Pre-cooling heat exchanger for aircraft and aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to a pre-cooling heat exchanger for an aircraft and the aircraft. The pre-cooling heat exchanger comprises a shell and a heat exchanger core obliquely arranged in the shell; the heat exchanger core comprises at least three partition plates which are sequentially stacked and arranged at intervals, in every three adjacent partition plates, an air flow channel is formed between two adjacent partition plates, a heat exchange working medium flow channel is formed between the other two adjacent partition plates, and the air flow channels are arranged in the first direction of the partition plates. The heat exchange working medium runner is arranged in the second direction of the partition plate. The first direction is perpendicular to the second direction; the partition plate is a bent partition plate so that the air flow channel can form a curve type air flow channel, the inlet end of the curve type flow channel inclines towards the air inlet of the shell, and the outlet end of the curve type flow channel is communicated with the air outlet of the shell, so that pneumatic separation is restrained to a certain degree, and the uniformity of airflow distribution is improved; and the heat exchange efficiency is further improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular, to a pre-cooling heat exchanger for an aircraft and an aircraft. Background Art

[0002] The high-speedization of aircraft has extremely important military and civilian values. However, the aerodynamic heating effect generated during the high-speed flight of an aircraft restricts the flight limit of the aircraft.

[0003] A turbine engine is an important part of an aircraft and is used to provide flight power for the aircraft. In order to increase the flight speed of the turbine engine, related technologies cool the ram air intake through a pre-cooling heat exchanger to reduce the temperature of the inlet air flow, in order to offset to a certain extent the temperature increase caused by the aerodynamic heating effect during high-speed flight. Among them, in order to reduce the frontal area occupied by the pre-cooling heat exchanger, related technologies tilt the heat exchanger core in the heat exchanger housing. However, this will cause aerodynamic separation of the air flow at the inlet, resulting in uneven air flow distribution and thus reducing the heat exchange efficiency. Summary of the Invention

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

[0005] In a first aspect, the present disclosure provides a pre-cooling 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, the air inlet and the air outlet are oppositely arranged on both sides of the housing, and the air outlet is used to communicate with the engine air inlet of the aircraft; in the direction from the air inlet to the air outlet, the heat exchanger core is inclined in the housing;

[0007] The heat exchanger core includes at least three partition plates that are sequentially stacked and spaced apart. Among every three adjacent partition plates, an air flow channel is formed between two adjacent partition plates, and a heat exchange working medium flow channel is formed between another two adjacent partition plates. 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 to each other;

[0008] The partition plate is a curved partition plate, 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 communicates with the air outlet.

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

[0010] Optionally, the joint of two adjacent arc-shaped diversion sections has a smooth transition.

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

[0012] Optionally, heat exchange fins are arranged in the air flow channel.

[0013] Optionally, the heat exchange fins include a plurality of fin segments;

[0014] Along the second direction, the plurality of fin segments are arranged in sequence, and a gap for air flow is formed between two adjacent fin segments;

[0015] The area close to the outlet of the heat exchange working medium flow channel in the air flow channel is the first area, the area close to the inlet of the heat exchange working medium flow channel in the air flow channel is the second area, and a plurality of fin segments are arranged in both the first area and the second area. The distance between two adjacent fin segments in the first area is smaller than the distance between two adjacent fin segments in the second area.

[0016] Optionally, the heat exchange fins include a plurality of fin segments; along the second direction, the plurality of fin segments are arranged at intervals and in parallel, and a gap for air flow is formed between two adjacent fin segments;

[0017] Alternatively, the heat exchange fins include a plurality of fin segments. Along the second direction, the plurality of fin segments are arranged in sequence, and one end of two adjacent fin segments is close to and connected to each other, and the other end of two adjacent fin segments is far from each other, so that the heat exchange fins form corrugated fins or serrated fins.

[0018] Optionally, an area of sudden expansion is formed in the flow channel area between the air inlet and the upstream side of the heat exchanger core;

[0019] A cross-section reduction member is arranged in the area of sudden expansion, and the cross-section reduction member is connected to the housing.

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

[0021] In a second aspect, the present disclosure provides an aircraft, including an engine and the pre-cooling heat exchanger for aircraft as described above;

[0022] The pre-cooling heat exchanger for aircraft is located on the air intake side of the engine.

