraft during high-speed flight limits the flight limits of aircraft.

[0003] Turbine engines are a crucial component of aircraft, providing propulsion. To increase the flight speed of turbine engines, related technologies utilize pre-cooling heat exchangers to cool the ramjet intake air, lowering its temperature to partially offset the temperature rise caused by aerodynamic heating during high-speed flight. To reduce the frontal area occupied by the pre-cooling heat exchanger, the heat exchanger core is installed at an angle within the heat exchanger shell. However, this causes aerodynamic separation of the airflow at the inlet, resulting in uneven airflow distribution and consequently reduced heat exchange efficiency. Summary of the Invention

[0004] In order to solve the above-mentioned technical problems, or at least partially solve the above-mentioned technical problems, this disclosure provides a precooling heat exchanger for aircraft and an aircraft.

[0005] In a first aspect, this disclosure provides a precooling heat exchanger for an aircraft, including a housing and a heat exchanger core located within the housing;

[0006] The housing has an air inlet and an air outlet, which are disposed opposite to each other on both sides of the housing. The air outlet is used to communicate with the engine air inlet of the aircraft. The heat exchanger core is inclinedly disposed within the housing in the direction from the air inlet to the air outlet.

[0007] The heat exchanger core includes at least three partitions stacked sequentially and spaced apart. In every three adjacent partitions, an air flow channel is formed between two adjacent partitions, and a heat exchange working fluid flow channel is formed between the other two adjacent partitions. The air flow channel is arranged along a first direction of the partition, and the heat exchange working fluid flow channel is arranged along a second direction of the partition. The first direction and the second direction are perpendicular to each other.

[0008] The baffle is a curved baffle, so that the air flow channel is formed into a curved air flow channel, and the inlet end of the curved air flow channel is inclined towards the direction of the air inlet, and the outlet end of the curved air flow channel is connected to the air outlet.

[0009] Optionally, along the first direction, the partition includes at least two sequentially connected arc-shaped guide sections, and the bending directions of two adjacent arc-shaped guide sections are opposite.

[0010] Optionally, the joints of two adjacent arc-shaped guide sections are smoothly transitioned.

[0011] Optionally, the partition is a shape memory alloy partition.

[0012] Optionally, heat exchange fins are provided in the airflow channel.

[0013] Optionally, the heat exchange fins include multiple fin segments;

[0014] Along the second direction, a plurality of wing segments are arranged sequentially, and a gap for airflow is formed between two adjacent wing segments;

[0015] The area of ​​the airflow channel near the outlet of the heat exchange medium flow channel is a first region, and the area of ​​the airflow channel near the inlet of the heat exchange medium flow channel is a second region. Both the first region and the second region are provided with a plurality of fin segments. The spacing between two adjacent fin segments in the first region is smaller than the spacing between two adjacent fin segments in the second region.

[0016] Optionally, the heat exchange fins include multiple fin segments; along the second direction, the multiple fin segments are spaced apart and arranged in parallel, and a gap for airflow is formed between two adjacent fin segments;

[0017] Alternatively, the heat exchange fins may include multiple fin segments arranged sequentially along the second direction, with one end of two adjacent fin segments close to and connected to each other, and the other ends of two adjacent fin segments far apart from each other, so that the heat exchange fins form corrugated fins or serrated fins.

[0018] Optionally, the flow channel region between the air inlet and the upstream side of the heat exchanger core forms a region with a sudden area expansion;

[0019] A cross-sectional reduction member is provided within the area of ​​the sudden expansion, and the cross-sectional reduction member is connected to the shell.

[0020] Optionally, the cross-section reduction member is an arc-shaped plate extending along the airflow direction and disposed on the upstream side of the heat exchanger core.

[0021] In a second aspect, this disclosure provides an aircraft, including an engine and a precooling heat exchanger for an aircraft as described above;

[0022] The precooling heat exchanger for the aircraft is located on the intake side of the engine.