[0023] The pre-cooling heat exchanger for an aircraft and the aircraft provided by the present disclosure tilt the heat exchanger core in the housing to reduce the windward area of the heat exchanger core, thereby reducing the pressure difference resistance and improving the heat exchange efficiency. On this basis, by setting the heat exchanger core to include at least three partition plates that are sequentially stacked and spaced apart, an air flow channel is formed between two adjacent partition plates among every three adjacent partition plates, and a heat exchange working medium flow channel is formed between the other two adjacent partition plates, and the air flow channel and the heat exchange working medium flow channel are perpendicular. By setting the two heat exchange flow channels perpendicular to each other, the heat exchange efficiency is improved. At the same time, by setting the partition plates as curved partition plates, 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. In this way, good diversion of the air entering from the air inlet is achieved, and the air is smoothly diverted into the curved air flow channel, thereby suppressing the occurrence of aerodynamic separation at the inlet to a certain extent, improving the uniformity of the air flow distribution, and further improving the heat exchange efficiency.

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

[0025] It is to be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the claimed technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] By describing the embodiments of the present disclosure in more detail in conjunction with the drawings, the above and other objects, features, and advantages of the present disclosure will become more apparent. The drawings are used to provide a further understanding of the embodiments of the present disclosure, and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0027] Figure 1 FIG. is a schematic structural diagram of a heat exchanger core of a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure;

[0028] Figure 2 FIG. is a schematic side view structure of a heat exchanger core of a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure Figure 1 ;

[0029] Figure 3 FIG. is a schematic side view structure of a heat exchanger core of a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure Figure 2 ;

[0030] Figure 4Schematic diagram of the local structure of a pre-cooling heat exchanger for an aircraft and an engine according to an embodiment of the present disclosure;

[0031] Figure 5 Schematic diagram of the flow direction of the air flow in the pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure.

[0032] Wherein, 1. housing; 11. air inlet; 12. air outlet; 2. heat exchanger core; 20. end plate; 21. partition; 211. arc-shaped diversion section; 22. air flow channel; 221. inlet end; 23. heat transfer working medium flow channel; 24. heat transfer fins; 241. fin segments; 3. area sudden expansion region; 4. cross-section reduction member; 5. engine. Detailed implementation manners

[0033] In order to make the objectives, technical solutions and advantages of the present disclosure more apparent, exemplary embodiments according to the present disclosure will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all of the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0034] It should be understood that the various steps recited in the method embodiments of the present disclosure may be executed in a different order and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this regard.

[0035] The term "including" and its variants used herein are open-ended, that is, "including but not limited to". The term "based on" is "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". The relevant definitions of other terms will be given in the following description. It should be noted that the concepts such as "first" and "second" mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order of the functions executed by these devices, modules or units or the interdependent relationship.

[0036] It should be noted that the modifications of "one" and "multiple" mentioned in the present disclosure are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise clearly specified in the context, it should be understood as "one or more".

[0037] Aircraft precooling heat exchangers, specifically located on the intake side of an aircraft engine, cool the incoming air, reducing the temperature of the turbine engine's inlet airflow and enabling the turbine to operate at higher speeds. To reduce the precooling heat exchanger's frontal area, the heat exchanger core is installed at an angle within the heat exchanger housing to minimize pressure differential resistance. However, this can easily cause flow separation at the heat exchanger inlet, leading to uneven airflow distribution, which in turn affects heat exchange efficiency and can even cause engine overheating and failure.

[0038] Based on this, the embodiments of the present disclosure provide a pre-cooling heat exchanger for an aircraft and an aircraft, wherein the pre-cooling heat exchanger is provided with at least three stacked partitions so that mutually perpendicular air flow channels and heat exchange medium flow channels are formed between the three adjacent partitions respectively, and the partitions are provided as curved partitions so that the air flow channel between two adjacent partitions is formed into a curved flow channel, and the inlet end of the curved flow channel is directed toward 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 following describes in detail the aircraft pre-cooling heat exchanger and the aircraft provided by the embodiments of the present disclosure with reference to the accompanying drawings:

[0040] Reference Figures 1 to 5 As shown, an embodiment of the present disclosure provides a pre-cooling heat exchanger for an aircraft, comprising: a shell 1 and a heat exchanger core 2 located in the shell 1 .

[0041] The housing 1 has an air inlet 11 and an air outlet 12 , which are arranged on two sides of the housing 1 . The air outlet 12 is used to communicate with an air inlet of an engine 5 of the aircraft.

[0042] The heat exchanger core 2 is tilted in the housing 1 along the direction from the air inlet 11 to the air outlet 12. The tilt angle of the heat exchanger core 2 is a, that is, the angle between the heat exchanger core 2 and the horizontal plane is a. Figure 4 and Figure 5 As shown, it can be understood that when the heat exchanger core is placed normally, that is, not tilted, Figure 4 and Figure 5 The upper surface of the middle heat exchanger core (ie the side where the inlet of the air flow channel is located) is in a vertical state. At this time, the inlet end of the air flow channel is facing the air inlet.

[0043] Compared with placing the heat exchanger core normally (i.e. the inlet end of the air channel faces the air inlet), Figure 4 and Figure 5 By tilting the heat exchanger core 2, the windward area is reduced, thereby reducing the pressure difference resistance and improving the heat exchange efficiency.

[0044] Among them, the heat exchanger core 2 includes at least three partitions 21 that are stacked in sequence and spaced apart. Among every three adjacent partitions 21, an air flow channel 22 is formed between two adjacent partitions 21, and a heat exchange working medium flow channel 23 is formed between the other two adjacent partitions 21. When specifically implemented, end plates 20 can be connected between the two ends of the other two adjacent partitions 21 to form a sealed heat exchange working medium flow channel 23. The end of the partition 21 can also be connected to the housing 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 working 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] Exemplarily, referring to Figure 1 as shown, the first direction is specifically the Figure 1 X-X direction in Figure 1 for example, the first direction is the length direction of the partition 21; the second direction is specifically the

[0047] Y-Y direction in

[0048] for example, the second direction is the width direction of the partition 21. Among them, the partition 21 is a curved partition, so that 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 direction of the air inlet 11. Among them, the outlet end of the curved air flow channel is communicated with the air outlet 12.

[0049] When specifically implemented, the heat exchange working medium flow channel 23 has an inlet and an outlet. Exemplarily, the inlet of the heat exchange working medium flow channel 23 can be communicated with a heat exchange working medium storage container, and the heat exchange working medium is provided to the heat exchange working medium flow channel 23 through the heat exchange working medium storage container to realize the cyclic flow of the heat exchange working medium in the heat exchange working medium flow channel 23.

[0050] Exemplarily, the heat exchange working medium can be, for example, a liquid-cooled metal working medium, specifically, a gallium-based alloy, etc. The heat exchange working medium can also be a gaseous heat exchange working medium, etc.

[0051] Combined with Figure 1 and Figure 5 as shown, Figure 5The arrow in [description] indicates the direction of the air flow. Specifically, the air entering from the air inlet 11 of the housing 1 enters the air flow channel 22 from the inlet end 221 of the curved air flow channel 22. By setting the partition plate 21 as a curved partition plate, 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, so as to achieve better guiding of the air entering from the air inlet 11, making the air tangentially enter the curved air flow channel 22, suppressing pneumatic separation to a certain extent, and improving the uniformity of the air flow distribution. The heat of the air entering the curved air flow channel 22 is transferred to the partition plate 21, and then transferred by the partition plate 21 to the heat exchange working medium in the adjacent heat exchange working medium flow channel 23. After absorbing the heat of the air, the heat exchange working medium flows out from the outlet of the heat exchange working medium flow channel 23, thus realizing the cooling of the air. The cooled air in the air flow channel 22 finally flows towards the engine 5 from the outlet end of the air flow channel 22 and enters the engine 5 from the air inlet of the engine 5, thus realizing the cooling of the intake air temperature of the engine 5, ensuring the performance of the engine 5, and further ensuring that it can fly at a higher speed.