[0023] The precooling heat exchanger and aircraft disclosed herein reduce the frontal area of ​​the heat exchanger core by tilting it within the casing, thereby reducing pressure drag and improving heat exchange efficiency. Furthermore, the heat exchanger core is configured with at least three sequentially stacked and spaced baffles. In each set of three adjacent baffles, an airflow channel is formed between two adjacent baffles, and a heat exchange medium flow channel is formed between the other two adjacent baffles. The airflow channel and the heat exchange medium flow channel are perpendicular. This perpendicular arrangement of the two heat exchange channels improves heat exchange efficiency. Simultaneously, by configuring the baffles as curved baffles, the airflow channel is formed as a curved airflow channel, with the inlet end of the curved airflow channel tilted towards the air inlet. This effectively guides the air entering from the air inlet, smoothly directing the air into the curved airflow channel, thereby suppressing aerodynamic separation at the inlet to a certain extent, improving the uniformity of airflow distribution, and further enhancing heat exchange efficiency.

[0024] Moreover, since the airflow channel is a curved airflow channel, the heat exchange contact area between the air and the baffle is increased without changing the outer contour volume of the heat exchanger core, thereby further improving the heat exchange efficiency.

[0025] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0026] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0027] Figure 1 This is a schematic diagram of the structure of the heat exchanger core of an aircraft precooling heat exchanger according to an embodiment of this disclosure;

[0028] Figure 2 This is a side view of the heat exchanger core of an aircraft precooling heat exchanger according to an embodiment of the present disclosure. Figure 1 ;

[0029] Figure 3 This is a side view of the heat exchanger core of an aircraft precooling heat exchanger according to an embodiment of the present disclosure. Figure 2 ;

[0030] Figure 4This is a partial structural schematic diagram of an aircraft precooling heat exchanger and engine according to an embodiment of the present disclosure;

[0031] Figure 5 This is a schematic diagram of the airflow direction in a precooling heat exchanger for aircraft according to an embodiment of this disclosure.

[0032] Among them, 1. Shell; 11. Air inlet; 12. Air outlet; 2. Heat exchanger core; 20. End plate; 21. Baffle; 211. Arc-shaped guide section; 22. Air flow channel; 221. Inlet end; 23. Heat exchange working fluid flow channel; 24. Heat exchange fins; 241. Fin segment; 3. Area expansion region; 4. Cross-section reduction component; 5. Engine. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this disclosure more apparent, exemplary embodiments according to this disclosure will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments of this disclosure. It should be understood that this disclosure is not limited to the exemplary embodiments described herein.

[0034] It should be understood that the steps described in the method embodiments of this disclosure may be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of this disclosure is not limited in this respect.

[0035] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". Definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc., used in this disclosure are only used to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0036] It should be noted that the terms "a" and "a plurality of" used in this disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0037] Aircraft precooling heat exchangers, specifically located on the intake side of the aircraft engine, are used to cool the intake air, reducing the temperature of the inlet airflow to the turbine engine and enabling the turbine to fly at higher speeds. Related technologies aim to reduce the frontal area of ​​the precooling heat exchanger by installing the heat exchanger core at an angle within the heat exchanger shell to decrease pressure drag. However, this can cause airflow separation at the heat exchanger inlet, resulting in uneven airflow distribution, which in turn affects heat exchange efficiency and may even lead to engine overheating and failure.

[0038] Based on this, the present disclosure provides a precooling heat exchanger for aircraft and an aircraft. The precooling heat exchanger is configured with at least three stacked baffles, so that the three adjacent baffles form mutually perpendicular air flow channels and heat exchange working fluid flow channels. The baffles are configured as curved baffles, so that the air flow channel between two adjacent baffles forms a curved flow channel, and the inlet end of the curved flow channel faces the air inlet of the heat exchanger shell, thereby achieving better guidance of the air entering from the air inlet of the shell, so as to suppress airflow separation, improve the uniformity of airflow distribution, and thus improve heat exchange efficiency.

[0039] The precooling heat exchanger for aircraft and the aircraft provided in the embodiments of this disclosure will be described in detail below with reference to the accompanying drawings:

[0040] Reference Figures 1 to 5 As shown, this disclosure provides a precooling heat exchanger for aircraft, including: a housing 1 and a heat exchanger core 2 located within the housing 1.

[0041] The housing 1 has an air inlet 11 and an air outlet 12, which are disposed opposite to each other on both sides of the housing 1. The air outlet 12 is used to communicate with the air intake of the aircraft's engine 5.

[0042] The heat exchanger core 2 is inclined within the shell 1 along the direction from air inlet 11 to air outlet 12. The inclination angle of the heat exchanger core 2 is α, that is, the angle between the heat exchanger core 2 and the horizontal plane is α. Figure 4 and Figure 5 As shown, this can be understood as the state when the heat exchanger core is placed normally, that is, without tilting. Figure 4 and Figure 5 The upper surface of the heat exchanger core (i.e. the side where the air inlet is located) is in a vertical position, and the inlet end of the air inlet is directly opposite the air inlet.