[0052] The pre-cooling heat exchanger for an aircraft provided by the present disclosure reduces the windward area of the heat exchanger core 2 by inclinedly arranging the heat exchanger core 2 in the housing 1, thereby reducing the pressure difference resistance and improving the heat exchange efficiency. On this basis, by setting the heat exchanger core 2 to include at least three partition plates 21 that are sequentially stacked and spaced apart, an air flow channel 22 is formed between two adjacent partition plates 21 among every three adjacent partition plates 21, and a heat exchange working medium flow channel 23 is formed between the other two adjacent partition plates 21, and the air flow channel 22 and the heat exchange working medium flow channel 23 are perpendicular. By setting the two heat exchange channels perpendicular to each other, the heat exchange efficiency is improved. At the same time, by setting the partition plate 21 as a curved partition plate, 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 direction of the air inlet 11. In this way, good guiding of the air entering from the air inlet 11 is achieved, and the air is smoothly guided into the curved air flow channel 22, thereby suppressing the occurrence of pneumatic separation at the inlet to a certain extent, improving the uniformity of the air flow distribution, and further improving the heat exchange efficiency.

[0053] Moreover, since the air flow channel 22 is a curved air flow channel, without changing the outer contour volume of the heat exchanger core 2, the heat exchange contact area between the air and the partition plate 21 is increased, thereby further improving the heat exchange efficiency.

[0054] By directly improving the partition plate 21, there is no need to additionally add a flow guiding device outside the heat exchanger core 2, so as to realize the guiding of the air flow under the same volume, improve the air flow distribution uniformity and the heat exchange efficiency, and better adapt to the aviation space constraints.

[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 flow guiding sections 211, and the bending directions of two adjacent arc-shaped flow guiding sections 211 are opposite.

[0056] This setting can avoid flow dead zones while implementing a curved air flow channel, further improving the smoothness of air flow in the air flow channel 22 and the air flow uniformity, and thus further improving the heat exchange efficiency.

[0057] The radius of curvature of the arc-shaped flow guiding section 211 can be specifically adapted to the inclined installation angle to enable smooth turning of the air flow.

[0058] Furthermore, the joints between two adjacent arc-shaped flow guiding sections 211 can be made to have a smooth transition, which further avoids the occurrence of flow dead zones, reduces the stress at the joints, improves the connection strength between the two arc-shaped flow guiding sections 211, and thus ensures the structural strength of the partition 21 and extends the service life of the heat exchanger.

[0059] Exemplarily, referring to Figures 1 to 3 As shown, the partition 21 includes, for example, two arc-shaped flow guiding sections 211, so that the partition 21 is an S-shaped partition.

[0060] Exemplarily, for example, the ratio of the wavelength to the wave amplitude of the S-shaped partition 21 can be 2:1 to 5:1, which matches the Reynolds number range (Re = 500 - 5000) under aviation conditions.

[0061] Of course, in other embodiments, the partition 21 can also include three or more flow guiding sections, such as being formed into a wavy partition, etc.

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

[0063] This setting enables the partition 21 to automatically adjust the curvature according to temperature or air flow pressure at different flight stages (takeoff, cruise) of the aircraft, realizing dynamic optimization of the air flow channel 22, thereby further improving the air flow distribution uniformity and heat exchange efficiency. Through adaptive structure design, the pre-cooling requirements under complex flight condition changes are met.

[0064] For example, referring to Figure 2 As shown, when the flight speed is relatively high (Ma ≥ 3), a larger curvature is adopted so that the entire air flow channel 22 is a curved surface with a larger curvature and higher heat exchange performance; for example, referring to Figure 3 As shown, when the flight speed is relatively low (Ma < 3), a smaller curvature is adopted, for example, the middle part of the partition 21 is relatively straight, and at this time the flow loss in the flow channel is small.

[0065] In specific implementation, the shape memory alloy partition can be heat-treated to ensure its shape memory performance.

[0066] Exemplarily, the partition 21 can specifically be a nickel-titanium alloy partition, which has excellent high-temperature resistance, corrosion resistance, heat conduction, and deformation memory performance.

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

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

[0069] By providing the heat exchange fins 24 in the air flow channel 22, the heat exchange area between the air and the air flow channel 22 is increased, and at the same time, flow dead zones can be avoided to a certain extent, thereby further improving the heat exchange efficiency. Moreover, the provision of the heat exchange fins 24 can also improve the structural strength of the heat exchanger core 2.

[0070] Further, the heat exchange fins 24 include a plurality of fin segments 241; in the second direction, the plurality of fin segments 241 are arranged in sequence, and a gap for air flow is formed between two adjacent fin segments 241.

[0071] By providing a plurality of fin segments 241, the heat exchange area is further increased, the flow dead zones are reduced, and thus the heat exchange efficiency is improved.

[0072] Among them, the region of the air flow channel 22 close to the outlet of the heat exchange working medium flow channel 23 is defined as the first region, and the region of the air flow channel 22 close to the inlet of the heat exchange working medium flow channel 23 is defined as the second region. Referring to Figure 1 , for example, the heat exchange working medium inlet is located at the top of the heat exchange working medium flow channel 23, the heat exchange working medium outlet is located at the bottom of the heat exchange working 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, a plurality of fin segments 241 are provided in both the first region and the second region, and the distance between two adjacent fin segments 241 in the first region is less than the distance between two adjacent fin segments 241 in the second region.

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

[0075] Referring to Figure 1As shown, in some embodiments, in the second direction, a plurality of fin segments 241 are spaced apart and arranged in parallel, and a gap for air flow is formed between two adjacent fin segments 241.

[0076] In other embodiments, in the second direction, a plurality of fin segments 241 are arranged in sequence, and one end of two adjacent fin segments 241 is close to and connected to each other, and the other ends of two adjacent fin segments 241 are far from each other, so that the heat exchange fin 24 forms a corrugated fin or a serrated fin.

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

[0078] Specifically, the heat exchange fin 24 can be connected to the partition 21 by brazing or other means.

[0079] Refer to Figure 4 and Figure 5 As shown, a flow passage area between the air inlet 11 of the housing 1 and the upstream side of the heat exchanger core 2 forms an area of sudden expansion 3. That is, the cross-sectional area of the air flow suddenly expands, and the sudden expansion of the area will cause gas backflow and pressure loss. Based on this, in some embodiments, a cross-section reducing member 4 is provided in the area of sudden expansion 3, and the cross-section reducing member 4 is connected to the housing 1.

[0080] By providing the cross-section reducing member 4 in the area of sudden expansion 3, the expansion ratio of the cross-sectional area of the air flow space can be reduced to a certain extent, thereby reducing the air flow loss and pressure loss to a certain extent, reducing the inlet separation risk, and further improving the heat exchange efficiency.

[0081] Specifically, the cross-section reducing member 4 can be connected to the inner wall of the housing 1 by welding or screws, etc.

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

[0083] This setting has a simple structure. While reducing the expansion ratio of the cross-sectional area of the flow space, it also plays a role in guiding the air flow, further guiding the air flow into the air flow passage 22 of the heat exchanger core 2, and further reducing the air flow loss and aerodynamic separation phenomenon, and further improving the heat exchange efficiency.

[0084] The cross-section reducing member 4 can be specifically located in the middle of the area of sudden expansion 3 to improve the uniformity of the air flow distribution.

[0085] Of course, in other implementation manners, the cross-section reducing member 4 may also be a structure such as a partition block, etc., and the structure such as a partition block is located in the middle of the area sudden expansion region 3.

[0086] It has been verified that for the pre-cooling heat exchanger for an aircraft provided by the embodiments of the present disclosure, the curved air flow channel 22 has a guiding effect on the air flow, can to a certain extent inhibit the flow separation caused by the inclined installation of the heat exchanger core body 2, and the uniformity of the velocity distribution in the heat exchanger core body 2 is increased by 30% to 50%. At the same time, the combined action of the enhanced turbulence intensity and the flow uniformity has increased the comprehensive heat transfer efficiency by at least 15% to 25%. Moreover, for the pre-cooling heat exchanger provided by the embodiments of the present disclosure, the pressure drop is reduced by 10% to 18%.

[0087] In specific implementation, the curvature radius of the partition plate 21 can be optimized according to the inclined installation angle of the heat exchanger core body 2 to ensure the coordination between the air flow turning and the flow channel setting of the engine 5. For example, the angle at the inlet of the heat exchanger core body 2 = the expected air flow deflection angle - the deflection angle of the area sudden expansion region 3. For example, when the inclined installation angle a of the heat exchanger is 10°, the expected air flow deflection angle is 80°, and the deflection angle of the area sudden expansion region 3 is generally about 10° to 30°.

[0088] The pre-cooling heat exchanger provided by the embodiments of the present disclosure can be specifically applied to an aeroengine, a variable cycle engine, a hypersonic turbine-based combined cycle engine, etc.