[0043] Compared to placing the heat exchanger core normally (i.e., the inlet end of the airflow channel is directly opposite the air inlet), such as Figure 4 and Figure 5 By tilting the heat exchanger core 2, the frontal area is reduced, thereby reducing the pressure resistance and improving the heat exchange efficiency.

[0044] The heat exchanger core 2 includes at least three sequentially stacked and spaced-apart partitions 21. In every three adjacent partitions 21, an airflow channel 22 is formed between two adjacent partitions 21, and a heat exchange medium flow channel 23 is formed between the other two adjacent partitions 21. Specifically, end plates 20 can be connected between the two ends of the other two adjacent partitions 21 to form a sealed heat exchange medium flow channel 23. Alternatively, the ends of the partitions 21 can be connected to the shell 1 to form a sealed flow channel.

[0045] Specifically, the air flow channel 22 is arranged along the first direction of the partition 21, and the heat exchange medium flow channel 23 is arranged along the second direction of the partition 21; the first direction and the second direction are perpendicular to each other.

[0046] For example, refer to Figure 1 As shown, the first direction is specifically... Figure 1 In the context of XX direction, for example, the first direction is the length direction of partition 21; the second direction is specifically... Figure 1 The YY direction in the diagram, for example, the second direction is the width direction of the partition 21.

[0047] The baffle 21 is a curved baffle, which makes the air flow channel 22 a curved air flow channel, and the inlet end 221 of the curved air flow channel is inclined towards the air inlet 11. The outlet end of the curved air flow channel is connected to the air outlet 12.

[0048] In a specific implementation, the heat exchange medium flow channel 23 has an inlet and an outlet. For example, the inlet of the heat exchange medium flow channel 23 can be connected to the heat exchange medium storage container, and the heat exchange medium is supplied to the heat exchange medium flow channel 23 through the heat exchange medium storage container, so as to realize the circulation of the heat exchange medium in the heat exchange medium flow channel 23.

[0049] For example, the heat exchange medium can be a liquid-cooled metal medium, specifically a gallium-based alloy. The heat exchange medium can also be a gaseous medium.

[0050] It is understandable that the partition 21 is made of materials that meet the requirements of high temperature resistance, corrosion resistance and good thermal conductivity in aviation, such as high temperature alloys, high temperature stainless steel or titanium alloys.

[0051] Combination Figure 1 and Figure 5 As shown, Figure 5The arrows in the diagram indicate the direction of the airflow. Specifically, the air entering through the air inlet 11 of the housing 1 enters the airflow channel 22 through the inlet end 221 of the curved airflow channel 22. By setting the baffle 21 as a curved baffle, the airflow channel 22 is formed into a curved airflow channel, and the inlet end 221 of the curved airflow channel is inclined toward the air inlet 11, thereby achieving better guidance of the air entering from the air inlet 11, so that the air enters the curved airflow channel 22 tangentially, which to a certain extent suppresses aerodynamic separation and improves the uniformity of airflow distribution. The heat of the air entering the curved airflow channel 22 is transferred to the baffle 21, and then from the baffle 21 to the heat exchange medium in the adjacent heat exchange medium flow channel 23. After absorbing the heat of the air, the heat exchange medium flows out from the outlet of the heat exchange medium flow channel 23, thereby cooling the air. The cooled air in the airflow channel 22 finally flows from the outlet end of the airflow channel 22 to the engine 5, and enters the engine 5 from the air intake, thereby cooling the intake air temperature of the engine 5, ensuring the performance of the engine 5, and thus ensuring that it can fly at higher speeds.

[0052] The precooling heat exchanger for aircraft disclosed herein reduces the frontal area of ​​the heat exchanger core 2 by tilting it within the shell 1, thereby reducing pressure drag and improving heat exchange efficiency. Furthermore, the heat exchanger core 2 is configured to include at least three sequentially stacked and spaced baffles 21, such that in every three adjacent baffles 21, an airflow channel 22 is formed between two adjacent baffles 21, and a heat exchange medium flow channel 23 is formed between the other two adjacent baffles 21. The airflow channel 22 and the heat exchange medium flow channel... 23. By setting the two heat exchange channels vertically, the heat exchange efficiency is improved. At the same time, by setting the baffle 21 as a curved baffle, the air flow channel 22 is formed into a curved air flow channel, and the inlet end 221 of the curved air flow channel is inclined towards the air inlet 11. This achieves good guidance of the air entering from the air inlet 11, and guides the air smoothly into the curved air flow channel 22. This, to a certain extent, suppresses the phenomenon of aerodynamic separation at the inlet, improves the uniformity of airflow distribution, and thus improves the heat exchange efficiency.

[0053] Moreover, since the air flow channel 22 is a curved air flow channel, the heat exchange contact area between the air and the baffle 21 is increased while the outer contour volume of the heat exchanger core 2 remains unchanged, thereby further improving the heat exchange efficiency.

[0054] By directly modifying the baffle 21, there is no need to add an additional flow guiding device outside the heat exchanger core 2, thereby achieving airflow guidance within the same volume, improving the uniformity of airflow distribution and heat exchange efficiency, and better adapting to the constraints of aerospace space.

[0055] Continue to refer to Figures 1 to 3 As shown, in some embodiments, along the first direction, the partition 21 includes at least two sequentially connected arc-shaped guide sections 211, and the bending directions of the two adjacent arc-shaped guide sections 211 are opposite.

[0056] This design achieves a curved airflow channel while avoiding dead zones, further improving the smoothness and uniformity of airflow in the airflow channel 22, and thus further improving heat exchange efficiency.

[0057] The radius of curvature of the arc-shaped guide section 211 can be adapted to the inclined installation angle, so that the airflow can be smoothly redirected.

[0058] Furthermore, the joint between two adjacent arc-shaped guide sections 211 can be smoothly transitioned, which further avoids the occurrence of flow dead zones, reduces the stress at the joint, improves the connection strength between the two arc-shaped guide sections 211, and thus ensures the structural strength of the baffle 21 and extends the service life of the heat exchanger.

[0059] For example, refer to Figures 1 to 3 As shown, the baffle 21 includes, for example, two arc-shaped guide sections 211, so that the baffle 21 is an S-shaped baffle.

[0060] For example, the wavelength to amplitude ratio of the S-shaped septum 21 can be 2:1 to 5:1 to match the Reynolds number range (Re = 500 to 5000) under aviation conditions.

[0061] Of course, in other embodiments, the baffle 21 may also include three or more flow guide sections, such as being formed as a corrugated baffle.

[0062] In some embodiments, the partition 21 may specifically be a shape memory alloy partition.

[0063] This configuration allows the baffle 21 to automatically adjust its curvature based on temperature or airflow pressure during different flight phases (takeoff and cruise), achieving dynamic optimization of the airflow channel 22 and further improving airflow uniformity and heat exchange efficiency. Through adaptive structural design, it meets the pre-cooling requirements under complex flight conditions.

[0064] For example, refer to Figure 2 As shown, when the flight speed is high (Ma≥3), a larger curvature is used to make the entire airflow channel 22 a curved surface with a larger curvature, resulting in higher heat transfer performance; for example, referring to... Figure 3 As shown, when the flight speed is low (Ma < 3), a smaller curvature is used, such as the middle part of the partition 21 being relatively straight, at which time the flow loss in the flow channel is small.

[0065] In practice, the shape memory alloy separator can be heat-treated to ensure its shape memory performance.

[0066] For example, the partition 21 can be a nickel-titanium alloy partition, which has excellent high temperature resistance, corrosion resistance, thermal conductivity and deformation memory properties.

[0067] In addition, in other embodiments, the partition 21 may also be made of other materials such as cobalt-based alloys or copper-nickel alloys.

[0068] Continue to refer to Figure 1 As shown, in some embodiments, heat exchange fins 24 are provided in the airflow channel 22.

[0069] By incorporating heat exchange fins 24 in the airflow channel 22, the heat exchange area between the air and the airflow channel 22 is increased, while dead zones in the flow can be avoided to some extent, thereby further improving heat exchange efficiency. Furthermore, the heat exchange fins 24 also enhance the structural strength of the heat exchanger core 2.

[0070] Furthermore, the heat exchange fins 24 include a plurality of fin segments 241; along the second direction, the plurality of fin segments 241 are arranged sequentially, and a gap for airflow is formed between two adjacent fin segments 241.