[0089] The embodiments of the present disclosure also provide an aircraft, including an engine 5 and a pre-cooling heat exchanger for an aircraft. Among them, the pre-cooling heat exchanger for an aircraft is located on the intake side of the engine 5 and is used to cool the intake air, reduce the temperature of the air flow at the inlet of the engine 5, offset the increase in the intake air temperature caused by the aerodynamic heating effect during high-speed flight, and enable the turbine to fly at a higher speed.

[0090] The specific structure and implementation principle of the pre-cooling heat exchanger for an aircraft in this embodiment are the same as those of the pre-cooling heat exchanger for an aircraft provided by the above embodiments, and can bring the same or similar technical effects, which will not be elaborated one by one here. For details, reference can be made to the description of the above embodiments.

[0091] The above description is only some embodiments of the present disclosure and an explanation of the applied technical principles. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosure concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present disclosure.

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

Claims

1. A pre-cooling heat exchanger for an aircraft, characterized in that, It includes a housing and a heat exchanger core located within the housing; The housing has an air inlet and an air outlet, and the air inlet and the air outlet are oppositely arranged on both sides of the housing. The air outlet is used to communicate with the engine air inlet of the aircraft; in the direction from the air inlet to the air outlet, the heat exchanger core is inclined in the housing; The heat exchanger core includes at least three partition plates that are sequentially stacked and spaced apart. Among every three adjacent partition plates, an air flow channel is formed between two adjacent partition plates, and a heat exchange working medium flow channel is formed between another two adjacent partition plates. The air flow channel is arranged along the first direction of the partition plate, and the heat exchange working medium flow channel is arranged along the second direction of the partition plate; the first direction and the second direction are perpendicular to each other; The partition plate is a curved partition plate, 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 communicates with the air outlet.

2. The pre-cooling heat exchanger for an aircraft according to claim 1, wherein In the first direction, the partition plate includes at least two sequentially connected arc-shaped guiding sections, and the bending directions of two adjacent arc-shaped guiding sections are opposite.

3. The pre-cooling heat exchanger for an aircraft according to claim 2, characterized in that, The joint of two adjacent arc-shaped guiding sections has a smooth transition.

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

5. The pre-cooling heat exchanger for an aircraft according to any one of claims 1 to 3, characterized in that, Heat exchange fins are arranged in the air flow channel.

6. The pre-cooling heat exchanger for an aircraft according to claim 5, characterized in that, The heat exchange fins include a plurality of fin segments; In the second direction, the plurality of fin segments are sequentially arranged, and a gap for air to flow is formed between two adjacent fin segments; The area near the outlet of the heat exchange working medium flow channel in the air flow channel is the first area, and the area near the inlet of the heat exchange working medium flow channel in the air flow channel is the second area. A plurality of fin segments are arranged in both the first area and the second area, and the distance between two adjacent fin segments in the first area is smaller than the distance between two adjacent fin segments in the second area.

7. The pre-cooling heat exchanger for an aircraft according to claim 5, characterized in that, The heat exchange fins include a plurality of fin segments; in the second direction, the plurality of fin segments are spaced and arranged in parallel, and a gap for air to flow is formed between two adjacent fin segments; Alternatively, the heat exchange fins include a plurality of fin segments. In the second direction, the plurality of fin segments are sequentially arranged, and one end of two adjacent fin segments is close to and connected to each other, and the other end of two adjacent fin segments is far from each other, so that the heat exchange fins form corrugated fins or serrated fins.

8. The pre-cooling heat exchanger for an aircraft according to any one of claims 1 to 3, characterized in that, An area sudden expansion area is formed in the flow channel area between the air inlet and the upstream side of the heat exchanger core; A cross-section reduction member is arranged in the area sudden expansion area, and the cross-section reduction member is connected to the housing.

9. The pre-cooling heat exchanger for an aircraft according to claim 8, characterized in that, The cross-section reduction member is an arc-shaped plate extending along the air flow direction and arranged on the upstream side of the heat exchanger core.

10. An aircraft, characterized in that, It includes an engine and a pre-cooling heat exchanger for an aircraft according to any one of claims 1 to 9; The pre-cooling heat exchanger for an aircraft is located on the air intake side of the engine.

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