[0071] By setting multiple fin segments 241, the heat exchange area is further increased, the flow dead zone is reduced, and the heat exchange efficiency is improved.

[0072] The region of the airflow channel 22 near the outlet of the heat exchange medium flow channel 23 is defined as the first region, and the region of the airflow channel 22 near the inlet of the heat exchange medium flow channel 23 is defined as the second region. (Refer to...) Figure 1 For example, the heat exchange medium inlet is located at the top of the heat exchange medium flow channel 23, and the heat exchange medium outlet is located at the bottom of the heat exchange medium flow channel 23. The first region can be regarded as the bottom region of the air flow channel 22, and the second region can be regarded as the top region of the air flow channel 22.

[0073] In some embodiments, both the first region and the second region are provided with a plurality of wing segments 241, and the spacing between two adjacent wing segments 241 in the first region is smaller than the spacing between two adjacent wing segments 241 in the second region.

[0074] In other words, near the cold source inlet, the heat exchange difference is large, and low-density fins are used in the air flow channel 22; near the cold source outlet, the heat exchange difference is small, and high-density fins are used in the air flow channel 22 to enhance heat exchange, thereby improving the overall heat exchange effect and heat exchange efficiency.

[0075] Reference Figure 1As shown, in some embodiments, a plurality of wing segments 241 are spaced apart and arranged in parallel along the second direction, and a gap for airflow is formed between two adjacent wing segments 241.

[0076] In other embodiments, multiple fin segments 241 are arranged sequentially along the second direction, with one end of two adjacent fin segments 241 close to each other and connected, and the other ends of two adjacent fin segments 241 far from each other, so that the heat exchange fins 24 form corrugated fins or serrated fins.

[0077] By setting the fins to multiple parallel fins, or to corrugated or serrated fins, the heat exchange efficiency can be further improved, and the structural strength of the heat exchanger can be strengthened to a certain extent.

[0078] In practice, the heat exchange fins 24 can be connected to the partition plate 21 by means of brazing or other methods.

[0079] Reference Figure 4 and Figure 5 As shown, a sudden expansion region 3 is formed in the flow channel region between the air inlet 11 of the shell 1 and the upstream side of the heat exchanger core 2. That is, the cross-sectional area of ​​the air flow suddenly expands, which causes gas backflow and pressure loss. Based on this, in some embodiments, a cross-sectional reduction member 4 is provided in the sudden expansion region 3, and the cross-sectional reduction member 4 is connected to the shell 1.

[0080] By setting a cross-sectional reduction element 4 in the area expansion region 3, the expansion ratio of the cross-sectional area of ​​the air flow space can be reduced to a certain extent, thereby reducing airflow loss and pressure loss, reducing the risk of inlet separation, and thus improving heat exchange efficiency.

[0081] In practice, the cross-section reduction component 4 can be connected to the inner wall of the housing 1 by means of welding or screws.

[0082] In some embodiments, the cross-section reduction member 4 is specifically an arc-shaped plate extending along the airflow direction and disposed on the upstream side of the heat exchanger core 2.

[0083] This simple structure not only reduces the expansion ratio of the cross-sectional area of ​​the flow space, but also guides the airflow, directing it into the airflow channel 22 of the heat exchanger core 2. This further reduces airflow loss and aerodynamic separation, thereby improving heat exchange efficiency.

[0084] The cross-section reduction element 4 can be located in the middle of the area expansion region 3 to improve the uniformity of airflow distribution.

[0085] Of course, in other implementations, the cross-section reduction component 4 can also be a structure such as a partition block, which is located in the middle of the area expansion region 3.

[0086] Verification has shown that the precooling heat exchanger for aircraft provided in this embodiment guides the airflow through its curved airflow channel 22, effectively suppressing flow separation caused by the tilted installation of the heat exchanger core 2. This improves the uniformity of velocity distribution within the heat exchanger core 2 by 30% to 50%. Simultaneously, the enhanced turbulence and improved flow uniformity work synergistically, resulting in an overall heat exchange efficiency increase of at least 15% to 25%. Furthermore, the precooling heat exchanger provided in this embodiment reduces pressure drop by 10% to 18%.

[0087] In practice, the curvature radius of the baffle 21 can be optimized based on the tilt angle of the heat exchanger core 2 to ensure that the airflow direction is coordinated with the flow channel setting of the engine 5. For example, the angle at the inlet of the heat exchanger core 2 = the expected airflow deflection angle - the deflection angle of the area expansion region 3. For example, if the tilt angle a of the heat exchanger is 10°, then the expected airflow deflection angle is 80°, and the deflection angle of the area expansion region 3 is generally around 10° to 30°.

[0088] The precooling heat exchanger provided in this disclosure can be specifically applied to aero engines, variable cycle engines, hypersonic turbine-based combined cycle engines, etc.

[0089] This disclosure also provides an aircraft, including an engine 5 and an aircraft precooling heat exchanger, wherein the aircraft precooling heat exchanger is located on the intake side of the engine 5 and is used to cool the intake air, thereby reducing the temperature of the airflow at the engine 5 intake and offsetting the increase in intake air temperature caused by aerodynamic heating effect during high-speed flight, so that the turbine can fly at higher speeds.

[0090] The specific structure and implementation principle of the precooling heat exchanger for aircraft in this embodiment are the same as those of the precooling heat exchanger for aircraft provided in the above embodiments, and can bring the same or similar technical effects. They will not be described in detail here, but can be referred to the description of the above embodiments.

[0091] The above description is merely an embodiment of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0092] While specific embodiments of this disclosure have been described in detail by way of example, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of this disclosure. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of this disclosure. The scope of this disclosure is defined by the appended claims.

Claims

1. A precooling heat exchanger for aircraft, characterized in that, Includes a housing and a heat exchanger core located within the housing; The housing has an air inlet and an air outlet, which are disposed opposite to each other on both sides of the housing. The air outlet is used to communicate with the engine air inlet of the aircraft. The heat exchanger core is inclinedly disposed within the housing in the direction from the air inlet to the air outlet. The heat exchanger core includes at least three partitions stacked sequentially and spaced apart. In every three adjacent partitions, an air flow channel is formed between two adjacent partitions, and a heat exchange working fluid flow channel is formed between the other two adjacent partitions. The air flow channel is arranged along a first direction of the partition, and the heat exchange working fluid flow channel is arranged along a second direction of the partition. The first direction and the second direction are perpendicular to each other. The baffle is a curved baffle, so that the air flow channel is formed into a curved air flow channel, and the inlet end of the curved air flow channel is inclined towards the direction of the air inlet, and the outlet end of the curved air flow channel is connected to the air outlet; The airflow channel is equipped with heat exchange fins; The heat exchange fins include multiple fin segments; Along the second direction, a plurality of wing segments are arranged sequentially, and a gap for airflow is formed between two adjacent wing segments; The area of ​​the air flow channel near the outlet of the heat exchange medium flow channel is a first region, and the area of ​​the air flow channel near the inlet of the heat exchange medium flow channel is a second region. Both the first region and the second region are provided with a plurality of fin segments. The spacing between two adjacent fin segments in the first region is smaller than the spacing between two adjacent fin segments in the second region. The heat exchange fins include multiple fin segments; along the second direction, the multiple fin segments are spaced apart and arranged in parallel, and a gap for airflow is formed between two adjacent fin segments; Alternatively, the heat exchange fins include multiple fin segments arranged sequentially along the second direction, with one end of two adjacent fin segments close to and connected to each other, and the other ends of two adjacent fin segments far from each other, so that the heat exchange fins form corrugated fins or serrated fins. The flow channel region between the air inlet and the upstream side of the heat exchanger core forms a region with a sudden expansion in area. A cross-sectional reduction member is provided within the area of ​​the sudden expansion, and the cross-sectional reduction member is connected to the shell.

2. The precooling heat exchanger for aircraft according to claim 1, characterized in that, Along the first direction, the partition includes at least two sequentially connected arc-shaped guide sections, and the bending directions of two adjacent arc-shaped guide sections are opposite.

3. The precooling heat exchanger for aircraft according to claim 2, characterized in that, The junction of two adjacent arc-shaped guide sections is smoothly transitioned.

4. The precooling heat exchanger for aircraft according to any one of claims 1 to 3, characterized in that, The partition is a shape memory alloy partition.

5. The precooling heat exchanger for aircraft according to claim 1, characterized in that, The cross-section reduction member is an arc-shaped plate extending along the airflow direction and disposed on the upstream side of the heat exchanger core.

6. An aircraft, characterized in that, Includes an engine and an aircraft precooling heat exchanger as described in any one of claims 1 to 5; The precooling heat exchanger for the aircraft is located on the intake side of the engine.

Images